Engineering Research Institute University of Michigan Ann Arbor FOURTH QUARTERLY PROGRESS REPORT TO MATERIALS LABORATORY, WRIGHT AIR DEVELOPMENT CENTER DEPARTMENT OF THE AIR FORCE ON INTERMEDIATE TEMPERATURE CREEP AND RUPTURE BEHAVIOR OF TITANIUM AND TITANIUM ALLOYS By J. V. Gluck J, W. Freeman Contract No. AF 33(616)-244 Supplemental Agreement No. S-1 (53-247) Expenditure Order Nos. R605-225 SR 3c R.605-227 SR 3a R615- 11 SR 3c Project 2076 covering the period 16 April 1953 to 15 July 1953

SUMMARY This report, the fourth under contract AF 33(616)-244, covers the period from April 16, 1953 to July 15, 1953. The object of the investigation is to establish general principles relating types of microstructures of typical titanium base alloys to rupture and creep resistance in the range from 6000 to 1000~F. Rupture testing is now complete at 600~, 800~ and 1000~F on Ti 75A and Ti 150A. Rupture testing at 600~ and 1000~F is complete on three conditions of the experimental alpha alloy (6%A1l) and three conditions of the experimental beta alloy (30% Mo), Creep tests on all materials are in progress, Metallographic and x-ray studies have revealed changes in microstructure as a result of testing. The meta-stable beta alloy (10% Mo) has not yet been received.

2 INTRODUCTION The present report, covering the period from April 16, 1953, to July 16, 1953, is the fourth to he issued under Contract AF 33(616)244. The investigation is sponsored by the Materials Laboratory- Wright Air Development Center. The purpose of the investigation is to study creep and rupture behavior of titanium and its alloys in the range from 600~ to 10000F, Five alloys are included in the study. They were selected to be representative structural types. They include: 1. Commercially pure titanium (Ti 75A) 2. Commercial martensite-forming alloy (Ti 150A) 3. Stable alpha alloy (6% Al) 4. Meta-stable beta alloy (10% Mo) 5. Stable beta alloy (30% Mo) The latter three alloys are being obtained in the form of small experiznental heats from the Armour Research Foundation. All materials have been received, save the meta-stable beta alloy. Treatments were selected so as to explore as fully as possible the microstructural conditions appropriate to each alloy, The number of tests has been limited so that as many as possible of the conditions of heat treatment of interest may be surveyed in the period covered by the present contract. Thus, for each condition and at each temperature, are run a tensile test, two rupture tests (up to 100-150 hours), and a creep test. Data from each test are utilized in planning the succeeding one, the long-time creep test being the last one run. Microstructural examination is made of specimens after testing in order that changes, if any, can be correlated with creep and rupture behavior,

3 By taking as much data as possible during each test, it is possible to make a limited analysis on the basis of total deformation criteria, RESULTS AND DISCUSSION A detailed discussion of the aims and method of attack of this investigation was presented in the First and Second Progress Reports (dated October 15, 1952, and January 15, 1953, respectively). The Third Progress Report (dated April 15-, 1953) presented considerable tensile data and some rupture data for all materials. No comparison was made between materials. Sufficient data have now been accumulated to permit some comparison between the alloys under investigation. Each alloy is discussed separately and appropriate comparisons are made where possible. Following the discussion of the alloys, there has been tabulated, on the basis of creep and rupture criteria, a very tentative quantitative comparison. Commercially Pure Titanium (Ti 75A) Rupture and tensile tests at 600~, 800~ and 1000~F are now n"arly complete for the seven conditions of commercially pure titanium (Ti 75A) chosen for study in the initial phase of the investigation. In addition, two-thirds of the creep tests at these temperatures have been completed and the others are in progress. The conditions studied include as-received (hot rolled and annealed), re-annealed at either 1500~ or

4 1700~F, and 10,9%- and 31. 3% cold work for each of the re-annealing temperatures. Metallographic and x-ray techniques have been used to study completed rupture and tensile specimens. Rupture Properties of Ti 75A Rupture test results at 800~ and 1000~F for seven conditions of Ti 75A were presented previously in both tabular and graph form. * The present report extends these results to 600~F (see Table I). The data are also plotted on Figures 1, 2, 3 and 4. At 600~F, as-received or annealed Ti 75A possess an extremely flat rupture curve. A change in stress of only 1,000 psi may extend rupture life by over 1000 hours. Consequently, selection of test stresses has-been difficult, To further complicate the matter, cold worked conditions of Ti 75A are somewhat more stress dependent for rupture life. Thus, the criteria for choosing rupture stresses for the annealed material could not be successfully applied to the cold worked case. Table I thus presents the best estimate that could be made under the circumstances of 100-hour rupture strength. In conjunction with previously reported data from the higher temperatures, these results have been plotted as a function of the amount of cold work on Figure 5. Here it will be seen that the strengthening effect of cold work is considerably diminishing in going from 600~ to 800~F and eliminated almost completely at 1000~F. To further emphasize this result, a plot was presented in the previous report** which showed a linear decrease of the quotient * Third Progress Report, Contract AF 33(616)-244, April 15, 1953, Table I and Figure 4. ** Third Progress Report, Figure 5.

5 100-hour Rupture Strength tiate Teniel Strength with increasing temperature. Thus, at Ultimate Tensiel Strength 600~F the quotient was about 0.94, and at 1000~F it fell to 0.21. It is believed that the quotient approaches 1. 0 asymptotically for decreasing temperatures. This effect is shown to have some generality for titanium and its alloys in Figure 6. Here data obtained for Ti 150A, a ferrochrome ternary alloy, show good agreement with the Ti 75A data. This will be discussed in a succeeding section. The inference to be drawn is that, barring reduction of strength by extreme brittleness (a condition encountered in room temperature tests of Ti 150A strip specimens in another investigation*), the rupture strength at temperatures up to 600~F is approximately equal to the ultimate tensile strength, i.e., between 95 to 98% of it. Yet, appreciable deformation does occur at stresses immediately below the rupture strength without leading to rupture, as will be shown later. At 600~F, tests on Ti 75A at stresses only very slightly below the tensile strength were characterized by a high initial deformation on loading and immediately thereafter, and then a very small second stage component with no indication of third stage creep. (Duration of longest test was 1500 hours.) The question of deformation will be covered more fully in a later section of this report. A consideration of rupture strength alone shows with increasing temperature both.a greatly increased stress dependency and a lowered cold-working dependency. Creep and Total Deformation Studies of Ti 75A Creep testing of Ti 75A at 800~ and 10000F has progressed to the point where some indication of the relationship can be presented * Under Contract AF 33(038)-14111.

6 (Figure 7). Of interest is the extremely high stress dependency of creep rate at these temperatures. Little difference, if any, was found between the annealed and cold worked conditions -- cold working did decrease creep rate somewhat. At 600~F it is noted that annealed and as-received conditions showed very low second stage creep rates even after appreciable deformation during loading and during first-stage creep. This was found for stresses about 98% of the ultimate tensile strength. It is believed that creep tests at 600~F now in progress on cold worked material will show a definite second stage since stress dependency of rupture results for these materials appears to be increased. In Table II are presented a tabulation of all creep data on Ti 75A to date together with an estimate of the stress to cause a minimum rate of 5 x 10 in. /in. /hr. (roughly equivalent to the 1000-hour rupture strength). For this criterion, the stress at 800~F ranged from only 5, 000 to 10, 000 psi and at 1000~F is between 1,500 and 3,500 psi. The ranges resulted from varying treatments. It will also be noted that the ratio of the rupture strengths to the creep resistance increases with increasing temperature. Total deformation characteristics have been determined (as far as the available data permits) for all conditions at 800~ and 1000~F and for only the annealed condition at 600~F. These are presented in Figures 1, 2, 3 and 4. Salient points to be noted are the large amounts of total deformation at 600~F on annealed or as-received stock without lowering of rupture life. Also to be noted are the high elongations in rupture tests at 1000~F. One-per cent total deformation was reached at 1000~F in one-hundredth to one-tenth of the rupture life at that stress. This is also emphasized by the low stresses for a given minimum creep rate —discussed in the preceeding paragraph.

7 A correlation with lower temperature creep test results* is shown in Figure 8. Here the stress for a minimum creep rate of 3 x 10 6 in. /in. /hr. (0. 3%/1000 hours) has been determined over a range from 76~ to 1000~F. A strengthening, characteristic of a strain aging reaction, is noted at 400~F following which the relationship drops off rapidly. Above 800~F, the indications are that the stress for:the cre'ep rate correlated approaches zero. Metallographic Studies of Ti 75A Metallographic studies have been made on several completed tensile and rupture specimens. Some difficulty has been experienced in;the prevention of pitting of electro-polished samples. Little change, if any, has been noted on micro-structure as an effect of stress and/or temperature. Figure 21 is representative of the type of structure obtained. It shows a sample originally annealed from 1700~F after testing at 1000~F and 6, 500 psi. When correlated with Figure 20, the same structure previous to testing, little effect is noticeable. X-Ray Studies of Ti 75A Several x-ray diffraction traverses have been made on representative conditions of Ti 75A before or after testing, employing a Norelco Hi Angle geiger tube spectrometer equipped with a Brown recorder. Studies to date have been confined merely to identification of diffracted lines. * Obtained with strip specimens under Contract AF 33(038)-14111.

