The Development and Long-Time Structural Stability of a Low Segregation Hf Free Superalloy - DZ125L

Yaoxiao Zhu’, John F. Radavich2, Zhi Zheng’, Xiuzhen Ning’, Langhong Lou’, Xishan Xie’, Changxu Shi4

(1) Institute of Metal Research, Chinese Academy of Sciences, Shenyang 110015 (2) Micro-Met Laboratories, Inc., West Lafayette, IN 47906, USA

(3) University of Science & Technology Beijing, Beijing 100083, China (4) National Natural Science Foundation of China, Beijing 100083, China

Abstract

Solidification studies of cast superalloys carried out at the Institute of Metals Research showed that the trace elements P, Si, B, and Zr had a profound effect on the resultant as-cast structure. These trace elements lowered the liquidus and incipient melting temperatures as well as enhanced solidification segregation.

The control of the P, Si, B, and Zr levels, called low segregation technology, can raise the incipient melting temperature as to provide a higher service temperature of 20- 25°C and reduce the segregation to enhance long-time stability at 900°C.

A new Hf free DS alloy has been developed by the low segregation technology called DZ125L. It shows rupture strengths two to three times longer than the corresponding conventional alloys either at high or medium temperatures in both longitudinal or transverse directions. These properties are attributed to less shrinkage porosity due to a smaller liquidus-solidus gap and lower segregation.

Introduction

At the present time and in the future, superalloys will still be the “workhorse” of materials for jet engines and industrial gas turbine engines. Current studies are underway to raise the service temperature of existing alloys by melt practice, design, or new coatings. However, the melting point limits the temperature of application of superalloys and the addition of large amounts of refractory elements for high temperature strength lowers the melting point and

increases segregation which affects the stability of the alloy during service.

Solidification studies of superalloys have been carried out since the sixties at the Institute of Metal Research. It was found that some trace elements, notably P, Si, B, and Zr, affected the segregation of these elements resulting in lower incipient melting points. A number of new superalloys have been developed based on the principle of trace element control ( l-3). A most recent application of low segregation technology has been in the field. of directionally solidified alloys.

DS superalloy blades were developed in the early sixties to take advantage of no grain boundaries perpendicular to the direction of applied stress, which resulted in higher creep and rupture strengths. However, because of the high refractory element content, the DS blades showed erratic third stage creep, low ductility, and exhibited transverse cracks along the grain boundaries. This detrimental behavior was solved by the addition of l-2% Hf (4,5).

Hf is a rare and expensive element and reacts strongly with oxygen to form HfO either during the melt or remelt cycles. A number of studies have been carried out on the effects of Hf on the microstructure and mechanical properties of a number of superalloys (6,7). The objective of this paper is to describe the results of applying the low segregation technology to the development of a Hf free DS superalloy.

329

Superalloys 2000 Edited by T.M. Pollock, R.D. Kissinger, R.R. Bowman

K.A. Green. M. McLean, S. Olson, and J.J. Schirra ’ ‘l’MS Cite Minerals, Metals &Materials Society), 2000

Alloy Development

To study the effects of trace elements P and Si on the solidification and mechanical properties of a Ni base alloy with high refractory content, a series of alloys were made with varying amounts of P and Si and stress-rupture tested at 760°C and 804 MPa. The results of the tests are given in Table 1.

Based on these results, a low segregation alloy called DZ125L was developed similar in composition to Rene 125 except the Hf and Zr were removed and the B, P, and Si contents were reduced to very low levels as shown in Table 2.

The nominal composition of Rene 125 is shown in Table 2. Although RenC 125 was put in a DS form in order to compare it to a Hf free composition, DZ125L, Rene 125 is a Ni base superalloy developed by GE and is used in equiaxed turbine blades. The development and application of RenC 125 has been described by P. Aldred (8).

The Rene 125 and DZ125L composi- tions were directionally solidified in a conventional DS furnace. Samples of DS RenC 125 and DZ125L alloys were stress- ruptured tested in the longitudinal and transverse directions. The results are given in Table 3.

