CA1192477A - Method of producing columnar crystal superalloy material with controlled orientation - Google Patents
Method of producing columnar crystal superalloy material with controlled orientationInfo
- Publication number
- CA1192477A CA1192477A CA000415909A CA415909A CA1192477A CA 1192477 A CA1192477 A CA 1192477A CA 000415909 A CA000415909 A CA 000415909A CA 415909 A CA415909 A CA 415909A CA 1192477 A CA1192477 A CA 1192477A
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- CA
- Canada
- Prior art keywords
- sheet
- cold
- rolling
- superalloy
- axis
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B1/00—Single-crystal growth directly from the solid state
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
- C30B29/10—Inorganic compounds or compositions
- C30B29/52—Alloys
Abstract
Method of Producing Columnar Crystal Superalloy Material With Controlled Orientation Abstract A processing sequence is described for producing specific controlled elongated oriented crystal structures in nickel base superalloys. The method is performed in the solid state. Superalloy material is provided in a dense workable form. The material is cold straight rolled and cold cross rolled with intermediate anneals. This sequence produces a particular texture or preferred orientation in the rolled article. This textured article is then directionally recrystallized to produce the desired final microstructure comprised of aligned elongated grains of a particular controllable orientation.
Description
Description Method of Producing Columnar Crystal Superalloy Material With Controlled Orientation Technical Field This invention relates to the field of nickel base superalloy articles having elongated aligned gxains of ; controlled orientation and to methods for producing , such articles.
Background Art It is known that metallic materials generally have a crystalline for,m, that is to say, individual atoms of the material have predictable relationship to their neigh~oring atoms and this relationship extends in a 1~ repetitive fashion throughout a particular crystal or grain. Nickel base superalloys have a face centered cubic structure. It is also known that the properties of such crystals vary significantly with orientation.
Most metallic articles contain many thousands of individual crystals or grains and the properties of such an article in a particular direction are reflective of average orientation of the individual crystals which , make up the article. If the grains or crystals have a random orientation then the article properties will be isotropic, that is equal in all directions. Although widely assumedr this is rarely the case since most ' casting and forming processes produce a preferred crystal ', orientation or text~re. In a deformation situation such preferred orientation results from several factors.
~' 30 Crystals in certain orientations are more resistant to deformation than are other crystals. These deformation F-~12 ~92~
resistant oriented crystals tend to rotate during deformation thereby producing a preferred vrientation.
During recrystallization, preferred orientations result from the preferential nucleation and/or growth of grains o~ certain orientations.
Textures have been extensively studied and some practical uses have been made of textured materials.
Particularly in the area of magnetic materials such as transformer steels, texturizing has produced substantial performance enhancements. This is dPscribed, for example, in U.S. Patent 3,219,496 and in an article in Metal Progress, December 1953, p. 71-75.
In another area, methods have been developed for the production of nickel base articles having elongated grains using directional recrystallization techniques.
This is described in U.S. Patent 3,975,219. In this patent, hot extrusion is used to densify superalloy powder which is then isothermally forged and direction-ally recrystalliæed by passage through a thermal gradient.
The patent does not indicate, what if any, preferred orientation resulted.
In another related area, the benefits of aligned grains of controlled orientation in aircraft gas turbine components are well known and are described in U.S. Patent 3,260,505 which described such components and the methods o~ their production by casting techniques.
Disclosure of Invention This inven~on has particular application to nickel base superalloys of the following broad composition range: 2-9% Al, 0-6% Ti, 0-16% Mo, 0-12% Ta, 0-12% W, 0-4% Cb, 0-20% Cr, 0-20% Co, 0-.3% C, 0-1% Y, 0-.3% B, 0-.3~ Zr, 0-2% V, 0-5% Re, ~alance essentially nickel.
I believe the invention to be generally applicable to all nickel base superalloys. The starting material is pro-vided in a workable form. One approach is to consolidate powder, another approach is to start with a casting, preferably a fine ~rain casting. This material is then hot worked at a temperature near but below the gamma prime solvus. Preferably this initial hot working is in an amount in excess of about 50%. This hot worked - material is then cold rolled, in a particular fashion, a further amount, about 65~. The cold rolling step is performed as follows: the material is first cold rolled. A second cold rolling step is performed in the cross rolling direction, i.e., a direction 90 removed from the direction of initial cold rolling.
The ratio of the reductions in the initial cold rolling step and final cold cross rolling step is about 75:25.
Intermediate annealing steps are employed during both cold and hot rolling steps as necessary to prevent cracking. The result is an article having a strong 110) C112~ sheet texture.
This textured material is directionally recrystal-lized to produce multiple elongated grains or single grains of a controlled orientation. The ~110} ~112~
texture controls- the orientation of the recrystallized grains. By varying the directional recrystallization parameters, a variety of final orientations can be produced.
Accordingly, this is the object of this invention to provide a method for producing nickel superalloy sheet ha~ing a strong ~110~ c112> sheet texture.
It is a further object of the invention to provide directionally recrystalli~ed sheets comprised of grains whose ~111~ direction is parallel to the cross rolling direction.
I~
It is another object of the invention to provide sheets whose ~110~ direction is parallel to the straight rolling direction.
And yet another object of the invention i5 to provide such sheets whose '100~ direction bisects the angle between the straight rolling and cross rolling direction.
The foregoing and other obiects, features and advantages of the present invention will become more apparent from the following description of preferred embodiments and accompanying drawings.
Brief Description of Drawings Fig. 1 shows the relation between the normal direction, straight rolling (S.R.) direction and cross rolling (X.R.) directions.