8 Commercial Martensite-Forming Alloy (Ti 150A) Although described as a martensite-forming alloy, Ti 150A, a ferro-chrome ternary alloy of titanium, shows very poor properties when such structures are tested. It can also be characterized as an alloy undergoing eutectoid decomposition. In either case, structures most appropriate to creep and rupture testing (reasonable room temperature tensile ductility) were only found for conditions of treatment solely within the a + p phase region, or solution treated in the P region followed by isothermal transformation in the a + P region. Accelerated cooling from the P region (producing the martensite structure) results in excessive brittleness. Hence, treatments under investigation in the present study represent different methods of approach to variation of a + P proportions. Employing two solution temperatures, 1350~ and 1500~F, either furnace cooling, air cooling, or water quenching was used from each temperature. In addition, subsequent re-heating to lower temperatures of the above treated material was used, and full isothermal transformation at 1000~ and 1300~F after solution treatment at 1800~F was also studied. Rupture tests are almost complete at 600~, 800~, and 1000~F for most of these conditions. In addition, tensile test results were obtained for several conditions not reported previously. Some creep test results have also been obtained. Metallographic and x-ray studies are also reported. Tensile Properties of Ti 150A A complete presentation of tensile properties of Ti 150A at 600~, 800~ and 1000~F was given in a preceding report for conditions

9 of single heat treatment and isothermal treatment * Additional data have now been obtained at 75~, 800~ and 1000~F on two conditions of double heat treatment: 1500~F water quench + 1350~F anneal, and 1350~F water quench + 900~F anneal. These are presented in Table III. The annealing at 1350~F of material originally water quenched from 1500~F produces properties at 75~ and 1000~F identical to a 1350~F anneal alone. This is a case of reheating into the a + P region (lower boundary approximately 1050~F.) If, however, re-heating is done to a temperature below the a + p region, then a different effect is to be noted. Material reheated to 900~F after a 1350~F water quench shows a tendency to be embrittled, Thus, brittle failure in the threads at 193, 000 psi was found in contrast to 18% elongation and a 170, 000 psi tensile strength for the stock water quenched only and not reheated. While less marked at higher test temperatures, nevertheless there exists a tendency for the doubly heat treated material to show less elongation at comparable tensile strengths. The as-quenched and 900~F re-heated structure, Figure 42, shows nothing to differentiate it from the merely as-quenched structure, Figure 30. On re-heating to 1350~F after a 1500~F water quench, a structure of large a grains similar to a 1350~F anneal alone (Figure 40) is found. However, a dark etching precipitate is noted in the matrix of the doubly treated s ample. Rupture Properties of Ti 150A Results of all rupture testing to date at 600~, 800~ and 1000~F on eleven conditions of Ti 150A are summarized in Table IV and plotted in Figure 9, One-hundred hour rupture strengths were determined indi* e Third Progress Report, Table II and Figures 7 and 8

10 vidually for each condition at each temperature and are summarized graphically in Figure 10o In conjunction with Figure 9 it will be noted that a rather narrow band encompasses all results at 1000~Fo Little variation from prior treatment was found in 100-hour rupture strengths. At 600~ and 800~F, the results separated into three bands. The as-received or annealed structures —save that for a 1500~F water quench —can be lumped together; and the 1500~F water quench stands alone. No breaks in the rupture curve such as were found at 800~F in the case of Ti 75A were found for Ti 150Ao From the bar graph, Figure 10, it was then possible to plot on Figure 11 the 100-hour rupture strength for the three "grouped" treatments as a function of test temperature. Tensile strengths at these temperatures were similarly plotted on the same figure. The quotient, 100-hour rupture strength ultimate tensile strength for each group for each temperature was plotted in Figure 6, showing an extremely good agreement with those previously obtained and discussed for Ti 75Ao Thus, some generality of this ratio appears to be the case, The effect of alloying is to almost double or triple the rupture strength at each temperature over that of Ti 75A. Nevertheless, the absolute level of the strengths for Ti 150A were not high at 800~ and 1000~F. In particular, at 1000~F the 100-hour rupture strength was only about 12, 500 psi, Creep Properties of Ti 150A All available creep data from this investigation for Ti 150A at 600~, 800~ and 1000~F are tabulated in Table V and plotted in Figure 12, A.t 1000~F variations from heat treatment to heat treatment was so

11 slight based on available data that one line has been deemed satisfactory to correlate the datao At 800~F the influence of heat treatment required the data be broken down to "groups" similar to the case of rupture strengths discussed previously. Data at this temperature are still extremely limited, The only points available at 600~F are shown in Figure 13 in relation to 600~F tests of similarly treated strip specimens0 Indeed, it is quite surprising to find such close adherence to the same straight line, (Incidentally, strip specimens could not be tested satisfactorily above about 65, 000 psi due to brittlenesso ) In relation to these results it will be noted that a considerable increase in stress dependence of creep rate occurs in going to 800~F and even more so at 1000~F. A relationship over the entire range from 76~ to 1000~F is plotted in Figure 8 of the stress to cause a creep rate of 3 x 106 in. / in. /hr. in as-received Ti 150A with a similar relation plotted for Ti 75A. The lower temperature data was taken on strip specimens. * The general features of both plots are the strengthening at 400~F from strain aging and the rapid drop with increasing temperature at 600~F and aboveo Metallographic Examination of Ti 150A A number of samples of Ti 150A have been examined metallographically to study the effects of temperature, stress and/or time on microstructure occurring as a result of testing. Changes involving a decomposition of 3 have been found in a number of conditions whose treatment was solely within the a + P regiono Similar results had previously been noted at lower temperatures on strip specimens of Ti 150A. g Beginning with the as-received material, a progressive type of precipitation in the,3 matrix was observedo That this is dependent on * Under Contract AF 33(038)-14111.

12 temperature is shown in Figures 22 and 23. Thus, 979 hours at 600~F and 80, 000 psi did not result in a significant micro.structural change, yet, only 150 hours at 1000~F and 12, 000 psi did show a change. A similar effect was found with 1500~F annealed material. All tests at 600~ and 800~F had structures as shown in Figure 24 (an 800~F tensile test), while exposure at 1000~F and 111,000 psi for 116 hours showed a deterioration of the P similar to the as-received material tested at 1000~F (Figure 25). When the material is given an original accelerated cooling treatment, then structural alterations are greatly increased, The ascooled structures show decreased amounts of a depending on solution temperatures in the two phase region and cooling rate. Upon testing, changes in microstructure occur. For instance, Figure 26 shows a sample air -cooled from 1500~F and then tensile tested at 800~F. No change over the as-treated structure was noted, Similarly, 10o.5 hours at 800~F and 52, 000 psi, Figure 27, was not sufficient to produce any noticeable change. However, a tensile test at 1000~F was sufficient to result in considerable precipitation in the matrix (Figure 28). Similarly, 16 hours at 1000~F and 16, 000 psi, Figure 29, resulted in greater precipitation, A longer time at a lower stress produced somewhat different results, Figure 30 (188.8 hours at 1000~F and 11,000 psi) is anomalous. It shows what could be the beginning of a precipitation reaction or the end of an agglomerating process, Because of the different character of the precipitate between the tensile test and 16 hour test on one hand, and the 188, 8 hour test on the other, it is difficult to make a clear cut statement as to its nature at this time, After water quenching from 1500~F, the structural changes are still more extensive, Figure 31 shows the result of 2, 3 hours at 800~F

13 and 85 000 psio No change in the as-quenched structure was notedo Apparently the time at 8000F was too short since 1000-hour creep tests at 600~F of this condition on strip samples did show precipitation. When tensile tested at 1000~F (Figure 32) considerable precipitation occurred. Extension of 1000~F test time to 348. 8 hours (Figure 33) at 9, 000 psi showed progression of the reaction, Figures 34 and 35 show respectively the result of a tensile test at 800F and 34 hours at 10000F and 14, 000 psi on material annealed from 1350~Fo Results were similar to those noted for 1500~F annealing. Figure 36 shows a 1350~F air cooled specimen after 43. 5 hours at 800~F and 55,000 psi. Figure 37 shows the same original treatment after 194, 3 hours at 1000~F and 11,000 psi. Matrix precipitation is noted in the case of the latter. Similarly, Figures 38 and 39 show a 1350~F water quench after a 600~F tensile test and 16. 7 hours at 1000~F and 15,000 psi respectively. A. matrix effect is again noted, When a specimen rapidly cooled from the a +,3 region is then annealed in the a + P region, microstructural changes follow to a degree the effect on properties. For instance, a 1500~F water quenched plus 1350~F annealed treatment was shown previously to have properties quite close to those of the 1350~F annealed treatment alone. Figure 40, a 1000~F tensile test of this condition, shows large a grains in a dark etching matrix very similar to a 1350~F anneal (also very similar to 1500~F anneal), Figure 41 shows the progression of this reaction after a rupture test for 43 hours at 1000~F and 13, 000 psi. If, however, re-annealing is carried out below the a + P3 region the results are quite different, Not only is strength retained, but the microstructural effects are different. * Under Contract A.F 33(038)-14111.

14 Figure 42 shows the structure of a 1350~F water quench plus 900~F annealing treatment essentially as treated (tested at 75~F). Figure 43 shows the same structure after an 800~F tensile test, Here, matrix precipitation has occurred. A longer time at a lower stress appears to show a different effect. Thus, 37 hours at 800~F and 58, 000 psi result in a structure (Figure 44) showing only the barest beginnings of any reaction or perhaps the end of the reaction with the product going to the grain boundaries, It is, therefore, possible to characterize microstructural changes in Ti 150A in the following manner: 1. They are favored by higher temperatures. 2, Times are short at 1000~F and considerably longer at 800~ and 600~F (up to 1000~F). The nature of this dark etching product has not been positively determined. There is a further possibility that it may be the result of hydride formation * Enough evidence does exist from this and other investigations**, ***, to substantiate the conclusion that it is the result of a eutectoid decomposition reaction. The composition of this alloy is such as to favor precipitation of Ti Cr2 from non-equilibrium beta structures, The eutectoid is then formed from a and Ti Cr2. Further study of these and other effects is to be made. Examination of isothermally transformed structures after testing has not yet revealed any clear cut results. * Battelle Memorial Institute, Second Progress Report on Development of Improved Titanium Base Alloys, April 20, 1953/ ** Contact AF 33(038)-14111. ~*** "Constitution of Titanium Alloy Systems," WADC Tech, Report 53-41, (Hansen et al,), pp. 185-194 (Feb. 1953.)