The results show a much longer life in stress- rupture for the DZ 125L alloy. To understand and explain the reasons for the longer stress rupture life of the DZ 125L alloy compared to that of the DS Rene 125 alloy, a solidification study was carried out on both alloys as well as a long time structural stability program.

Solidification Behavior of DZ125L and DS RenC 125

In the solidification study, a 10 mm cube of each alloy was melted in a graphite boat and heated to 1420°C in a Sic tube furnace and held for 5 minutes to ensure a total molten condition. It was then cooled down slowly to a preset temperature, held for 10 minutes and water quenched. The percent

of liquid and (y+y’) eutectic structure of the solidified material was determined under an optical microscope. Table 4 shows the results of this study.

The data in Table 4 shows that DS RenC 125 begins solidification below 1350°C and (y+y’) precipitates below 1230°C. The alloy is finally solidified at 1100°C. For the DZ125L alloy, the liquidus is 137O”C, the (y+v) eutectic precipitates from 125O”C, and the solidus is at 1230°C from which y ’ precipitates. The difference in the solidus temperatures of the two alloys can range up to 130°C.

The (y+y’) eutectic formation range for the DZ125L is about 30°C while in the DS RenC 125 alloy the eutectic keeps forming until 1100°C. The amount of eutectic measured is 14.5% for the DS RenC 125 alloy to only 5% for the DZ125L alloy.

An electron probe study of the final liquid to freeze in the DS RenC 125 alloy, Table 5 shows the greatest enrichment takes place in the P content followed by Zr, B, and Si. These elements can form low melting point eutectics such as Ni-P and Ni-Zr. Samples that were quenched from 1350°C and 1230°C show the degree of MC formation at 1350°C is more advanced in the DZ125L alloy, Figure la, while a large amount of segregation is still present in the DS Rene 125 alloy at 123O”C, Figure lb.

The nature of the segregation is quite different in the DS Rene 125 at 1290°C as compared to the DZ125L alloy as shown in Figure 2. The segregation area shown for the DS RenC 125 contains small discrete borides and Hf enrichment while the segregation areas in the DZ125L tend to show high Ti liquid giving rise to an MC structure.

Structure Analysis

As-Cast Condition

The as-cast microstructure of the DZ125L alloy consists of two MC phases. The main MC phase is a script form with lessor amounts of a discrete carbide. The MC carbide in the DS Rene 125 is a discrete shaped carbide.

330

Table 1. Effect of P on the stress rupture life (hr). P(wt%) 0.0005 0.0022 0.0034 0.0052 760°C/804MPa 336 218 187 126

Effect of Si on the Stress Rupture Life (hr). Si(wt%) 0.03 0.1 0.2 980°C/235MFa 117 111 59

Table 2. Composition of the Experimental Alloys (wt%)

Alloy C Cr W Al -ri MO Co Ta Hf B Zr P Si Ni

A* 0.11 9 7 4.8 2.5 2 10 3.8 1.8 0.015 0.1 0.005 0.1 Bal

B* 0.11 9 7 4.8 2.5 2 10 3.8 -- 0.008 0.05 0.0005 0.05 Dal

Table 3. Stress Rupture Life of DS RenC 125 and DZ125L Alloys (hr).

Alloy Rupture Strength (hours)

980Z/23SMPa(L)** 760C/804MPa(L)** 760C/725MPa(T)***

I A* I B* 98-135 218-354 62-97

A*= conventional DS Rene’125 B*= low segregation DS Rene’ 125 without Hf. L* *= longitudinal T* * *= transversal

331

Table 4. Solidification of Two Alloys.

Table 5. Enrichment in the Final Residual Liquid in DS Rene’ 125 Alloy.