Fig. 2 shows the material orientation during straight rolling.
Fig. 3 shows the material orientation during cross rolling.
Fig. 4 shows the technique for producing a orientation material.
- Fig. 5 shows the technique for producing a ~1107 orientation material.
Fig. 6 shows the technique for producing a ~100 orientation material.
Figs. 7 through 10 are pole figures illustrating the texture produced by the processes described in Example 1 through 4.
^ 5 -Best Mode F~r Carrying Out The Invention The starting material is a nickel base superalloy powder. Generally, any nickel ~ase superalloy may be employed. The broad composition range of such alloys is: 2-9% Al, 0-6% Ta, 0-16% Mo, 0-12% Ta, 0-12% W, 0-4% Cb, 0-20% Cr, 0-20% Co, 0-2~ V, 0-5% Re, balance essentially nickel. Other minor ingredients may be present including 0-.3% C, 0-.5% Hf, 0-.3~ Zr, 0-.3~ B
and 0-1~ Y. These alloys are processed by a method which will produce a homogeneous hot wcrkable material.
The starting material should be homogeneous, dense, and hot workable. One approach is to consolidate superalloy powder, for example, by hot isostatic pressure (HIP) or by hot extrusion. Another approach is to start with a cast body, preferably a fine grain casting. If the powder approach is employed, care must be taken to prevent cont~m;nAtion of the powder and preferably, the powder is maintained and handled under inert conditions which will eliminate oxidation of the powder particles. The powder is then compacted to form an article of full theoretical density. The me-thod of compaction does not appear to be critical to the success of the invention. Typically hot isostatic pressing has been employed. The powder is sealed in an evacuated stainless steel can. Typical compaction conditions are gas pressures of about 15 ksi and temperatures of about 21-2250F for a time of about two hours followed by a furnace cooling. Hot extrusion methods have also been successfully utilized. Typical extrusion conditions are temperatures of 2200-2300F
and extrusion ratios ol ~r~ater than about 4:1. The powder is placed in a stainless steel container prior to extrusion.
32~
-- 6 ~
The workable article is then h~t deformed to achieve a reduction in area of at least 40% and preferably at leas~ 55%. This hot deformation improves the subsequent cold workability of the material. Hot rolling has been employed but other processes such as forging appear equally applicable. The process described in U~S.
Patent 3,519,503 may be emplo~ed. The hot deformation is performed at a temperature which is near but less than the ganm~ prime solvus temperature o~ the alloy, typically 2150-2275F. If hot rolling is employed, initial hot rolling passes are preferably per~ormed at the high end of the temperature range and with relatively low reductions per pass (i.e., 5%). Subsequent passes may be taken at greater reductions (i.e~, 15%) and the temperature may be allowed to decrease towards the low end of the range. The article is reheated between passes as appropriate to maintain the alloy within the desired temperature range. At the end of the hot working step, the material may be le~t in the worked condition and allowed to air coolO
The next step is the one which is the most significant in developing the desired texture. This is a two-stage rolling operation which ;s referred to as cold rolling but which may be performed at temperatures of up to about 1200F. This step may be understood through reference to Figure 1 which shows the strip prior to the cold rolling operation and shows three orthogonal axes, SR, XR and ND. The cold rolling operation comprises two steps, in the first step rolling is performed in the SR (straight rolling) direction and in the second step the rolling proceeds in ~he XR (cross rolling~ direction, i.e., at a 90~angle to the SR direction.
JW
The two steps of the cold rolling operation must produce a total reduction o~ more than 55% and most preferably more than 65~. The amount of deformation is apportioned between the two cold rolling steps so that nominally, 75~ of the deformation occurs in the initial straight rollins step and 25~ occurs in the cross rolling step. It is the sequence of steps which yields the desired final texture. The typical r~duction per pass is 1~2% and the total reduction between intermediate anneals ~e.g. 2200F for three minutes) is 8-15%. The ratio between the cold straight rolling and cold cross rolling steps may vary from 80:20 to 70:30 The result of this procedure is the development o~
a strong ~110~ ~112~ sheet texture. This means that a signifi_ant number of crystals in the sheet are oriented so that they have {1103 planes parallel to the sheet surface and C112~ directions which are parallel to the SR direction. Of course, in a random sheet a certain nu~ber of crystals would meet these criteria. However in sheets processed according to the preceding method, the number of crystals m~eting this criteria is at least 4x and usually at least 6x greater than expected in the random case.
I have discovered that the sheet: of this texture is highly receptive to directional recrystallization to produce recrystallized sheets whose orientation are different from the original texture and which are useful for the fabrication of superalloy articles as described in ~.S. Patent 3,~72,563. The previously described ~110}
3Q ~112~ sheet text~Fa can be used to produce directionally recrystallized materials having either the ~100~, ~110 or ~111> direction as a predominant direction in the sheet. I use the term directional recrystallization somewhat loosely and actually believe what occurs may be more accurately described as directional abnormal grain growth. That is to say, it seems likely that certain existing grains grow at the expense of other existing grains rather than the case of true directional recrystallization in which new grains would be nucleated and grow at the expense of the existing grains. Regard-. less of their origin it appears that differences in the rate of grain growth among competing grains producesthe obser~ed texture.