15 X-Ray Study of Ti 150A X-ray diffraction traverses have been made on a limited number of representative conditions of Ti 150A after testing. The results are briefly summarized in Table XI. Because of difference in sample size, it was impossible to obtain a correlation by line intensities. This was dictated because the actual specimens, representing different reductions of area, were used. Rather, the number of discrete a lines and P lines observed has been recorded. As expected, conditions of accelerated cooling tend to have a fairly high number of I lines. These, in turn, disappear under conditions of testing. Since non-equilibrium 3 is retained under fast cooling, it is only reasonable that the material should seek equilibrium and is thus aided by stress, time and temperature. Hence the reduction in the number of p lines is to be expected, Experimental Alpha Alloy (6% Al) Rupture testing of the experimental alpha alloy, a binary containing 6%o Al, has been confined* in the period covered by this report, to completion of the study of the treatments outlined in the previous period. Results are now complete at 600~ and 1000~F for one quenched condition and two cold worked conditions. Some creep data are also available. Metallographic examination has been made on a number of specimens after testing. Exploratory x-ray work was also started. Rupture Properties of Alpha Alloy (6% Al) Rupture tests are now complete at 600~ and 1000~F for three conditions of the experimental 6% Al alpha alloy. The conditions are: water quenched from 2025~F, and 10% and 17% cold work respectively, The data are summarized in Table VI and plotted on Figure 14,

16 Several points are evident from examination of the data, The relationships at 600~F is a very flat one. Very slight changes in stress (1000 to 2000 psi) may change rupture life by over 1000 hours. In this respect, the behavior of the aluminum alloy is even more sensitive than that of Ti 75A. Very little improvement from cold working up to 17-per cent reduction resulted. At 1000~F the 100-hour rupture strengths are fairly high, 26, 000 to 39, 000 psi. The deleterious effect of an increased amount of cold work on rupture strength at 1000~F should be noted. If the condition of water quenching from 2025~F can be regarded as the unstressed, uncold-worked alpha condition, then the effect is quite striking and consists of a progressive decrease in rupture properties with increased cold work. This will be checked by testing material which has not been rapidly cooled from as high a temperature as 2050~F. Some metallographic evidence exists to support the possibility of recrystallization as being the reason for this effect. It will be discussed subsequently. Creep Properties of Alpha Alloy (6% Al) All creep data available for the experimental alpha alloy are summarized in Table VII and plotted on Figure 15. The results are still limited, expecially at 600 F. As was noted in the case of rupture properties, creep properties, too, show a decrease with greater amounts of cold work. This seems to be greater at 1000~F than at 600~F. The stress for a minimum creep -6 rate of 5 x 10 in, /in. /hr. was estimated from extremely sparse data and appears to be surprisingly low in comparison with the seemingly favorable rupture properties at 1000~F. At 1000~F it was found to be in the range from 5, 000 to 10, 000 psi in relation to a 100-hour rupture strength

17 of about 35, 000 psi. Yet, in the case of Ti 150A, the stress for 5 x 10-6 in /in. /hr. minimum creep strength is about 11,000 psi. Since the strength for a given minimum creep rate is about the same for both the 6% Al alloy and Ti 150A, and Ti 150A shows much lower rupture properties, it appears that the difference between first stage or third stage creep deformations are the controlling factors in these alloys. Metallographic Examination of Alpha Alloy (6% Al) A number of completed tensile and rupture specimens of the experimental alpha alloy were examined metallographi cally. Some significant changes could be noted as a result of test conditions. Figure 45 shows a sample (at 100X magnification) after a tensile test at 1000~F. Although not as well definied, the structure is very similar to the as-quenched structure, * An example of the type of structural alteration possible in this material is shown in Figure 46, giving the effect of an accidental overheat of a test of the same structure after a long time at 600~F. After 1443.9 hours at 600~F and 96,000 psi the test was accidentally overheated to at least 1600~F and, of course, ruptured long before 1600~F was reached. The effect on the structure is to grossly exaggerate it. At 50X magnification the individual grains, although still bearing evidence of definite crystallographic orientation, are much enlarged. A different effect was noted for the cold work conditions. This is the effect of recrystallization occurring during testing. Figure 47 shows material given 17% cold work and tested 1172. 2 hours at 600~F and 101, 000 psi Little difference was noted between this and the astreated structure.** Figure 48 shows the effect of a tensile test on this * Third Progress Report, April 15, 1953, Figure 30. ** Ibid., Figure 29.

18 structure at 1000~F, Some slight changes are in evidence, Quite a different effect is noted for a rupture test. Figure 49 shows the same material (17% cold work) after 13.4 hours at 1000~F and 37,000 psi. Here it appears that some sort of recrystallization process has taken place. The structure seems to consist of small equiaxed grains in contrast to the elongated, as-forged structure of the proceeding conditions, A somewhat confusing picture is obtained from a study of the structures from the 10% cold worked condition. This is most probably due to non-homogeneous deformation. Figure 50 shows a structure after a 600~F tensile test. It shows little change over the as-treated structure.* Figure 51 shows the same structure after 1216 hours at 6000F and 96,500 si. Again, little change is evident. Figure 52, after a 1000~F tensile test, suggested that a seeming recrystallization has occurred under conditions of stress and temperature. Figure 53, after 20. 5 hours at 1000~F and 40, 000 psi, shows no such effect, although the as-forged and cold worked structure appears diffuse and may be on the verge of recrystallization. Figure 54 lends credence to this possibility. After 176.4 hours at 1000~F and 26, 800 psi, it does seem to be in progress. The foregoing facts of the recrystallization may be summarized as follows: Condition Temp (~F) Type Test, Stress, Time Progress of ~____~____ ___~____ ___~___ Recrystallization 10% Cold 600 Tensile - 97,800 psi none Work 600 1216 hr - 96,500 psi none 1000 Tensile - 83,300 psi fairly complete 1000 20, 5 hr - 40, 000 psi on verge 1000 176. 5 hr - 26, 800 psi in progress 17% Cold 600 1172 hr - 101,000 psi none Work 1000 Tensile - 82,400 psi doubtful 1000 13.4 hr - 37,000 psi complete * Third Progress Report, April 15, 1953, Figure 28,

19 The existance of anomalies in the data at 600~F is recognized and being investigated. Quite possibly these are due, as mentioned before, to non-homogeneous deformation. In any case, recrystallization appears to be favored by high stress or long time and occurs in time periods under 1200 hours only at 1000~F. X-Ray Study of Experimental Alpha Alloy (6% Al) One complete diffraction traverse was run for exploratory purposes on the experimental alpha alloy after testing at 1000~F. The specimen investigated was the condition of 10%o cold work after testing at 1000~F for 176.4 hours at 26,800 psi (Figure 54). Thirteen a lines were identified out of a possible twenty in the range covered by the high angle spectrometer. No beta lines were found. Experimental Stable Beta Alloy (30% Mo) S tudy of the experimental stable beta alloy, a binary containing 30% Mo, has continued with exploratory tensile testing of heat treated conditions and continuation of rupture and creep testing of conditions outlined previously. Metallographic examination revealed formation of a precipitate in this material at 1000~F. X-ray studies suggest this may be a phase. Tensile Properties of Stable Beta Alloy (30% Mo) Several additional conditions of the experimental stable beta alloy were tensile tested in order to establish conditions promising for creep and rupture testing. In addition, testing of the as-forged material was initiated.

20 In Table VIII the results of the tensile testing performed in this period are summarized. Data at two temperatures for material water quenched after 1 hour at 1325~F was included for comparison purposes. The as-forged material was found to have only a very slight difference in tensile properties at 75~ over the 1325~F water quenched stock. To explore the effect of a different solution treatment, stock was heated to 1500~F for 2 hours and then water quenched. Properties are almost identical with the 1325~F treatment. One test at 75~F is available for a "double" heat treatment. Material was held at 1500~F for 2 hours and water quenched. It was then reheated to 1375~F for 24 hours and water quenched. The effect of this treatment was to lower the 75~F tensile properties slightly, In addition to the above, a cold working treatment was attempted on this alloy, Four bars were solution treated at 1325~F for 1 hour and then water quenched. An attempt was then made to cold reduce the bars. Two of the bars were reduced about 3 to 3. 5 per cent. Both the other bars split on attempts to obtain reductions only slightly greater than 3. 5%. In view of the 12% reduction on tensile testing, it was expected that more cold work than 3. 5% could be put into the material. Thus far, it appears that the 30% Mo alloy is relatively insensitive to heat treatment and not amenable to cold work. Rupture Properties of Stable Beta Alloy (30% Mo) Rupture testing at 600~ and 1000~F was continued on the asforged and 1325~F water quenched conditions of the experimental stable beta alloy. The data are summarized in Table IX and plotted in Figure 16. The relationship at 600~F is extremely flat, as is characteristic of other alloys at this temperature. At 1000~F the points for all

21 conditions of testing fall on the same line. A check test at 1000~F was run on a sample water quenched after 2 hours at 1500~F. It was run at 37, 500 psi, the estimated 100-hour rupture strength for this material. The slightly short rupture time of 83.4 hours appears to be in good agree. ment with the other treatments. For the heat treatments tested to date, no essential differences in rupture properties exist. Creep Properties of Stable B-eta Alloy (30% Mo) Only very limited creep data are available for the experimental stable beta alloy. The data are summarized in Table X and plotted in Figure 17. At 600~F the results of one test at 90, 000 psi are all that presently are available for the 1325~F water quenched condition. The test duration was 1485 hours and, following a short period of first stage creep, the minimum creep rate was very low. At 1000~F the results from the as-forged and 1325~F water quenched conditions were found to be correlated by the same line. The estimated stress for a minimum creep rate of 5 x 10-6 in. /in. /hr. was 10, 000 psi for the 30% Mo alloy. This indicates a higher ratio of creep to rupture strength than has been obtained for other alloys tested. This may be of considerable importance because the creep strength in the other alloys has appeared to be abnormally low in relation to rupture strength with the implication that excessive deformation by creep at stresses well below the rupture strength would severely limit load carrying ability. Metallographic Examination of Stable Beta Alloy (30% Mo) Several conditions of the experimental stable beta alloy have been examined after tensile and rupture testing in order to ascertain if