Element P B zr Hf Si Alloy(wt%) 0.0029 0.019 0.10 1.15 0.21 In final residual OAV1.3 0.60.2 3.815.7 15/21 1.4/3.3 liq.(wt%) Enrichment rate 275148 3 l/63 38157 13/18 6/15

Table 6. Content of M in MC

Element Ti Ta Hf W MO Cr Ni co DZ125L wt% 19.9 56.7 - 15.9 2.6 1.0 3.4 0.6

at% 44.6 33.7 - 9.3 3.0 2.1 6.3 1.0 DS wt% 17.0 62.5 2.1 11.7 1.7 0.7 4.1 0.5

at% 40.1 39.2 1.3 7.2 2.0 1.4 7.0 1n

332

Figure la: MC precipitation at1350°C

Figure lb: Segregation structure at 123OOC

333

I i 10: pm

Figure 2: Segregation areas at 1290°C and 1140°C

334

Both alloys contain eutectic or primary y’ islands but the amount of these island on M23s is much greater in the DS Rene 125 alloy, Figure 3. There appears to be one y’ size in the DS RenC 125 alloy while two sizes of y’ appear in the DZ 125L in a dendrite pattern.

The amount of y’ forming elements are the same in both alloys but the presence of a large amount of primary y islands in the DS RenC 125 ahoy would indicate higher segregation and less possible y’ for strengthening in the DS RenC 125 alloy. The periphery of the primary y islands are known areas where borides and Hf rich carbides form upon high temperature heat treatments.

The chemical analyses of the carbides in both alloys are given in Table 6. High Ti and Ta are present in the carbides in both alloys with minor amounts of Cr, Ni, and Co. However, the carbides in DS Rene 125 also contain Hf and lessor amounts of W+Mo than those in the Hf free DZ125L. Additional micro probe studies show the discrete carbides in the DZ125L alloy are richer in Ti than the script carbides which would indicate a greater tendency to decompose during heat treatments and/or long-time exposures.

Heat Treatment

Both alloys were given the same heat treatment before testing and long-time stability tests at 900°C. The heat treatment consisted of 122O”C/2 hours-A.C. + 108O”C/4 hours A.C. + 9OO”C/16 hours A.C.

The resultant structures are shown in Figure 4a. The DS RenC 125 alloy shows some small precipitation near primary y ’ islands due to the 1220°C temperature, M,,C, at the grain boundaries and a uniform y ’ phase. Near the primary y’ islands there are areas of finer y’ present. The main y precipitation is due to the y’ solutioning at 1220°C and re-precipitation of y’ at 1080°C.

The y’ has not totally solutioned at 1220°C in the DZ125L alloy. The y’ precipitated at the 1080°C temperature is more carboidal in shape than the unsolutioned y’ .

The grain boundaries also show some M,C, precipitates.

900°C Stability

After 1000 hours exposure at 9OO”C, the DS Rene 125 shows more fine pr;2k&;abni~ regigi; of -primary y.

evidence of decomposition and additional M,,C, is seen at the grain boundaries, Figure 4b. An occasional needle or plate is present in random areas.

ln the case of the DZ 125L, the discrete carbides show decomposition resulting in a rosette like formation of M,& More M,,C, is present at the grain boundaries and no plate structure is seen.

After 2000 hours exposure at 9OO”C, there is more discrete M,,C, precipitation in the grain boundaries of each alloy. The y’ phases do not appear to have changed due to the additional 1000 hour exposure as shown in Figure 5a. The most notable change appears to be as large additional formation of the plate phase in the DS Rene 125 and only a few small areas showing plates in DZ 125 L as shown in Figure 5b.

A micro-probe analysis of the plate phase gives in wt.% 39.1W, 15.3M0, 13.4Cr, 16.9Ni, 11.7C0, 1.3A1, 1Ti and 1.4Ta. The composition suggests the Mu phase which by extraction and x-ray analysis confirms the phase to be Mu.

Phase Identification

The inert carbide and other phases present after 2000 hours at 900°C were extracted in a 10% HCl-methanol solution and analyzed by x-ray diffraction.

The x-ray chart for the DZ125L shows only M,&, and an MC whose lattice parameter is 4.36A. The presence of only one M,,C, phase indicates that the grain boundary carbide is M,,C, and the rosette structure due to the discrete breakdown is also M,,C,.

The x-ray pattern of the DS RenC 125 is more complex. Two MC phases are present with lattice parameters of 4.37A and 4.52A, a M,C, phase, and a Mu phase.