There are three primary crystal directions in the cubic system: the C100~, the <110~ and the~
- representing respectively, an edge of the unit cell, the face diagonal of the unit cell and a diagonal running between oppposite corners and passing through . the center of the cell. The ~100~ orientation has a low elastic modulus and thus turbine components whose primary axis coincides with a ~100~ axis will be resistant to thermal fatigue. Similarly, the ~111~
direction has a high elastic modulus and articles having this direction parallel to the primaxy stress direction are resistant to high cyclic fatigue. Through the i present invention and its ability to produce material with these different orientations, a high degree of flexibility is afforded the turbine component designer.
The method o~ producing sheet having these axes lying within the plane of the sheet is shown in Figures 4, 5 and 6. Figure 4 shows that passing the sheet through a thermal gradient such that the direction of the gradient is parallel to the XR axis results in sheet consisting of elongated grains whose axis of elongation is the Clll~ direction. As shown in the - Figure, the SR direction of the sheet contains ~110~
direction of the elongated crystals while the original normal direction of the sheet contains the ~112~ axis of the elongated crystals. In analogous fashion, Figure 5 shows that if the sheet is passed through the thermal gradient so that SR axis is parallel to the direction of motion through the thermal gradient, the grains have an axis of ~110~ and a ~110~ axis lies in the XR direction and ~100~ axis lies in the ND direction. The procedure shown in Figure 6 differs slightly in that the sheet passes through the the~mal gradient along an axis which bisects the SR and XR direction resulting in the -100~ direction by the elongation of the crystals and the two orthogonal axes being of the 1~0~ type.
- 15 Typically, the re~uired thermal gradient will have a steepness of at least about 100F measured at the gamma prime solvus temperature of the alloy. The hot end of the gradient will exceed the gamma prime solvus temperature but will obviously not exceed the incipient melting temperature of the alloy. Typical rates of traverse through the gradient will range from 1/8 to 4"
per hours.
- The present invention may be better understo~d by reference to the following examples which are intended to be illustrative rather than limiting.
Example 1 1 Composition - 14.4% Mo, 6.25% W, 6.8% Al, .04% C, balance Ni.
Background Art It is known that metallic materials generally have a crystalline for,m, that is to say, individual atoms of the material have predictable relationship to their neigh~oring atoms and this relationship extends in a 1~ repetitive fashion throughout a particular crystal or grain. Nickel base superalloys have a face centered cubic structure. It is also known that the properties of such crystals vary significantly with orientation.
Most metallic articles contain many thousands of individual crystals or grains and the properties of such an article in a particular direction are reflective of average orientation of the individual crystals which , make up the article. If the grains or crystals have a random orientation then the article properties will be isotropic, that is equal in all directions. Although widely assumedr this is rarely the case since most ' casting and forming processes produce a preferred crystal ', orientation or text~re. In a deformation situation such preferred orientation results from several factors.
~' 30 Crystals in certain orientations are more resistant to deformation than are other crystals. These deformation F-~12 ~92~
resistant oriented crystals tend to rotate during deformation thereby producing a preferred vrientation.
During recrystallization, preferred orientations result from the preferential nucleation and/or growth of grains o~ certain orientations.
Textures have been extensively studied and some practical uses have been made of textured materials.
Particularly in the area of magnetic materials such as transformer steels, texturizing has produced substantial performance enhancements. This is dPscribed, for example, in U.S. Patent 3,219,496 and in an article in Metal Progress, December 1953, p. 71-75.
In another area, methods have been developed for the production of nickel base articles having elongated grains using directional recrystallization techniques.
This is described in U.S. Patent 3,975,219. In this patent, hot extrusion is used to densify superalloy powder which is then isothermally forged and direction-ally recrystalliæed by passage through a thermal gradient.
The patent does not indicate, what if any, preferred orientation resulted.
In another related area, the benefits of aligned grains of controlled orientation in aircraft gas turbine components are well known and are described in U.S. Patent 3,260,505 which described such components and the methods o~ their production by casting techniques.
Disclosure of Invention This inven~on has particular application to nickel base superalloys of the following broad composition range: 2-9% Al, 0-6% Ti, 0-16% Mo, 0-12% Ta, 0-12% W, 0-4% Cb, 0-20% Cr, 0-20% Co, 0-.3% C, 0-1% Y, 0-.3% B, 0-.3~ Zr, 0-2% V, 0-5% Re, ~alance essentially nickel.
I believe the invention to be generally applicable to all nickel base superalloys. The starting material is pro-vided in a workable form. One approach is to consolidate powder, another approach is to start with a casting, preferably a fine ~rain casting. This material is then hot worked at a temperature near but below the gamma prime solvus. Preferably this initial hot working is in an amount in excess of about 50%. This hot worked - material is then cold rolled, in a particular fashion, a further amount, about 65~. The cold rolling step is performed as follows: the material is first cold rolled. A second cold rolling step is performed in the cross rolling direction, i.e., a direction 90 removed from the direction of initial cold rolling.
The ratio of the reductions in the initial cold rolling step and final cold cross rolling step is about 75:25.
Intermediate annealing steps are employed during both cold and hot rolling steps as necessary to prevent cracking. The result is an article having a strong 110) C112~ sheet texture.
This textured material is directionally recrystal-lized to produce multiple elongated grains or single grains of a controlled orientation. The ~110} ~112~
texture controls- the orientation of the recrystallized grains. By varying the directional recrystallization parameters, a variety of final orientations can be produced.
Accordingly, this is the object of this invention to provide a method for producing nickel superalloy sheet ha~ing a strong ~110~ c112> sheet texture.
It is a further object of the invention to provide directionally recrystalli~ed sheets comprised of grains whose ~111~ direction is parallel to the cross rolling direction.
I~
It is another object of the invention to provide sheets whose ~110~ direction is parallel to the straight rolling direction.