22 changes occurred in the microstructure. Very conclusive evidences of a precipitation reaction have been found for tests at 1000~F and long times. Figure 55 shows the as-forged structure after testing for 77 hours at 1000~F and 40,000 psi. No change can be noted over the untested structure.* However, the same condition after 133 hours at 1000~F and 35, 000 psi (Figure 56) shows a fine, dark precipitate within the P grains. The 1325~F water quenched material exhibits the same behavior. Figure 57 shows the structure after 836 hours at 600~F and 100,000 psi. Slight precipitation, if any, is visible. Figure 58 shows the same condition after 141.2 hours at 1000~F and 35, 000 psi. The precipitate is finer, but, more widely dispersed than that noted in the as-forged condition. Specimens were also examined for the condition of 2 hours at 1500~F plus a water quench. Figure 59 is the structure after a tensile test at 1000~F. No evidence of precipitation is visible. However, 83.4 hours at 1000~F and 37, 500 psi (Figure 60) was sufficient to cause the initiation of precipitation within the P grains. It appears to form in lines along crystallographic planes as dispersed particles. The nature of this precipitate is not clear; however, evidence does exist from x-ray data to suggest a phase as a component. This will be discussed in the next section. The formation of the precipitate is favored by a temperature of 1000~F and time periods of about 100 hours. The stress condition (35, 000 to 40, 000 psi) undoubtedly has some effect. X-Ray Study of Stable Beta Alloy (30% Mo) The specimen whose microstructure appears in Figure 58 was examined by x-ray diffraction analysis in an effort to discern the nature * Third Progress Report, April 15, 1953, Figure 31.

23 of the observed precipitate. The specimen was given the 1325~F water quench treatment and tested 141.2 hours at 1000~F and 35,000 psi. A complete traverse with a high angle geiger tube x-ray spectrometer was made on the sample. Although the material is supposed to have an all3 structure, the a 100 and 102 lines were definitely identified. In addition, the appearance of the a 002 and 103 was also suspected, although they were not strong enough for a positive identification. It thus appears likely that the precipitate in this sample at least contains a. Comparison between Alloys Sufficient data have now been accumulated to premit some comparison between the various alloy types to be made. This has been done in Table XII on the basis of two criteria, 100-hour rupture strength and stress to give a minimum creep rate of 5 x 10 6 in. /in. /hr. The data are also plotted in Figures 18 and 19. Several points appear worthy of mention at present. First, both Ti 75A and Ti 150A show relatively poor properties above 800~F and little difference in properties exists between treatments at 1000~F. The experimental binary alloys show moderate tensile and rupture strength properties at temperatures up to 600~F, yet retain considerably greater strength at 1000~F than do the commercial alloys. In addition, all alloys have the common characteristic of permitting relatively large amounts of loading and first stage creep deformation. In addition, rupture life appears to be quite high in relation to the amount of deformation that has occurred. The next report will explore these points more fully.

TABLE I Rupture Results at 600~F for Ti 75A Test Stress Time Elongation Reduction Minimum 100-Hour Treatment Temp of Area Creep Rate Rupture Strength (F) (psi) (hrs) (% in 1 in. ) (%) (in/in/hr) (psi) As Received 600 37,600 0. 1 34.9 68.6 - 37,000 0. 15 45.0 65.5 35,000 >911.0 (5.5)* -- 4. 7x 10-7 33,000 >1313.6 (2.8)* — <108 36,000 1500~F An- 600 34,900 0. 1 41.5 67.0. nealed (1 hr at 33,000 0. 3 43.5 71.5 - temp + furnace 32,000 >977. 7 (7.4)* — <10c6ol) 28,000 >1512.0 (3.7)* -- <10-8 32,500 1700~F An- 600 33,600 0. 1 40.7 69.6 nealed 31,500 0.2 34.0 55.4 4 30,000 >975. 1 (7. 8)* <10-8 25, 000 >1002.9 (1.9)* -- <108 31,000 1500~F An- 600 53,300 0. 1 14.6 57.5 -- nealed + 10.9% 51,000 0.3 14.7 45.0 - cold work 48, 500 1.0 14.7 57.0 -- 45,000+ 1500~F An- 600 67,000 0. 1 13.3 51. 1 nealed + 31.3% 64,000 0.2 16.5 52.0 -- cold work 61,000. 0.2 15.4 46.6 -- 55,000+ 1700~F An- 600 53,700 0. 1 14.8 55.2 - nealed + 10.9% 51, 000 0. 1 13. 1 53.5 -- cold work 45, 000 54.4 not available yet -- 44,000 1700~F An- 600 66,500 0. 1 14.0 57. 5 - nealed + 31. 3% 62, 000 0. 1 15.5 56.2 - cold work 59,000 0.3 14.4 59.5 -- 55,000+ * Permanent deformation after test - did not rupture. NOTE: Tensile test used as 0. 1-hour rupture. > Greater than, i.e., did not rupture, test stopped.

TABLE II Creep Rates at 600~, 800~ and 1000~F for Ti 75A Test Stress Minimum Test Est. Stress for Treatment Temp Creep Rate Time Rate of 5 x 10-6 (F) (psi) (in/in/hr) (hrs) in/in/hr -7 As Received 600 35,000 4.7 x 107 911.0 33,000 <10-8 1313.6 800 16,000 8.6 x10-4 156. 0 7,000 1.8 x 105 736.0 5,000 1000 5,000 6.0 x 10-3 54. 4 2,000 5. 0 x 105 575. 0 1,500 1500~F An- 600 32,000 <108 977 7 nealed (1 hr at 800 20,000 1.9 x 10"' 54. 1 temp + furnace 16,000 8.3 x 104 126. 6 cooled) 6 000 1.8 8x105 779.5 5,000 1000 5,000 3.4 x 10-3 92.5 2,500 1.6x10-4 1126.4 1,500 1700~F An- 600 30,000 <108 957.1 nealed 800 15, 000 8.0 x 10- 184. 3 6,000 3.8 x 10' * 5,000 1000 5,500 6.0 x 10'3 65.2 2,500 1.4 x 10-5 766.0 1,500 1500~F An- 600 40, 000 not available * nealed + 10.9% 800 19,000 2.8 x 104 159.4 cold work 12,000 5.0 x 10-5 1052.4 8,000 100a 6,500 1.9x 10-3 88.4 4,000 8. 0x10-4 259.8 3,500 1500~F An- 600 50,000 not yet available * nealed + 31.3% 800 22,000 4.2 x 10-4 69.9 cold work 15,000 not available * 10,000 1000 4,200 1.6x10-3 120.1 2,500 1.3x10-4 1200.0 <1,000 1700~F An- 600 not available * nealed + 10.9% 800 22,000 22 x 10-3 63.0 cold work 14, 000 not available * 1000 7,000 3, 6x10-3 60.0 5,500 6.7 x 105 220. 2 4,200 2. 1x 10-5 610.0 3,500 1700 F An- 600 not available * nealed + 31. 3% 800 0,000 7.6 x 104 180. 6 cold work 15,000 not available * 10,000 1000 6,500 8.0 x 10-3 25. 8 5,000 1.6x 10'3 80.5 _3,000 3.5 x 104 765.0 <1,000 * Not Completed yet.

TABLE Ill Tensile Test Data for Ti 150A (not reported previously) Test Ultimate Yield Elongation Reduction Elastic Treatment Temp Strength Strength of Area Modulus f___________ (~F) (psi) (0 2% Offset) (% in 1 in.) (%) (x 10 psi) 1500~F Water 75 156,900 152,800 14.6 15.2 16.6 Quench + 1000 39,500 32,300 123.0 98.4 8.2 1350~F Anneal 1350~F Water 75 >193,000 Broke in threads -- 14.7 Quench + 800 98,800 59,000 31.8 76.0 9.5 9 00F Anneal 1000 43,500 25,800 91.5 99.0 6.8

TABLE IV Rupture Test Results at 600~, 800~ and 1000~F for Ti 150A Test Stress Time Elongation Reduction Minimum 100-Hour Estimated Treatment Temp of Area Creep Rate Rupture Strength Elongation (~F) (psi) (hrs) (% in 1 in. ) () (in/in/hr) (psi) (%) As Received 600 90,600 0. 1 30.4 60. - 89,000 5 min 30.6 60. 0. 85,000 not yet available 80,000 >979.3 5.7* — 2.0x 10-5 85,000** 35 800 69,900 0.1 36.2 75.5 - 50,000 5.5 44 2 76.6 - 38,000 142.7 *** *** 1.1 x 10'4 39,000 50 1000 37,800 0.1 93.0 98.0 - -. 20,000 3.2' 65, 3 87.8 LC 12,000 150.2 55.3 92.6 5.4 x 104 12,500 55 1500~F An- 600 85,300 0.1 29.5 61.0 nealed 80,000 >791.6 11.6* -- 2.0 x 10-5 82,000 35 800 68,300 0.1 41.7 74.3 -. 45,000 94.6 53.4 78.4 2.5 x 10-3 42,000 118.1 44.8 76.0 *** 43,000 50 1000 37,400 0.1 68.0 93.5 - 14,000 24.7 87.0 88.4 8.0 x 10'3 11,000 116.0 82.0 92.0 1.4 x 103 11,500 85 1500~F + Air 600 115,000 0.1 19.6 70.4 - Cool 110,000 not completed 1.1 x 104 800 96,100 0.1 36.5 80.9 - - 60,000 31.8 30.0 70.0 8.3x10-4 - 52,000 100.5 48.0 81.0 1.4 x 10' 52,000 48 1000 46,000 0.1 91.5 97.0 - 16,000 16.1 90.0 92.0 LC 11,000 188.8 42.7 92.0 4.0 x10'4 12,000 50 1500~F + 600 162,300 0. 1 4.8 11.6 - _ Water Quench 155,000 125.4 *** *** *** 154,000 --