335

DS Reng125 (?+“I’) Eutectics 14%

DZ 125L (-y+y’) Eutectics 5%

Figure 3: A-cast (d+f) eutectic structure --

336

- - ̂ .-

Figure 4a: As heat treated structures

Figure 4b: Microstructures after 1000 hrs at 900°C

337

Figure 5a:Microstructures after 2000 hrs at 900°C

Figure 5b: Mu phase precipitation after 2000 hrs at 900°C

i n

338

References Conclusions

1. Y. X. Zhu et al., “Superalloys with Low Segregation,” D. N. Duhl et al., eds., Proceedings of Superallovs 1988, TMS (1988) 703.

A low segregation alloy DZ125L similar in base composition to DS Rent 125 was developed in China. It contains low P, Si, B and no Hf or Zr. Solidification studies show DZ125L to have a much narrower solidification gap compared to DS Rene 125 and has much fewer primary y’ islands (5% vs. 14%). As the Al+Ti in primary y’ islands does not contribute to strengthening, it is felt the higher stress-rupture properties of DZ125L compared to DS ReneC 125 is attributed to more Al+Ti available because of the fewer primary y islands.

As cast DS RenC 125 contains segregation areas on the periphery of many y’ islands. These areas are rich in MO and Hf and they form borides and Hf rich carbides during high temperature processing or heat treatments. In contrast, the areas of segregation found along some primary y ’ islands in the DZ125L. alloy are richer in Ti and revert to TiC during processing.

High segregation areas in alloys with high y’ and refractory elements form plate structures when the solubility of the matrix is exceeded by more alloying or long-time exposures. DS Rene 125 develops appreciable Mu plates after 2000 hours at 900°C while only a small amount of isolated Mu phase is found in DZ125L alloy in the same exposure time. Because the solidification gap in DZ125L is small, the degree of porosity is minimized and columnar growth during solidification is improved. Porosity enhances the tendency for longitudinal cracking and lowers the transverse properties at intermediate temperatures.

2. Y. X. Zhu et al., “A New Way to Improve Superalloys,” S. D. Antolovich et al., eds., Proceedings of Suuerallovs 1992, TMS (1992) 145.

3. Y. X. Zhu et al., “Super-alloys with Low Segregation Controlled by Trace Elements,” An award paper presented at the Conference

Innovations ’ Real Washington, D.C., Jug 21, 1998.

Materials,

4. A. W. Cochardt, “High-Temperature Alloys,” U.S. Patent 3,005,705, October 24, 1961.

5. Martin Metal’s brochure (Ductility Improvement Discovery, MMO04) See also: C.H. Lund, J. Hockin and J.J. Woulds, ‘High Temperature Castable Alloys and Casstings,” U.S. Patent 3,677,747, July 18, 1972.

6. J.M. Dahl, W.F. Danesi and R.G. Dunn, “The Partitioning of Refractory Metal Elements in Hf Modified Cast Nickel Base Superalloys,” Met. Trans. 4, p. 1087, April 1973.

7. J.E. Doherty, B.H. Kear and A.F. Giamei, “On the Origin of the Ductility Enhancement in Hf Doped Mar-M-200,” Journal of Metals, 23, (ll), p. 59, 1971.

8. P. Aldred, “Rene 125 Development and Application,” Paper presented at the National Aerospace engineering Meeting, Culver City, Los Angeles, Nov. 17-20, 1975.

339

Table of Contents-------------------------Next PagePrevious Page-------------------------Next HitPrevious HitSearch ResultsNew Search-------------------------Keynote AddressSuperalloys: The Utility Gas Turbine Perspective