And yet another object of the invention i5 to provide such sheets whose '100~ direction bisects the angle between the straight rolling and cross rolling direction.
The foregoing and other obiects, features and advantages of the present invention will become more apparent from the following description of preferred embodiments and accompanying drawings.
Brief Description of Drawings Fig. 1 shows the relation between the normal direction, straight rolling (S.R.) direction and cross rolling (X.R.) directions.
Fig. 2 shows the material orientation during straight rolling.
Fig. 3 shows the material orientation during cross rolling.
Fig. 4 shows the technique for producing a orientation material.
- Fig. 5 shows the technique for producing a ~1107 orientation material.
Fig. 6 shows the technique for producing a ~100 orientation material.
Figs. 7 through 10 are pole figures illustrating the texture produced by the processes described in Example 1 through 4.
^ 5 -Best Mode F~r Carrying Out The Invention The starting material is a nickel base superalloy powder. Generally, any nickel ~ase superalloy may be employed. The broad composition range of such alloys is: 2-9% Al, 0-6% Ta, 0-16% Mo, 0-12% Ta, 0-12% W, 0-4% Cb, 0-20% Cr, 0-20% Co, 0-2~ V, 0-5% Re, balance essentially nickel. Other minor ingredients may be present including 0-.3% C, 0-.5% Hf, 0-.3~ Zr, 0-.3~ B
and 0-1~ Y. These alloys are processed by a method which will produce a homogeneous hot wcrkable material.
The starting material should be homogeneous, dense, and hot workable. One approach is to consolidate superalloy powder, for example, by hot isostatic pressure (HIP) or by hot extrusion. Another approach is to start with a cast body, preferably a fine grain casting. If the powder approach is employed, care must be taken to prevent cont~m;nAtion of the powder and preferably, the powder is maintained and handled under inert conditions which will eliminate oxidation of the powder particles. The powder is then compacted to form an article of full theoretical density. The me-thod of compaction does not appear to be critical to the success of the invention. Typically hot isostatic pressing has been employed. The powder is sealed in an evacuated stainless steel can. Typical compaction conditions are gas pressures of about 15 ksi and temperatures of about 21-2250F for a time of about two hours followed by a furnace cooling. Hot extrusion methods have also been successfully utilized. Typical extrusion conditions are temperatures of 2200-2300F
and extrusion ratios ol ~r~ater than about 4:1. The powder is placed in a stainless steel container prior to extrusion.
32~
-- 6 ~
The workable article is then h~t deformed to achieve a reduction in area of at least 40% and preferably at leas~ 55%. This hot deformation improves the subsequent cold workability of the material. Hot rolling has been employed but other processes such as forging appear equally applicable. The process described in U~S.
Patent 3,519,503 may be emplo~ed. The hot deformation is performed at a temperature which is near but less than the ganm~ prime solvus temperature o~ the alloy, typically 2150-2275F. If hot rolling is employed, initial hot rolling passes are preferably per~ormed at the high end of the temperature range and with relatively low reductions per pass (i.e., 5%). Subsequent passes may be taken at greater reductions (i.e~, 15%) and the temperature may be allowed to decrease towards the low end of the range. The article is reheated between passes as appropriate to maintain the alloy within the desired temperature range. At the end of the hot working step, the material may be le~t in the worked condition and allowed to air coolO
The next step is the one which is the most significant in developing the desired texture. This is a two-stage rolling operation which ;s referred to as cold rolling but which may be performed at temperatures of up to about 1200F. This step may be understood through reference to Figure 1 which shows the strip prior to the cold rolling operation and shows three orthogonal axes, SR, XR and ND. The cold rolling operation comprises two steps, in the first step rolling is performed in the SR (straight rolling) direction and in the second step the rolling proceeds in ~he XR (cross rolling~ direction, i.e., at a 90~angle to the SR direction.
JW
The two steps of the cold rolling operation must produce a total reduction o~ more than 55% and most preferably more than 65~. The amount of deformation is apportioned between the two cold rolling steps so that nominally, 75~ of the deformation occurs in the initial straight rollins step and 25~ occurs in the cross rolling step. It is the sequence of steps which yields the desired final texture. The typical r~duction per pass is 1~2% and the total reduction between intermediate anneals ~e.g. 2200F for three minutes) is 8-15%. The ratio between the cold straight rolling and cold cross rolling steps may vary from 80:20 to 70:30 The result of this procedure is the development o~
a strong ~110~ ~112~ sheet texture. This means that a signifi_ant number of crystals in the sheet are oriented so that they have {1103 planes parallel to the sheet surface and C112~ directions which are parallel to the SR direction. Of course, in a random sheet a certain nu~ber of crystals would meet these criteria. However in sheets processed according to the preceding method, the number of crystals m~eting this criteria is at least 4x and usually at least 6x greater than expected in the random case.
I have discovered that the sheet: of this texture is highly receptive to directional recrystallization to produce recrystallized sheets whose orientation are different from the original texture and which are useful for the fabrication of superalloy articles as described in ~.S. Patent 3,~72,563. The previously described ~110}
3Q ~112~ sheet text~Fa can be used to produce directionally recrystallized materials having either the ~100~, ~110 or ~111> direction as a predominant direction in the sheet. I use the term directional recrystallization somewhat loosely and actually believe what occurs may be more accurately described as directional abnormal grain growth. That is to say, it seems likely that certain existing grains grow at the expense of other existing grains rather than the case of true directional recrystallization in which new grains would be nucleated and grow at the expense of the existing grains. Regard-. less of their origin it appears that differences in the rate of grain growth among competing grains producesthe obser~ed texture.