TABLE IV, Continued Test Stress Time Elongation Reduction Minimum 100-Hour Estimated Treatment Temp of Area Creep Rate Rupture Strength Elongation _____________ (~F) (psi) (hrs) (%0 in 1 in. ) (%) (in/in/hr) (psi) (%) 1500~F + 800 138,700 0.1 36.9 76,9 Water Quench 85, 000 2. 3 37. 0 75. 5 - 48, 000 659.2 7.4 x 10- 60,000 40 1000 46,.700 0.1 99.2 98.0 - P 16,000 7t1 67.0 94,.0 LC 9,000 348, 8 60.0 95.0 3. 3x10-4 11,000 65 1350~F An- 600 87,000 0.1 28,4 56.0 Onealed 84,000 4;,7 28.0 58,4 - -6 82,000 >979. - - 3. 3x10 83,500 30 800 70,200 0.1 41.1 76,5 - 44,000 -84.0 40,2 77.4 1,.6x106 -` 40,000 166,4 42.5 76.4 8.0 x10'4 43,000 40 1000 39,500 0.1 105.6 84.0 14,000 34.0 59.5 92.0 6.2 x 10-4 12,000 157t4 62.0 96.0 13,500 60 1350~F + Air 600 107,000 0.1 16,4 54.3 Cooled 102,000 not yet complete 800 88,500 0. 1 40.4 77. 0 55,000 43.6 42.0 76.5 * -50,000 101.6 52.0 79.4 1,5x10O 50,000 52 1000 41,700 0.1 115.4 98,0 -- - 14,000 33.6 57.2 71.8 4,7x10.3 -- 11,000 194.3 55.0 95.0 4.6x10-4 12,500 55 1350~F+ 600 119,000 0.1 12,9 47,0 Water Quench 114,000 368.8 7.6 1.6 * 115,000 10 800 106,200 0.1 34.3 69. 2 65,000 26.4 41.0 66.5 LC 55,000 61.8 39.2 77.0 2.0x103' 54,000 40 1000 41,500 0.1 98.0 98.0 15,000 16.7t2. 5 69.2 89.4 LC 10~000 160.6 44.4 90.6 1.4x10 10,500 45

TABLE IV, Concluded Test Stress Time Elongation Reduction Minimum 100-Hour Estimated Treatment Temp of Area Creep Rate Rupture Strength Elongation ____________ (~F) (psi) (hrs) (% in 1 in.) (%) (in/in/hr) (psi) (%) 1500~F Water 1000 39,500 0,.1 123.0 98.4 Quench + 1350 F 13,000 43.0 71.5 96.0 -** Anneal 10,500 247.7 172.0 94.0 4.6x10'4 11,500 120 1350~F Water 800 98, 000 0. 1 31.8 76.0 Quench + 900~F 58,000 37 + 5 37.4 76.0 -- Anneal 51,000 107.5 30.8 77.0 51,000 30 1000 43,000 0.1 91.5 99.0 14,000 48.9 57.5 93.5 LC 11,500 127.0 67.0 96.5 12,500 65 1800~F 600 113,600 0.1 15.0 35.5 Isoth, 1 hr 110,000 37.6 6.8 8.6 6* 13000F + Water 108,000 not yet complete *** Quench 800 92,700 0.1 26.0 33.3 55,000 55 4 42,0 78.0 * 45,000 320.4 26.4 76.0 2.9 x l0-4 52,000 35 1000 48,500 0.1 110.7 99.0 17,500 16.0 51.5 91.0 LC - 11,000 582.0 45.5 93.0 8.3x10 14,000 50 1800~F 800 98,900 0.1 20.8 65. 6 Isoth. 1 hr 60,000 8.4 30.4 73. 7 1000~F + Water 55,000 95.1 30.5 80.6 6* Quench 45,000 >790.0 1.9*- 1. 8x10-5 55,000 30 1000 59,100 0.1 79.3 99.0 20,000 7. 5 t2.5 36.0 93.5 LC 11,000 203.7 47.0 93,.5 5.7x10-4 12,000 45 s* Permanent deformation after cooling. s** Approximately.' Not yet available. LC Loading Curve only.

TABLE V Available Creep Data at 600~, 800~ and 1000~F for Ti 150A Test Stress Minimum Test Est. Stress for Treatment Temp Creep Rate Time Rate of 5 x 10(~F) (psi) (in/in/hr) (hrs) in/in/hr As Received 600 80,000 2.0 x 10'5 979.3 50,000 800 38,000 1.1 x 10-4 142.7 29,000 1000 12,000 5,4 x 10' 150.2 6,000 1.1 x 105 768.6 5,000 1500~F Anneal 600 80,000 2.0 x 10 791.6 * 800 45,000 2.5 x 10"3 94.6 29,000 1000 14,000 8.0 x 10-3 24.7 11,000 1.4 x 10"3 116.0 5,000 4. 8x 106 860.4 5,000 1500~F Air 600 110,000.1 x 10-4 * * Cooled 800 80,000 8.3 x 10- 31.8 52,000 1.4 x 10'3 100.5 35,000 1000 11,000 4.0 x 10-4 188.8 5,000 1500~F Water 800 48,000 74 x 10' 659 2 41,000 Quenched 1000 9,000 3 3 x 10 348.8 5,000 1 5 x 105 350 * 5,000 1350~F Anneal 600 82,000 3.3 x 10 6 979.1 * 800 44,000 1.6 x 10-3 84.0 40,000 8.0 x 10-4 166.4 29,000 1000 14,000 6.2 x 10-4 34.0 5,000 1350~F Air 800 50, 000 1.5 x 103 101.6 35, 000 Cooled 1000 14,000 4.7 x 10-3 33 6 11,000 4.6 x 10'4 194.3 5,000 1350~F Water 800 55, 000 2,0 x 10-3 61.8 41,000 Quenched 1000 10,000 1.4 x 10-3 160,6 5,000 1500~F Water 1000 10,500 4. 6 x 10-4 247.7 5, 000 Quench + 1350~F Anneal 1800~F Isoth. 1 800 45,000 29 x 10 4 320.4 35,000 hr 1300~F + 1000 11,000 8.3 x 10 582.0 5,000 Water Quench 1800~F Isoth. 800 45,000 18 x 10-5 790.0 41,000 1 hr 1000~F + 1000 11,000 6.7 x 10-4 203.7 5,000 Water Quench * Not yet complete.

TABLE VI Rupture - Test Results at 6000, 8000 and 1000F for Experimental 6% Al Alpha Alloy Test Stress Time Elongation Reduction Minimum 100-Hour Properties Treatment Temp of Area Creep Rate Rupture Strength Est, Elongation ____________ (~F) (psi) (hrs) (% in 1 in.) (%) (in/in/hr) (psi) (%) 2025~F Water 600 97,900 0.1 17.6 34.1 Quench 96,000 >1443,9 (overheated) 96,500 18 1000 80,300 0,1 14.9 33.8 35,000 361.0 30.6 34.2 2.3 x 10-4 40,000 25 10% Cold Work 600 97,800 0.1 9.6 45.8 - 96,500 >1216.0 1.0* -- not yet available 95,000 259.8 4.9 22.4 3.8x10" 96,00 7 1000 83,300 0.1 18.,6 38,1 40, 000 20.5 43.2 68.6 LC -- 26,800 176.4 53.5 87,.6 1.0x10-3 30,000 45 17% Cold Work 600 105,100 0.1 10.0 34.7 103,500 0.1 12.9 52.8 101.000 >1172.2 1.0* - 3.3x0-5 102,000 15 1000 83,400 0.1 14.6 32.8 37,000 13.4 19. 0 32,.8 9,9x103 -- 26, 000 123.6 56.0 83.0 1.5x 0-3 27,000 50 * Permanent deformation on cooling. > Greater than, test discontinued without rupture, NOTE: Tensile test used as 0. 1-hour rupture stress.

TABLE VII Creep Data at 600~ and 1000~F For Experimental 6%o Al Alpha Alloy Treatment Test Stress Minimum Test Estimated StrFess Temp Creep Rate Time for 5 x 10 _ (F) (psi) (in/in/hr) (hrs) in/in/hr 2025~F Water 600 96,000 data erratic 1443. 9 Quench 1000 35, 000 2.3 x 10 361.0 -- 20,000 3.8 x 105 * 5,000 - 10,000 10% Cold Work 600 95,000 3.8 x 106 259.8 -- 96,500 * *1216.0 95,000 1000 26,800 1.0 x 10-3 176.4 5,000 - 10,000 17% Cold Work 600 101,000 3.3 x 105 1172.2 80,000 1000 37,000 9.9 x 103 13.4 26,000 1.5 x 103 123.6 5,000 * Not complete.

TABLE VIII Tensile Results at 750, 6000 and 10000F for Experimental 30 Per Cent Mo Stable Beta Alloy Treatment Test Ultimate Yield Elongation Reduction Elastic Temp Strength Strength of Area Modulus ___________ (OF) (psi) (0.2% Offset) (% in 1 in.) (%) (x 10-6 psi) As Forged 75 144,700 142,500 14.0 27.4 13.6 1325~F 1 hr + 75 145,800 142,200 12.6 28,.0 14.6 Water Quenched 1000 82,500 74,400 22.1 40.5 13.0 1500~F 2 hr + 75 144,400 142,400 12.2 21.6 13.1 Water Quenched 600 106,000 95,600 19.4 47.5 11.7 1000 83,200 73,700 21.3 62.0 12.0 1500~F 2 hr + 75 140,500 136,600 11.6 22.6 14.0 Water Quench + 1375~F 24 hr + Water Quench

TABLE IX Rupture Data at 6000 and 1000~F for Experimental 30 Per Cent Mo Stable Beta Alloy Test Stress Time Elongation Reduction Minimum 100-Hour Rupture Properties Treatment Temp of Area Creep Rate Rupture Strength Est. Elong (~F) (psi) (hrs) (% in 1 in.) (%) (in/in/hr) (psi) (%) As Forged 600 90,000 >1158.0 (overheated -- too damaged) * 41000 40,000 77+2 54.8 49.4 8.8 x 10 35,000 133:0 62.8 70.0 2.0 x 10 37,500 60 1325~F 1 hr + 600 105,400 0.1 15.8 43.4 -- Water Quench 100,000 >836.0 -- -- 90,000 >1485.0 -- - -- 102,000 15 1000 82,500 0. 1 22. 1 40.5 40,000 74.5 54.4 37.9 LC 1 __ 35,000 141.2 54.3 75.4 4.3x10-4 -- 22,000 1143.9 84.0 82.1 2.5 x 10-5 37,500 55 1500~F 2 hr + 1000 37,500 83.4 66.6 71.2 LC 37,000 Water Quench * Not yet available. LC Loading curve only.