Ingot, Powder and Deformation Processing Characterization of Freckles in a High Strength Wrought Nickel SuperalloySimulation of Intrinsic Inclusion Motion and Dissolution during the Vacuum Arc Remelting of Nickel Based SuperalloysPredicting Grain Size Evolution of UDIMET(r) Alloy 718 during the "Cogging" Process through Use of Numerical AnalysisControl of Grain Size Via Forging Strain Rate Limits for R'88DTSub-Solvus Recrystallization Mechanisms in UDIMET(r) Alloy 720LIThe Mechanical Property Response of Turbine Disks Produced Using Advanced PM Processing TechniquesSegregation and Solid Evolution during the Solidification of Niobium-Containing SuperalloysMicrostructural Evolution of Nickel-Base Superalloy Forgings during Ingot-to-Billet Conversion: Process Modeling and ValidationRemoval of Ceramic Defects from a Superalloy Powder Using Triboelectric ProcessingProduction Evaluation of 718ER(r) AlloyQuench Cracking Characterization of Superalloys Using Fracture Mechanics ApproachDevelopment and Characterization of a Damage Tolerant Microstructure for a Nickel Base Turbine Disc AlloyThe Microstructure Prediction of Alloy 720LI for Turbine Disk ApplicationsCharacteristics and Properties of As-HIP P/M Alloy 720Enhanced Powder Metallurgy (P/M) Processing of UDIMET(r)Alloy 720 Turbine Disks - Modeling StudiesCharacterization and Thermomechanical Processing of Sprayformed Allvac(r) 720Alloy

Solidification and Casting ProcessingProperties of RS5 and Other Superalloys Cast Using Thermally Controlled SolidificationAdvanced Superalloys and Tailored Microstructures for Integrally Cast Turbine WheelsImproved Quality and Economics of Investment Castings by Liquid Metal Cooling - The Selection of Cooling MediaA Novel Casting Process for Single Crystal Gas Turbine ComponentsCarbon Additions and Grain Defect Formation in High Refractory Nickel-Base Single Crystal SuperalloysNew Aspects of Freckle Formation during Single Crystal Solidification of CMSX-4Competitive Grain Growth and Texture Evolution during Directional Solidification of SuperalloysRecrystallization in Single Crystals of Nickel Base SuperalloysStructure of the Ni-Base Superalloy IN713C after Continuous CastingThe Thermal Analysis of the Mushy Zone and Grain Structure Changes during Directional Solidification of SuperalloysFreckle Formation in SuperalloysModelling of the Microsegregation in CMSX-4 Superalloy and its Homogenisation during Heat TreatmentEnhancement of the High Temperature Tensile Creep Strength of Monocrystalline Nickel-Base Superalloys by Pre-rafting in Compression

Blade AlloysAlloying Effects on Surface Stability and Creep Strength of Nickel Based Single Crystal Superalloys Containing 12 Mass% CrEvaluation of PWA 1483 for Large Single Crystal IGT Blade ApplicationsEffect of Ru Addition on Cast Nickel Base Superalloy with Low Content of Cr and High Content of WPrediction and Measurement of Microsegregation and Microstructural Evolution in Directionally Solidified SuperalloysDevelopment of a Third Generation DS SuperalloyThe Development and Long-Time Structural Stability of a Low Segregation Hf-free Superalloy - DZ125LThe Growth of Small Cracks in the Single Crystal Superalloy CMSX-4 at 750 and 1000 CThe Influence of Load Ratio, Temperature, Orientation and Hold Time on Fatigue Crack Growth of CMSX-4Modelling the Anisotropic and Biaxial Creep Behaviour of Ni-Base Single Crystal Superalloys CMSX-4 and SRR99 at 1223KCBED Measurement of Residual Internal Strains in the Neighbourhood of TCP Phases in Ni-Base SuperalloysThe Influence of Dislocation Substructure on Creep Rate During Accelerating Creep Stage of Single Crystal Nickel-based Superalloy CMSX-4Oxidation Improvements of Low Sulfur Processed Superalloys

Disk AlloysOptimisation of the Mechanical Properties of a New PM Superalloy for Disk Applicationsg' Formation in a Nickel-Base Disk SuperalloyMicrostructure and Mechanical Property Development in Superalloy U720LISub-Solidus HIP Process for P/M Superalloy Conventional Billet ConversionEffect of Oxidation on High Temperature Fatigue Crack Initiation and Short Crack Growth in Inconel 718The Effects of Processing on Stability of Alloy 718Long Term Thermal Stability of Inconel Alloys 718, 706, 909 and Waspaloy at 593 C and 704 CEffects of Microstructure and Loading Parameters on Fatigue Crack Propagation Rates in AF2-1DA-6The Common Strengthening Effect of Phosphorus, Sulfur and Silicon in Lower Contents and the Problem of a Net SuperalloySimulation of Microstructure of Nickel-Base Alloy 706 in Production of Power Generation Turbine Disks