There are three primary crystal directions in the cubic system: the C100~, the <110~ and the~
- representing respectively, an edge of the unit cell, the face diagonal of the unit cell and a diagonal running between oppposite corners and passing through . the center of the cell. The ~100~ orientation has a low elastic modulus and thus turbine components whose primary axis coincides with a ~100~ axis will be resistant to thermal fatigue. Similarly, the ~111~
direction has a high elastic modulus and articles having this direction parallel to the primaxy stress direction are resistant to high cyclic fatigue. Through the i present invention and its ability to produce material with these different orientations, a high degree of flexibility is afforded the turbine component designer.
The method o~ producing sheet having these axes lying within the plane of the sheet is shown in Figures 4, 5 and 6. Figure 4 shows that passing the sheet through a thermal gradient such that the direction of the gradient is parallel to the XR axis results in sheet consisting of elongated grains whose axis of elongation is the Clll~ direction. As shown in the - Figure, the SR direction of the sheet contains ~110~
direction of the elongated crystals while the original normal direction of the sheet contains the ~112~ axis of the elongated crystals. In analogous fashion, Figure 5 shows that if the sheet is passed through the thermal gradient so that SR axis is parallel to the direction of motion through the thermal gradient, the grains have an axis of ~110~ and a ~110~ axis lies in the XR direction and ~100~ axis lies in the ND direction. The procedure shown in Figure 6 differs slightly in that the sheet passes through the the~mal gradient along an axis which bisects the SR and XR direction resulting in the -100~ direction by the elongation of the crystals and the two orthogonal axes being of the 1~0~ type.
- 15 Typically, the re~uired thermal gradient will have a steepness of at least about 100F measured at the gamma prime solvus temperature of the alloy. The hot end of the gradient will exceed the gamma prime solvus temperature but will obviously not exceed the incipient melting temperature of the alloy. Typical rates of traverse through the gradient will range from 1/8 to 4"
per hours.
- The present invention may be better understo~d by reference to the following examples which are intended to be illustrative rather than limiting.
Example 1 1 Composition - 14.4% Mo, 6.25% W, 6.8% Al, .04% C, balance Ni.
2. Powder Siz~ -80 mesh (~.S. Std~ Sieve)
3. Consolidation Method - Hot Isostatic Pressing (H.I.P.) at 2250F and 15 ksi pressure for two hours.
4. ~ot Working - by rolling at 2200F to 60%
reduction.
reduction.
5. Cold Rolling - total reduction 65%
a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200DF.
a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200DF.
6. Resultant Texture - singular ~110} ~112~, 7x random as shown in FigO 7.
7. Directional Recrystallization (180F/in gradient measured at gamma prime solvus temperature) a. D.R. parallel to cold cross rolling dixection at l/4"/hr. - result - ~112~ in plane of sheet, 111~ axial orientation.
b. D.R. parallel to cold straight rolling direction at 5/8-2"/hr - result - {100} in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisecting cold straight rolling and cold cross rolling directions (45 off axis~ at 5/8-2"/hr - result - {100~
in plane of sheet, ~100> in axial direction.
Exam~le 2 1. Composition - 9.0~ Cr, 5.0% Al, 10.0% Co, 200~ Ti, 12-~ W, 1.0~ Cb, 0.15% C, 0.015% B, O.05% Zr (Alloy MAR-M200) balance Ni.
2. Powder Size - -80 mesh (U.S. Std. Sieve) 3. Consolidation Plethod - Extrusion at 1950F at a 6.8:1 extrusion ratioO
4. Hot Working by isothermal forging at 2050~, strain rate of .1 min 1, 60~ -total strain.
5. Cold Rolling total reduction 60 a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2100F.
6. Resultant Texture - singular ~110~ .112~, 4~7x random as shown in Fig. 8.
7. Directional recrystallization not yet evaluated.
~l9~47~
Example 3 1. Composition - 9.0~ Cr, 7.0% Al, 9.5~ W, 3.0% Ta, 1.0% Mo, balance Ni.
2. Powder Size - -80 mesh (U.S. Std. Sie~e) 3. Consolidation Method - Hot Isotatic Pressing (H.I.P.) at 2250F and 15 ksi pressure for two hours.
4. Hot Working - by rolling at 2200F to 60 reduction.
5. Cold Rolling - total reduction 65 a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200F.
6. Resultant Texture - singular ~110~ ~112>, 12x random as shown in Fig. 9.
7. Directional ~ecrystallization (180F/in gradient measured at gamma prime solvus temperature) a. D.R. parallel to cold cross rolling direction at l/4"/hr. - result - fll2~ in plane of sheet, ~111> axial orientation.
b. D.R. parallel to cold straight rolling direction at 5/8-2"/hr - result - ~100~ in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisecting cold straight rolling and cold cross rolling directions (45 off axis) at 5/8-2"/hr - result - ~100~
in plane of sheet, ~100> in axial direction.
~ 13 -Example 4 1. Composition - 9.0% Cr, 6.5% Al, 9.5% W, 1.6% Ta, 1.0% Mo, .8% Cb, 0.05% C, 0.01% B, 0.1% Zr, balance Ni.
2. Powder Si~e - -80 mesh (U.S. Std. Sieve) 3. Consolidation Method - Hot Isostatic Pressing (H.I.P.) at 2250F and 15 ksi pressure for two hours.
4. Hot Working - by rolling at 2200F to 60 reduction.
5. Cold Rolling - total reduction 65%
a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200F.