TABLE X Creep Data at 600~ and 1000~F for Experimental 30 Per Cent Mo Stable Beta Alloy Test Stress Minimum Test Est. Stres Treatment Temp Creep Rate Time for 5 x 10__________ (~F) (psi) (in/in/hr) (hrs) in/in/hr -4 As Forged 1000 40,000 8.8 x 104 772 -- 35,000 2.0x10-4 133.0 20,000 4.6 x 10 —5 912.5 10,000 1325~F 1 hr + 600 90,000 < 10'8 1485.0? Water Quench 1000 35,000 4.3 x 10-4 141.2 - 22,000 2.5x10'5 1143.9 10,000

TABLE XI Result of X-Ray Diffraction Traverse of Ti 150A Treatment and Test Details a Lines p Lines As Received - 979 hr -80,000 psi - 600~F 11 5 As Received - 150 hr - 12,000 psi - 1000~F 14 1 1500~F Air Cooled * 1000~F Tensile Test 10 3 15000F Air Cooled - 16 hr - 16,000 psi - 1000~F 8 1 1500~F Water Quench - 1000~F Tensile Test 11 5 1500~F Water Quench - 7 hr - 16,000 psi - 1000~F 11 3 1500~F Water Quench - 157 hr - 12,000 psi - 1000~F 11 4 1350~F Air Cooled - 33 hr - 14,000 psi - 1000~F 12 3 1350~F Water Quench - 26 hr - 65,000 psi - 800~F 4 0 1350~F Water Quench - 160 hr - 10,000 psi - 1000~F 10 4 1350~F Annealed - 84 hr - 44,000 psi - 800~F 7 1 1300~F Isothermal - 800~F Tensile Test 12 3 1000~F Isothermal - 8 hr - 60,000 psi - 800~F 10 0 1000~F Isothermal - 10 hr - 20,000 psi -10000~F 12 0 NOTE: All heat treatment times 1 hour. Isothermal Treatments: 1 hr 1800~F -* 1 hr at temp (leadpot) - Water Quench.

TABLE XII Alloy Comparison Property Temp Ti 75A Ti 150A 6% Al 30% Mo 100-Hour 600~F 31,000-55,000 82,000-154,000 96,000-102,000 102,000 Rupture 800~F 17,000-20,000 39,000- 60,000 Strength 1000~F 4,400- 6,200 11,500- 12,500 27,000- 40,000 37,500 Estimated 600"F 25,000-50,000 50, 000? 80,000- 95,000 >90,000 Stress for 800~F 5,000-10,000 29,000- 41,000 Minimum 1000~F 1,500- 3,500 5,000 5,000- 10,000 10,000 Creep Rate of 5 x 10 in/in/hr

A~O03 * _ ___ _. _.~. r —-<-t %: ~.... 4 O9 |__ - 0 0 —-_ - - <-0 t r 3r.i,,l j_ - i..!, _ i;... wow.. ~8.. i: b i ~ I I t i,,.,, t 0 R t O, j1 ( ea:::', ~* *: i j,'b':; e*1.r. 80, 00j S4 —-7 --— H- *-4 i a j I t |! i: E e:: 0. i i F r: 0 |'_+j s I:': i t. r. t.. * i 4io, tooo -- E: ^ -i-4 ^H ~*'4~-'A.is s e- e x — 4 t- " | -4-a*-{- A —.-^4-m-.4_i-M^^^^^ ^..-^ _.::>-.,,oo --. I A-et-d on:AneeC. Ni - tse 4 a I i+ i.

4~~ Q W _- _-w J4-44 ~r W~ t~ - -i-^ ^, _..-^^^,~4^ "44 —"^ - ^444lin 0~ ~ ~ 0w 40W P ~ ~ ^ ~ ~ r- ~ t | __ _ ~ ~ ~ ~ ~ ~ *...* I..... ^^ *: ^! L ~j ^ ^? ^'- _~_ ^- j _ I ^ f T~lpo i............. _....-4-L ~.-L —_J,._ iL.L —.'' i... — i,..'.. I00 000,0j —s f —f —~ - ~ -00 —-^4 <^^.^^ I t- *'5'''~''Sj~ —-, _____r^ _:4-^ _^4 —^ —---— 4^ —— J^^^^J! 1! i I5 - * x It j *i j < r & i ^ *! l j 5 t * 5/!*; 1'...'...! t i j t " I' I.. 60,'* Q *:000. 0i. _ i. 1400.000R' —- * —' -f-,~~~~~~~~~~~~~~~~~~~~~~,7 i -';'.: ~~~~~~~~~~~ l+t t ~~' 5~~~~ i6 ~ ~ -- -:- - r..........,'<~- t _ +, p ZOooo.. ~ t-+- - - "_ *S sr _ T i i + i; f i #S#|;!4& i l. Tt f fi ^ ^ 5 f7 I. I j i eF f; ei t f;.~.. i I-! i i i i i ~t'iF I 0j 000 f-_** f OOO' 1-T *': 1 P { 000.: 4 o 0 0 0@-j-+Xt+t=_5 __ -'' —' ~ Time -'ho rs, Q00 -4+ —; > tf_,~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~0 |z-s. F.'': ~ D'F i: -' S'.~:<.f~ rsu~~~~~~s iqe'i'3.me Figure - Stress es ie at S600C' 8V30' ad 1000O for RJiture and time To ac- S. ecified. TTotal Deforation for T'7i 75A Arnnealed at 1500 #'or 17 O~.F

F- o o-o -I-; —,,Y 4444-i-4_i44 — -s"M^ —-4 —4444-4-,: i * tFs ~ -I { t' i i' ~' i r * *.; t' ~ N O4e: Fi f lrure i r 4 00 ---- - _. to4o - -. T, _,- t i.'., t >. i s $ *~t j; s i ~~;' It M,- s l i -.-f s n _ t _~~~~ U r - - *~~~~~ m t a'-e -+';-S'i6 * e s~~~~~~~~~~ — _:;!;1'-''-' —T Y —-4 —_::' fi t* t 5 i I.; s' j. i 11 * k *> * *: f! i 1,; * i; i i!!,' F M t \ 400 000 ^.- -- --.I: its~~~~~~~~~~~~~~ I-I ~. —^ii+ — --— I,-+-'p- -t^ —,^ —-~ —1nTTTt1 ~~~~~~~~~~~~~....,. i_^_ —------—: —------------ J4 2ire000 —- o --- — t ----- t; tt~ -— |-^^^^ ---- - +-+4-4 —-_-^ —-,'.-!t; - b 5 -- e.i^;! S 1 i S * <. 400 000e f 1; 4 v = ~~~~~~~~~T ni - hour ~'; t 0 or, Ti75A. A aleat *500~ or i 7 0. F a Cold W ~ ~ [1'54L &V) 000 Io axoo ot 2, + ~00 T = -—.4 —~. —:d~'jf00- -A A ur'.rsu fT iirlft 3 ie a, t 6o 0 rf r r'.uFt jf;tf f e c h p ti f i, e T' o, -t t~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~~~~~~~~~~... F~~~~~A 5Lg A Ainrot c~ r ssTIre da 6O.' F arl,^ff' 3C &.- Xf ui W Fc) r" u-ue ad to R.efr bleCitlfd9>a eOr<rai:::: X for T4 nRA Ah~eated at 1 5005 o, r1700w>Fand Co1#S Wo~rked 10* 9:%

4 00, 00~|- -j I - - -.|-44' -I- -"t - - - -- — i —-- -H — ~?t-~~ -- -- ~ — - -- 4,0 ~oj T —— 74 -.-;t —-- tu —-0 —1m4 s-4 4 *r at ni tu ji1 * t - ___ - lo~oo — -- - -_ G ^.- — 4-! —, —t ___ ~^ j ~h~+-^5 i t1*' zoo0 000- -41 -S — >0-H -I 20. ooo — ^^^ifi^-.-l44. —^,, ~ _.... 4a~~ / e __ —B +_-Jl H —----- — h-0Boiof^~~~~~~~ oo^ i L~~^i.'-^^-t-^-~~~~1,^ 1-,_: IO0 000?4 4_ 600 = Qopture' 60__ _ -,0~ *s 000 - 20, G00 rar I, 0'.!0O -7,~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~:Z~~~~~~~~~~~~~Tm - hor 40, 000 — ~.~.~.~ T'~.,:::;A Amr'~eaied at i ~:~0O or!7"~fi F and Cold Worked 3 t'f~0^2ro~ ~ ~ ~ ~ ~ ~ ~ ~~~~~~~Tm fo ur s -~$ 4 f. f f ft~~-S Vesu T ~_4 and_ 100' *-f Rutuirh 7*ef a-i Tim ~ to ie-h SP i I r~ ~ ~ fr-.nto'I Af An ne a-~ t I - )-r 00E n odW re

* pa opo s-i pa4JoIs peoD VLT-V 5%9 pu-e,t00t t ro o005 ~.: PaTpau-w) v L U V L oj t 3eoOT PUB. 838~'o009. t-Sud.Sg o r',ndnt;jnoq-0o01 sn s A > O~A Pld 0o ao0 ga - "5 - Xfn. O PI0...o, %. *0 000 009:,.,.... - _',' 0 ~' 0g 0 1 0.t~: \ IS I P —, —--'.I 4;? 0 H1~~~~~~~~, t - --- 1 -.V.. -00 --,- ~ 1 -.t~o0'0.9-o —-- T X I t. *.. * * ~ ~'L f *m~;..' *' * *.. ^ *~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ *~ ~ ~ ~ ~ ~% q *!'..*.. *.! "''..! 0~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ * * * * *' *'!''^,.,!! ^~~~~~~......................................,!saaBass^ssssia^i.................................. 0