Mechanical BehaviorInfluence of Long Term Exposure in Air on Microstructure, Surface Stability and Mechanical Properties of UDIMET 720LIEffects of Grain and Precipitate Size Variation on Creep-Fatigue Behaviour of UDIMET 720LI in Both Air and VacuumEffects of Local Cellular Transformation on Fatigue Small Crack Growth in CMSX-4 and CMSX-2 at High TemperatureMultiaxial Creep Deformation of Single Crystal Superalloys: Modelling and ValidationInvestigations of the Origin and Effect of Anomalous RaftingStress Rupture Behavior of Waspaloy and IN738LC at 600 C in Low Oxygen Gaseous Environments Containing SulfurIsothermal and Thermomechanical Fatigue of Superalloy C263Structure/Property Interactions in a Long Range Order Strengthened SuperalloyMicrostructural Changes in MA 760 during High Temperature Low Cycle FatigueHigh Temperature Low-Cycle Fatigue Behavior of Haynes 230 SuperalloyHigh Cycle Fatigue of ULTIMET AlloyThe Effect of Strain Rate and Temperature on the LCF Behavior of the ODS Nickel-Base Superalloy PM 1000Effect of Thermomechanical Processing on Fatigue Crack Propagation in INCONEL Alloy 783The Ductility of Haynes(r) 242 Alloy as a Function of Temperature, Strain Rate and Environment

Coatings, Welding and RepairProcessing Effects on the Failure of EBPVD TBCs on MCrAlY and Platinum Aluminide Bond CoatsCompositional Effects on Aluminide Oxidation Performance: Objectives for Improved Bond CoatsModelling and Neutron Diffraction Measurement of Stresses in Sprayed TBCsInterdiffusion Behavior in NiCoCrAlYRe-Coated IN-738 at 940 C and 1050 CEffect of Coating on the TMF Lives of Single Crystal and Columnar Grained CM186 Blade AlloyProcess Modelling of Electron Beam Welding of Aeroengine ComponentsNovel Techniques for Investigating the High Temperature Degradation of Protective Coatings on Nickel Base SuperalloysSintering of the Top Coat in Thermal Spray TBC Systems Under Service ConditionsOveraluminising of NiCoCrAlY Coatings by Arc PVD on Ni-Base SuperalloysThe Influence of B, P and C on Heat Affected Zone Micro-Fissuring in INCONEL type SuperalloyImproving Repair Quality of Turbine Nozzles Using SA650 Braze AlloyImproving Properties of Single Crystal to Polycrystalline Cast Alloy Welds through Heat Treatment

Alloy DevelopmentDevelopment of a New Single Crystal Superalloy for Industrial Gas TurbinesHigh g' Solvus New Generation Nickel-Based Superalloys for Single Crystal Turbine Blade ApplicationsDistribution of Platinum Group Metals in Ni-Base Single Crystal SuperalloysDevelopment of A Low Angle Grain Boundary Resistant Single Crystal Superalloy YH61Topologically Close Packed Phases in an Experimental Rhenium Containing Single Crystal SuperalloyA Low-Cost Second Generation Single Crystal Superalloy DD6The Development of Improved Performance PM UDIMET(r) 720 Turbine DisksMicrostructural Stability and Crack Growth Behaviour of a Polycrystalline Nickel-Base SuperalloyThe Application of CALPHAD Calculations to Ni-Based SuperalloysFormation of a Pt2Mo Type Phase in Long-Term Aged INCONEL Alloy 686Development of New Nitrided Nickel-Base Alloys for High Temperature ApplicationsMC-NG: A 4th Generation Single-Crystal Superalloy for Future Aeronautical Turbine Blades and Vanes