6. Resultant Texture - singular ~110} c112~, 8x random as shown in Fig. 10.
7. Directional Recrystallization (180F/in gradi~nt measured at gamma prime solvus temperature) a. D.R. parallel to cold cross rollin~ direction at l/4"/hr. - result - ~1121 in plane of sheet, ~ axial orientation.
b. D.R. parallel to cold straigh~ rolling direction at 5/8-2"/hr - result - {100} in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisectins cold straight rolling and cold cross rolling dixectlons (45 off axis~ at 5/8-2"/hr - result - ~100}
in plane of sheet, ~100~ in axial direction.
;
~3 ~.g2~7~
Although this invention has been shown and described with respect to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail thereof may be made withou~ departing from the spirit and scope of the claimed invention.
b. D.R. parallel to cold straight rolling direction at 5/8-2"/hr - result - {100} in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisecting cold straight rolling and cold cross rolling directions (45 off axis~ at 5/8-2"/hr - result - {100~
in plane of sheet, ~100> in axial direction.
Exam~le 2 1. Composition - 9.0~ Cr, 5.0% Al, 10.0% Co, 200~ Ti, 12-~ W, 1.0~ Cb, 0.15% C, 0.015% B, O.05% Zr (Alloy MAR-M200) balance Ni.
2. Powder Size - -80 mesh (U.S. Std. Sieve) 3. Consolidation Plethod - Extrusion at 1950F at a 6.8:1 extrusion ratioO
4. Hot Working by isothermal forging at 2050~, strain rate of .1 min 1, 60~ -total strain.
5. Cold Rolling total reduction 60 a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2100F.
6. Resultant Texture - singular ~110~ .112~, 4~7x random as shown in Fig. 8.
7. Directional recrystallization not yet evaluated.
~l9~47~
Example 3 1. Composition - 9.0~ Cr, 7.0% Al, 9.5~ W, 3.0% Ta, 1.0% Mo, balance Ni.
2. Powder Size - -80 mesh (U.S. Std. Sie~e) 3. Consolidation Method - Hot Isotatic Pressing (H.I.P.) at 2250F and 15 ksi pressure for two hours.
4. Hot Working - by rolling at 2200F to 60 reduction.
5. Cold Rolling - total reduction 65 a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200F.
6. Resultant Texture - singular ~110~ ~112>, 12x random as shown in Fig. 9.
7. Directional ~ecrystallization (180F/in gradient measured at gamma prime solvus temperature) a. D.R. parallel to cold cross rolling direction at l/4"/hr. - result - fll2~ in plane of sheet, ~111> axial orientation.
b. D.R. parallel to cold straight rolling direction at 5/8-2"/hr - result - ~100~ in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisecting cold straight rolling and cold cross rolling directions (45 off axis) at 5/8-2"/hr - result - ~100~
in plane of sheet, ~100> in axial direction.
~ 13 -Example 4 1. Composition - 9.0% Cr, 6.5% Al, 9.5% W, 1.6% Ta, 1.0% Mo, .8% Cb, 0.05% C, 0.01% B, 0.1% Zr, balance Ni.
2. Powder Si~e - -80 mesh (U.S. Std. Sieve) 3. Consolidation Method - Hot Isostatic Pressing (H.I.P.) at 2250F and 15 ksi pressure for two hours.
4. Hot Working - by rolling at 2200F to 60 reduction.
5. Cold Rolling - total reduction 65%
a. cold straight rolled b. cold cross rolled ratio of cold straight rolling to cold cross rolling = 75:25, intermediate anneals at 2200F.
6. Resultant Texture - singular ~110} c112~, 8x random as shown in Fig. 10.
7. Directional Recrystallization (180F/in gradi~nt measured at gamma prime solvus temperature) a. D.R. parallel to cold cross rollin~ direction at l/4"/hr. - result - ~1121 in plane of sheet, ~ axial orientation.
b. D.R. parallel to cold straigh~ rolling direction at 5/8-2"/hr - result - {100} in plane of sheet, ~110~ in axial direction.
c. D.R. in direction bisectins cold straight rolling and cold cross rolling dixectlons (45 off axis~ at 5/8-2"/hr - result - ~100}
in plane of sheet, ~100~ in axial direction.
;
~3 ~.g2~7~
Although this invention has been shown and described with respect to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail thereof may be made withou~ departing from the spirit and scope of the claimed invention.
Claims (7)
1. A nickel base superalloy sheet having a {110}<112>
singular texture of an intensity at least 4x random.
singular texture of an intensity at least 4x random.
2. A sheet as in claim 1 having a texture intensity of at least 6x random.
3. A directionally recrystallized nickel base superalloy sheet comprised of aligned elongated grains with the <111> direction being parallel to the axis of elongation.
4. A directionally recrystallized nickel superalloy sheet comprised of aligned elongated grains with the <110> direction being parallel to the axis of elongation.
5. A directionally recrystallized nickel superalloy sheet comprised of aligned elongated grains with the <100> direction being parallel to the axis of elongation.
6. A method for producing nickel superalloy sheet comprised of aligned, elongated grains whose axis of elongation corresponds essentially to the direction including the steps of a. providing a textured nickel superalloy sheet having a {110} <112> sheet texture with the <112> axis corresponding essentially to the (straight) rolling direction b. passing the sheet through a thermal gradient whose hot end exceeds the recrystallization temperature of the alloy so as to effect directional recrystallization whereby the resultant sheet will contain elongated grains whose axis of elongation is a first <110>
direction with a second <110> direction lying in the sheet and a <100> orientation being perpendicular to the sheet, said second <110> direction and said <100>
direction being orthogonal to said first <110>
direction.
direction with a second <110> direction lying in the sheet and a <100> orientation being perpendicular to the sheet, said second <110> direction and said <100>
direction being orthogonal to said first <110>
direction.