'VOSI T.1 Pu VU-'5 o'J'- - lu.o) p': ~nszA;znseac: Za T9,- 5'9 znT..' 000 T 008 0' ~0 0 O 007 0 _____ _____ _____ -____ — _-__ -______ j.0TC VGL TI. ^.:O-. \:, ____.. _. -.-. * —--: 08 "' ____. *, -0T. o.. r... -------------- ^^_ -----------— __ ___.____~ ---- 09 I i~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~

60. ------ - - - _ —---- -- _ ~ —--- - -^ ^ ---- -__ 1 In general, second ztage ates for a11 ^ _ _______ _______.-~ ___,_ _ __ —,', 600 0FT; tests/not rupturirig:n withiL 10 I* t..," * *.''hours iw Ie approxirate1yt vzero i. e., fir st Stage,.but then vezry-little p c e ___3_5______ —___-_________ —-i__________ _________________ I ~ ~ ____ ^ __. _ _ _ _ ~ ~ 35 5 C) ~~0, A R'< 10~~~~~ 0 C A~~~~~r~~. jja?igurc17, tr s rs wsMnmmC~Rt t&~~a1 00FLrT 3 h c sIdtd Fiur 7. Stes Ve s. Miim *. -: at ea 800 I "00 Tfor.' Ti 75 T e - a t' ec s* di *

" 1 0I oI. 1 I'' * i *' I * r I' ~v. I I i j~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ I t S \r.^^.^N.' \ *: * r ~~~~~ ~ ~ 0Bar Stock u j 2. tv ^ *. N *j~ ** *. Stri St ck -o.,'.**-'i7A->.^' __________ _____________ |, 4-i. ~~~~J"~~~~~~ i 75 ^O^1111111111111111111111''1'' 1W O —'^^ ^ -- - ^ ^^^ ma — ^ ___ ___ ____ _00_Soo I ____ _ __10 1 -00 * *, 1'! Test c'Temlnpe rature ^.'F''*...',!.*.! Figr S. Test -T emnp erature V,,rs us S r s,; Ifo MiniJmumi i., Creep Rate ofI 3 x: iO a /in. /rfrT 6 arw Ti 15A.. P Poits for Strip Sto aie, und ontract A 3( 38)-141 ~~~~E~~~~~ll~~~~~~~i O~~~~pO

., - - 4- - --- - * 000 h I!: i t z - - - __ _ -;. - i - *.tI- 1- - -., 20 000 4 -—' — 0 As Receiv ed, -4 - 1500 Anneat, I x 1.500 Air Cool i I 0,-4000 _. 16500;.Water Quench.-.- _ ~0~' Ft 3 50'Air Cool ed., -, 0o01.35. 0 Water.Q4uench _ —^-,-t —.T-t O' i350. i t O0......... 4. Time - hours 4'igre 9.- Stress Versus.Ti:e to Rp"r.... at 800~t and'000 for "i.50A Heat ated aC ndi T 4 a I nd g iCt e',t, - Stress -sut t.m tP 4tu. e a. T t 80 an 7O, P 0 A.a ae. a I wat4:d.

150 0 l W.Q. ~ 1500) A.C W.Q.! 1'50 We Qo |''Jj. - -i 300 Iso 100-Ruhour Rupture Strengths 350;A.G Ti 150A A At 600~F Ann. 84 000 I: I T| | f d *Iso.!, A. X 2 - ~~I|~~~~,~~|~~~~~~~~~~~ s 0o. t- S I At000 All 12, oo I L, | *,-* o l ^ g l | f * (. i 5 I _ + W Qtt. t /o,!...' i ~At I0800 O 12,5 0F0 7. *|,- 2 <; ^'-'. ^ ^c* Figure 10. -On Huudred-]Hour Rupture Strenth at 6'00`, a and i000F fo Ti 15A Heat Tr ated One 2H 1u —- - inAc- -as In tc.- i - a --- e- -,- _._ clO_._ I i',~' — 1 =C> 0." *,. *.....as Ind i c ate ~~8~Lhta-~'~-);~,.<~ (:"~ ii'I~~~~~~~~~~~~~~~~~~e~',~ orf~~4iIr ii I i I I I I ~~~~~ I I I I I I i I I I I I. I I I I I I ~~~~~~~~~~ I $osoJ~J ~ 80"F loQ~d rigilre~~~~~~~~~~~~~~ odd g <.;nde-Hu RY~i ~caha 0",8O n 00FirTi10 etT~ae I~~~$Tr~ sfniaei

-PJ-3e-UI 6rT pUja">$e as'-3 YO T Su XO V$>uJS u z4'p;p9 -.ipu si2 ^u~iu~a~jO I H VOs I T-L Jo 7Sn -1 cl -dan jnoq-oO p0 e 110 2 at-T"u g [s- sanssa Y a n^ >ediuj K saL -'rI'anj' o - duai a;0001 00: 8 009 00Z O0. 0 —!^ - ----— __ oz ~tL. x aii9.<x3S ajn adn j.noH 001'~ ~' I J'. t- _L m _ - -'II''l \\'\l~~~ 1 fI \ \ "\ I I3a s11 98 ]\\ \____________ \ ____________-0 01_ -^ m m I- \ v \OIl \ X l l \0 9. * 0,'O S \' ~ ---. ----------------- ^; ------ - ------. —------- 091 k>^ -- i- -- -^- M ii u -- - -- -- ~ - --- - ~ii O — i OM 111111 mo i~~i~~~\...

60 L5 ~l- -;.- - L- I --— I — 1 rl I I I I:1: I XTE W _ _0 -_ 1 _ _-1 ITV i - - 40 35 3020 10 3 5 W 5E - 1; E rsu M0 a 0 aA a a Cree? Rate - irn. /ir. / ate Fig ur 1.. - S. t.ess V ersuts M i irur: C -ee. Rate ar 800' aid 0' f eat e a* *li;d

90**0! t |_! _ 4, * i i [ * t *: \ * *. __:_ | | 80 75 -- -- 70 >,65' 60 of As Rec eived I *'1.* "' *Strip Speciraexi'S 4 5 1 8 g, 5; I jI -: - o x B As RR e.a:e -v?Ce. RaJe - ^iri,. 1 rz * I. - A 50 n C a a 0 a T.. 301 -o z0-4 10-3 * O-2 Creep Rat e - i:n. /in. / hr.'Figure 13. St-es s Vesu Mini-"ur.. Creep Rate at 600~ and 800~ for Ti 50A Treated as IndicateTd. Jg... T, SI us: t ed ~ i

__ _ 4E _~~~~-~r-C- T - S 400 00i_ __.. _ t.__~t_..~ ~ ~ ~' ~ ~!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~r~.'"~""""'^'"' x bU ~i~ C~~ 1; _ -; -. "- _ m t i: t 0! e 3 r i t t i t _ =" i i:~~~5 ~ - i! 8gto r 7 got f 00 4oTT01 1 I 3 z~ a F Ot> i e rit l ~ ~~~~~~ —— ~ —B _ _, +.^. t _ t It: 1oo?F} t,, _ i a~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~i 20a,.0..'~'.;- 0Z02 5'F Water uench A C old ork F~~i,:>vte -:LZS~r~ss erss'i-Oua~ Q~~ AT.-aiasIlcai L -i~~~~~~~~~~~,0(~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ 6~~~~~~~~~ 0t 1 ~ ~ ~ ~,i' r;' " r: I j 4 ~ ~ ~ ~ r oooji rr i C 4,0001 ~S a: r: i: ~1 g! -~~~~~~~~~~~~~~~ ~-7-4 —7 2,00o 0 I00~~~ ~ ~~~ ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~,, I' I ii; i ~ ~~~ ~ ~~~ I i' I' 5:~~;' r F; 0 3 4 r ri TimeI - ho u.r s FigiteieRe!'A.-Ti Treated s dca IgStes e su 1 l-n, 00' - b/6 F Ur e S;~~~~~~~f

120 ---- - -- - - - ----- — ___ —--- — __ - ----- - - - - I 10 ho 1'C.... 600 F 90 80 -- rct~~~~~~~~~~~~~~~~~~~~~~~ 60i~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ 0 2 F T W at e ir Quench A JeCold W ork ri 3 0 —------- -— )- - - - --------- -— __ _ _ 1 —-------- -- - _ _ - -. ---------- -- -_1004h 3 0'..'.................. MO ~ ~ ~ ~ O~ 107-5 3~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~5 ~30~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ f'__________. __ ____ I -*!. i.' ~~~~~~LiLL~~~~~~~~~~~~~~LL reep Rate - in, n, */hr 0 Fig 1, S Stro e t1C__r3u Creep Rate at 600 a 0 F fo 6% A T Treated as I dicated

its!~~~~~~~~~ -v —'4 *1 _ _ -r-t ~~~~. I -:. r -a-' " "v,-4 j I ~ h ~ —4 —-, —7 ~ ~ ~~._ I I 1 4 4, ~~~~~~~~~~~~~~~ -- -. -. —,..- -—:.- -~: I: t f F Rt.....!-` 4 -rr5 I- -— 4 4-, 2.00 0i i j 0 "' i c~~~~ -IhT. 1 P a i g i a. r i. a E g r a o.~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~..... 40, 00Ot 42-..A- ~~~I,~ ~ ~~~~~ I e s. ~: i i ~ ~~~~~~~~~~~~i! i- ~:r 1.1'~~~ - I i - I I III "1- - -,,,. I' " 8,00O4~~~~~~~~~~~ 14'"-> "' i 1 iI I-~-, 000,00 ~~~~~~~ " ~~~~~~~~~~~~~~~~ t 60 000 - 0'r ecl —''t 4.000~~4 i I,K at Time - - ir t 00 1.F. -.~t~z2 V to R 3 a O aa T i rn e hours!'f h1fMo.T T r ooo I'D SV e R a Stt us t...f 1,I,. F itgz- u i l.. F, J a i "~~~~~~~~~~~~~.b%~~~~~~~Q 4 pr,%.kt~t::', j " "j:i-'.t,, n i~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ -; t -i i~ ~ ri 80oQ08~~~ ~ ~~~~~~~~~~~~ i m e - h u Fiuie1 trs eru Tiz~z oR~'~~~''ea 30 ad10~ fr3%!4-Ti.rada ndctd

. _0 —— _ —__?- ---,-i__-i_ I1 0F. - - - -. —--- - - _.......-.... 60r 350 -1- -Ii rt''1' t fl R k N 1 i | R 1 rF i _ 71 A sFo!"d 0 _154 —- ----— __ —.....,:Cree3 Rate in..:. i3 Eh Figr. --. r "S V IrU Min u C ee Rate at 1 t0F o Mo *T..!T Treat-d as lI a: r: ". ~ i: /h.Figure 17, -'Stress Ve.rs-us M'~Minimu_- Creep Rate at. 1000~F fo:r 30? MoTi Treated as Ind7icafed.