7. A method for producing a textured superalloy article including the steps of a. providing a hot workable superalloy article of full density b. hot working the article at a temperature near the gamma prime solvus c. cold rolling the material along a particular direction with intermediate anneals d. cold working the material in a direction 90°
removed from the direction used in step c with intermediate anneals with the total reduction in steps c and d exceeding 50% and with the ratio of reductions in steps c and d ranging from 70:30 to 80:20.
removed from the direction used in step c with intermediate anneals with the total reduction in steps c and d exceeding 50% and with the ratio of reductions in steps c and d ranging from 70:30 to 80:20.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US325,248 | 1981-11-27 | ||
| US06/325,248 US4518442A (en) | 1981-11-27 | 1981-11-27 | Method of producing columnar crystal superalloy material with controlled orientation and product |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1192477A true CA1192477A (en) | 1985-08-27 |
Family
ID=23267066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000415909A Expired CA1192477A (en) | 1981-11-27 | 1982-11-18 | Method of producing columnar crystal superalloy material with controlled orientation |
Country Status (17)
| Country | Link |
|---|---|
| US (1) | US4518442A (en) |
| JP (1) | JPS5896845A (en) |
| AU (1) | AU558195B2 (en) |
| BE (1) | BE895059A (en) |
| BR (1) | BR8206836A (en) |
| CA (1) | CA1192477A (en) |
| CH (1) | CH655951A5 (en) |
| DE (1) | DE3242607A1 (en) |
| ES (1) | ES8404712A1 (en) |
| FR (1) | FR2519350B1 (en) |
| GB (1) | GB2110241B (en) |
| IL (1) | IL67348A (en) |
| IT (1) | IT1154576B (en) |
| NL (1) | NL189678C (en) |
| NO (1) | NO156092C (en) |
| SE (1) | SE462803B (en) |
| ZA (1) | ZA828523B (en) |
Families Citing this family (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4522664A (en) * | 1983-04-04 | 1985-06-11 | General Electric Company | Phase stable carbide reinforced nickel-base superalloy eutectics having improved high temperature stress-rupture strength and improved resistance to surface carbide formation |
| US4554414A (en) * | 1983-04-28 | 1985-11-19 | Harman International Industries Incorporated | Multi-driver loudspeaker |
| US4499155A (en) * | 1983-07-25 | 1985-02-12 | United Technologies Corporation | Article made from sheet having a controlled crystallographic orientation |
| GB2153845A (en) * | 1984-02-07 | 1985-08-29 | Inco Alloys Products Limited | Production of superalloy sheet |
| US4702782A (en) * | 1986-11-24 | 1987-10-27 | United Technologies Corporation | High modulus shafts |
| CH671583A5 (en) * | 1986-12-19 | 1989-09-15 | Bbc Brown Boveri & Cie | |
| GB2235697B (en) * | 1986-12-30 | 1991-08-14 | Gen Electric | Improved and property-balanced nickel-base superalloys for producing single crystal articles. |
| US4781772A (en) * | 1988-02-22 | 1988-11-01 | Inco Alloys International, Inc. | ODS alloy having intermediate high temperature strength |
| JPH0225537A (en) * | 1988-07-15 | 1990-01-29 | Natl Res Inst For Metals | Heat-resistant ni-base alloy for super plastic forging and production of the alloy and forgings |
| US4932974A (en) * | 1989-07-06 | 1990-06-12 | Pappas Michael J | Prosthetic device with predetermined crystal orientation |
| US5820700A (en) * | 1993-06-10 | 1998-10-13 | United Technologies Corporation | Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air |
| FR2722510B1 (en) * | 1994-07-13 | 1996-08-14 | Snecma | PROCESS FOR THE PREPARATION OF 718 ALLOY SHEETS AND FOR THE SUPERPLASTIC FORMING OF SAME |
| US5725692A (en) * | 1995-10-02 | 1998-03-10 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
| US5682747A (en) * | 1996-04-10 | 1997-11-04 | General Electric Company | Gas turbine combustor heat shield of casted super alloy |
| DE19624055A1 (en) * | 1996-06-17 | 1997-12-18 | Abb Research Ltd | Nickel-based super alloy |
| DE10100790C2 (en) * | 2001-01-10 | 2003-07-03 | Mtu Aero Engines Gmbh | Nickel-based alloy for the cast-technical production of solidified components |
| US7338259B2 (en) * | 2004-03-02 | 2008-03-04 | United Technologies Corporation | High modulus metallic component for high vibratory operation |
| US20050227106A1 (en) * | 2004-04-08 | 2005-10-13 | Schlichting Kevin W | Single crystal combustor panels having controlled crystallographic orientation |
| US7378132B2 (en) * | 2004-12-14 | 2008-05-27 | Honeywell International, Inc. | Method for applying environmental-resistant MCrAlY coatings on gas turbine components |
| US20070095441A1 (en) * | 2005-11-01 | 2007-05-03 | General Electric Company | Nickel-base alloy, articles formed therefrom, and process therefor |
| US8708659B2 (en) | 2010-09-24 | 2014-04-29 | United Technologies Corporation | Turbine engine component having protective coating |
| US9551049B2 (en) * | 2012-08-28 | 2017-01-24 | United Technologies Corporation | High elastic modulus shafts and method of manufacture |
| WO2015122947A2 (en) * | 2013-12-06 | 2015-08-20 | United Technologies Corporation | Aluminum alloy airfoil with designed crystallographic texture |
| US10920595B2 (en) | 2017-01-13 | 2021-02-16 | General Electric Company | Turbine component having multiple controlled metallic grain orientations, apparatus and manufacturing method thereof |
| CN108588498B (en) * | 2018-05-30 | 2020-04-07 | 哈尔滨理工大学 | Nickel-based gradient material and method for preparing nickel-based gradient material by selective laser melting method |
| CN110592506B (en) * | 2019-09-29 | 2020-12-25 | 北京钢研高纳科技股份有限公司 | GH4780 alloy blank and forging and preparation method thereof |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3346427A (en) * | 1964-11-10 | 1967-10-10 | Du Pont | Dispersion hardened metal sheet and process |
| NL171309C (en) * | 1970-03-02 | 1983-03-01 | Hitachi Ltd | METHOD FOR THE MANUFACTURE OF A SEMICONDUCTOR BODY FORMING A SILICONE DIOXIDE LAYER ON A SURFACE OF A SILICONE MONOCRYSTALLINE BODY |
| US4002503A (en) * | 1970-09-29 | 1977-01-11 | Johnson, Matthey & Co., Limited | Treatment of metals and alloy |
| GB1381859A (en) * | 1971-05-26 | 1975-01-29 | Nat Res Dev | Trinickel aluminide base alloys |
| US3787205A (en) * | 1972-05-30 | 1974-01-22 | Int Nickel Co | Forging metal powders |
| US3992161A (en) * | 1973-01-22 | 1976-11-16 | The International Nickel Company, Inc. | Iron-chromium-aluminum alloys with improved high temperature properties |
| GB1449273A (en) * | 1973-07-25 | 1976-09-15 | Gen Electric | Heat treatment of alloys |
| US3975219A (en) * | 1975-09-02 | 1976-08-17 | United Technologies Corporation | Thermomechanical treatment for nickel base superalloys |
| US3982973A (en) * | 1975-12-11 | 1976-09-28 | The International Nickel Company, Inc. | Cube textured nickel |
| US4129464A (en) * | 1977-08-24 | 1978-12-12 | Cabot Corporation | High yield strength Ni-Cr-Mo alloys and methods of producing the same |
-
1981
- 1981-11-27 US US06/325,248 patent/US4518442A/en not_active Expired - Lifetime
-
1982
- 1982-11-18 CA CA000415909A patent/CA1192477A/en not_active Expired
- 1982-11-18 DE DE19823242607 patent/DE3242607A1/en active Granted
- 1982-11-18 ZA ZA828523A patent/ZA828523B/en unknown
- 1982-11-18 BE BE0/209509A patent/BE895059A/en not_active IP Right Cessation
- 1982-11-19 GB GB08233043A patent/GB2110241B/en not_active Expired
- 1982-11-19 NL NLAANVRAGE8204494,A patent/NL189678C/en not_active IP Right Cessation
- 1982-11-22 AU AU90773/82A patent/AU558195B2/en not_active Ceased
- 1982-11-23 CH CH6818/82A patent/CH655951A5/en not_active IP Right Cessation
- 1982-11-24 IT IT24402/82A patent/IT1154576B/en active
- 1982-11-24 SE SE8206694A patent/SE462803B/en not_active IP Right Cessation
- 1982-11-25 BR BR8206836A patent/BR8206836A/en not_active IP Right Cessation
- 1982-11-25 NO NO823951A patent/NO156092C/en not_active IP Right Cessation
- 1982-11-26 IL IL67348A patent/IL67348A/en not_active IP Right Cessation
- 1982-11-26 ES ES517721A patent/ES8404712A1/en not_active Expired
- 1982-11-26 JP JP57207488A patent/JPS5896845A/en active Granted
- 1982-11-26 FR FR8219855A patent/FR2519350B1/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| AU558195B2 (en) | 1987-01-22 |
| NO156092C (en) | 1987-07-29 |
| IL67348A (en) | 1986-04-29 |
| ES517721A0 (en) | 1984-05-16 |
| IL67348A0 (en) | 1983-03-31 |
| US4518442A (en) | 1985-05-21 |
| NL189678C (en) | 1993-06-16 |
| SE462803B (en) | 1990-09-03 |
| IT8224402A1 (en) | 1984-05-24 |
| IT8224402A0 (en) | 1982-11-24 |
| ZA828523B (en) | 1983-09-28 |
| ES8404712A1 (en) | 1984-05-16 |
| IT1154576B (en) | 1987-01-21 |
| NL8204494A (en) | 1983-06-16 |
| BR8206836A (en) | 1983-10-04 |
| FR2519350A1 (en) | 1983-07-08 |
| SE8206694L (en) | 1983-05-28 |
| SE8206694D0 (en) | 1982-11-24 |
| GB2110241A (en) | 1983-06-15 |
| CH655951A5 (en) | 1986-05-30 |
| DE3242607A1 (en) | 1983-06-01 |
| AU9077382A (en) | 1983-06-02 |
| DE3242607C2 (en) | 1988-09-15 |
| NO156092B (en) | 1987-04-13 |
| FR2519350B1 (en) | 1985-09-06 |
| GB2110241B (en) | 1985-09-18 |
| JPS5896845A (en) | 1983-06-09 |
| NO823951L (en) | 1983-05-30 |
| BE895059A (en) | 1983-03-16 |
| JPH0118988B2 (en) | 1989-04-10 |
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