-ij^1 y o q1' ua 3rg jn2dn rnoq-o 0g T sns' e a js n -eadu?9j- e.js, I -'8T a^.nesl O.,- 07:...:~n - d t n l rn qEd, COO.I O S *008::' &09'.. O0 0'' 0 1 -; I 09 C, 0 Q I VOS T;.. OI -Ot E \ r vsz rII I T I I L \.ffi T<1 0 6rI: l I t q t,. -, —. " i s^ siBssaa~~s~sR, - l &!, 0 |''*>'~s*"';Eff:2 ta; \ w t;tv< stsx erfa;$Exs'sSt.-sS5t:At,,S~~,,1,,,,>,S'A

p;D'p ti S PI S O [T vaXI ituJ. e j 0;' t/ T/:t t /T IT I _ O T X- JQ~:-' D':8g''1j3: n.4Xtx oj j SSA'n~ a 1radu Tdu8s - n61 T I- n24 - \: a ~ -0 a*'~a^ J* n* l ad Eu a 0:. I _000.;.1 ars0 -. o -0 - oo z vosi -I^;^^ \ -— V - - _<_ -~ 0 0% X _____ ____,,___,_____,_,___._____ 09 O QT --- r - - -- - SmSSSStSW tS~S'iSSSSS S~fgS??!*gSSiEBS3B* ~<aPSK y ^^ii%~iX%..~ iS~a~aE^Sa~?R3^~~^S^^**isy's'*'3::iKflwsstf'**'lS^~'***:e

+ As Received x 1500~F Anneal a 1700~F Anneal _ 1500~F Anneal + 10.9% Cold Work 0&F *~ 1500~F Anneal + 31.3% Cold Work - - -- a 1700~F Anneal + 10.9% Cold Work A 1700~F Anneal + 31. 3% Cold Work 31.3% CW 50. ---- -- - - - - -- --- --- --- - - - _ -_ - 1 X —- — 4- 600~F - l IIII 10.9%OCW;<240 _ I I I-'I1- -t -- — t -____ _ *|' <-+ <10-8'C'ig. 9. <_tres, Vs-.__ Minimun_____ — -._______ ____ ____ _ Creep Rate at 600~, 800o and 100I F for Various Conditions 313% 1CW of Ti 75A 1. W \O II ] —'^ ^r ~109% OW zo _! a I I I _ I0_ ] * | |-l — - - -_!:: —:i 7 -~ 1 - =II I I [I I 1!..... 0- Z 3 4 5 7 10- 2 3 4 5 7 10-5 2 3 5 3 4 5 72 1-4 2 3 4 5 7 10-3 Minimumr Creep Rate - in/in/hr

Figure 20 X250 Figure 21 X250 Tl 7SA 1700hF An Ti 7A 1700 F Annealed nealed + Z8 hr. 1000Y~F and 6,500 psi....................... F 0Figure 23 X10 80, 000 psi 1 2,0 0 psi.: Figure 24 X1000 Figure 25 X1000 Ti 15OA As$0 0F ilv Ti 5A 1 500ReF Ae n~aled TensileTested nealed + 1i6hr. 10 00F at78000F 3hr~ 6000F anc~-'l +and 1,0 00 ps10i;0 0: IEtchant: Ti ISA 2 HF, 2 HNO3 100 H2I \iur 24v- X' I*;' 000 Figure 25 10

Cooled. Tensile Tested Cooled+ 100.5 hr. 800~ F at 800~F and 52 000 psi Figure 28 X100 000 Figur 29 X!000 Ti 150A 150500F Air Ti 150A - 1500~F Air Cooled, Tensile Tested Cooled+ 1 hr. 1000F at l8000F and 516,000 psi _.. Figure 30 X i000 Figure 31 X1000 Ti 150A - I00F Air Ti 15OA- 1500~F Water Cooled + T88.8hr, 1000FtQuench + 2. 3 hr. 800 F and 1,000 psi and 85,000 psi All Heat Treat.A ment Time 1 Hour Electropol shed Etlhant: 1 H, 1 Glycerine

Figure 32 X 000 Figure 33 X1000 Ti 150A 1500F Water Ti 150A 15000F Water Q4uen1. Tenile:T Teted Quenched + 348, 8 l r* at 100OF 1000 F and 9, 0001 p i Figure 34 XtIO F igure 35 X1000 Ti 1.OA 5 A 3 50OF An Ti 150A 1350*F An.-: nealed. Tenile Tested nealed 34 hr 1000F and at 800BM - lF XE 14,00 0 p s Ti 150A - 350 Air Ti 150A -: 1350~ Air Cooled 43.5 hr. 800 ~F Cooled +19 3 hr. 1000 F and 55,000 psi d 1.1,000 psi:.; All Heat Treatrment Tines I Hour;.:::': Ele tropolishedcl Eftchant: I HF, I Glyceriie

>2 ~ - I~ E*~- ii ~ ~ ~ iiiir ~~ to _:::::*r,:: _S $2_a r 7 N t I tOh I K ) ~ -r\: oi 0 IF~I:? ii g:: IN v - i~iIieiiHi 0~ f~:~: 0-'I ~:::::,:::: r: s li~l -iC g~I: Ii9,5 _ il-"; #7 77 0.O................................................................... ~'~ t~f 0 b o+b~:::::: xe h +?:: r::::r L_ ii j:::~~~~~~~~~~~~~~~~~~~~~~~~~~9w W r7 ii~~~~~~i YZ - -— h~~~~~~~~~~~~~~~~~s ii~ ~ ~~~1 774 C> M~~~~~~~~~~iiilll C>~ ~ ~ ~ ~ ~ ~ ~ ~~~~~~~~~~~~11w ~

+ 900^ Anneal + 37 hr. Quench. Tensile Tested 800~F and 58,000 psi at 1000~F Figure 46 X50 Figure 47 X250 6% 0:..5t - ZQZyV W.Q. 6%. A1 -Tii -Cold Worked 1443.9 hr. 600. F, 9:6:,000 17% + 1172.2 hr. 6O0 F psi+ ac cidetal overheat and 101, 000 psi r^-I^... t- i':.. [: Figure 48 X25000 Figure 49 X250 6% A1A -1350old Worked 6 ATi 2025Cold Watorked + 17%00 TeF Ale Testedal + 37 h Quench. Tensile Tested000~F 000 F and 58,3700 I at 1000 All Heat TrXeatment Times 1 Hour Electropolished Etchant: Ti 150A - 1 HF, 1 Glycerine 6% Al-Ti - Z HF, 2 HN03, 100 H A0

'..~-. >-v \^x^ ^y.'' ^.' w A''' 6% AlTi- Cold Worked 6% A1Ti Cold Worked 10 o Tensile Tested at 10O:% + IZ~IS h~rs 600~F 600*F a:nd 96, 500 1 psi Figure 50 X250 Figure 51 X250 6Ali Cold Worked 6% Al!Ti Cold Worked 10%. Tensile Tested at 10% + 125 hr 1000 ~F 6000*F and 4096,00 psi Figu retn 54 X H50 All Heat Trea.tment Tim... - Hu: lectropolhed' Etchant: 6% Al-T- Z:HF, Z HNQ3, 98 HzO0 6% Al-Ti - Cold Worked 6% Al-Ti - Cold Worked~~~~~~~~~~~........ 10.TnieTetda-0+2.h.10' All: H wt: T ^eatm^Bt Time a 1 Hour ^ - ^;.......... > lcrpl~e Etchaiit^ 6% A'l- 4 F N3,g-^

X. 4 f a M4 * t' - Figure I5 XZSO Figure 56 X2|| 30% Mo2Ti As Forged + 30% MoTi As Forged 77 hrt 1000SF an~d 40,000l: + 133 h~r 1:000~F and psi 35,0O00 psi...................... Que _nche + 111 836 hr eiQece 4 r Figlurl $7X250 Figure 60 X2|| 3O0o Mo~i ISOO (2z 30% Mo-i 50'4 (:3Zhri.ae.r.u~en~ch~ed.+ I.. e~ri.-Waer Qu~en~ched + 83I 4 1~ ~ ~ ~~0 Mo -T -t~'' 1 HF T1y erine I: ~:1x 1 t 1 1 ~ g,g iiii i,ii!l lii~ ~ i~~~ iiii~~~~ ii~ i~i~ ~~~iiiii~ ii~ iiiiii~iiiiiiiiiiiiiiiiiii~~iiii~iiiiii~ iiiiiiiiiiiii~iiiiiiiiiiiiiigiiiii~iiiii~i~iiiiiiiiiiiiil iii. i^v~i~ iiiiiii~~i~ iiiii~i~ ~iiiiiiiii' iiiiii'~ii'~,.. ~ i "'' ~' ~*~ ~;;;;;;;;;;,;;;::ii:B.. ~0;;;;;;;;;;;;;i iiB~ ~ ii:i~i~ iiiiiix!iiii0i:-i iii;ivi;~i~ iii:i::i;;;;;,;;;i, i':iiiiiiiiiiiiii:!i'1 ~~ i!''~ i!" i,,, i i ~