CN115070041B - GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof - Google Patents
GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof Download PDFInfo
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- CN115070041B CN115070041B CN202110261044.XA CN202110261044A CN115070041B CN 115070041 B CN115070041 B CN 115070041B CN 202110261044 A CN202110261044 A CN 202110261044A CN 115070041 B CN115070041 B CN 115070041B
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- 239000000463 material Substances 0.000 title claims abstract description 30
- 238000002360 preparation method Methods 0.000 title claims abstract description 19
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 63
- 239000000956 alloy Substances 0.000 claims abstract description 63
- 239000000843 powder Substances 0.000 claims abstract description 36
- 238000000034 method Methods 0.000 claims abstract description 32
- 238000001513 hot isostatic pressing Methods 0.000 claims abstract description 28
- 238000010438 heat treatment Methods 0.000 claims abstract description 24
- 238000003466 welding Methods 0.000 claims abstract description 22
- 238000003825 pressing Methods 0.000 claims abstract description 14
- 230000032683 aging Effects 0.000 claims abstract description 13
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 238000001816 cooling Methods 0.000 claims description 16
- 238000011049 filling Methods 0.000 claims description 13
- 210000000746 body region Anatomy 0.000 claims description 12
- 238000004321 preservation Methods 0.000 claims description 9
- 238000003754 machining Methods 0.000 claims description 7
- 230000035882 stress Effects 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 238000002156 mixing Methods 0.000 abstract description 3
- 238000000465 moulding Methods 0.000 abstract description 3
- 239000002775 capsule Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000011056 performance test Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 230000014509 gene expression Effects 0.000 description 2
- 238000007654 immersion Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 239000011812 mixed powder Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000010275 isothermal forging Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/008—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of engine cylinder parts or of piston parts other than piston rings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly and a hot isostatic pressing near-net forming preparation method thereof, wherein the multistage rotor assembly is divided into two alloy areas, different alloy areas are compacted by a cold pressing method when powder is filled before hot isostatic pressing, and after hot isostatic pressing, the two different alloy areas and a heterogeneous material combination area are subjected to zonal solution heat treatment and aging treatment, so that the prepared rotor assembly can be freely combined in structural form and is not limited by the number of assembly stages; the final rotor assembly is formed by one-time hot isostatic pressing, the uniformity of the joint surface structure is good, the overall performance of the multi-stage rotor is high, the lean manufacturing of the multi-stage rotor assembly of the same GH4169 and TC17 alloy and different materials is realized, and the use performance of the rotor is improved; in addition, the method adopts cold press molding to the pre-pressed body, so that powder mixing can be avoided, the preparation cost of large welding equipment is reduced, the preparation process flow is shortened, and the preparation difficulty is reduced.
Description
Technical Field
The invention relates to an aeroengine rotor manufacturing technology, in particular to a dissimilar alloy multistage rotor assembly and a preparation method thereof.
Background
The aeroengine rotor operates at high temperature, high pressure and high rotation speed, parts bear thermal load, pneumatic load, centrifugal load and the like, and higher requirements are put on the comprehensive performance of the rotor assembly. On the one hand, as the thrust-weight ratio of the engine increases, the service temperature of the disc member is continuously increased, so that the powder superalloy GH4169 alloy and the low-cost TC17 alloy are gradually applied to the disc rotating member of the aeroengine, such as a high-pressure compressor disc, a high-pressure turbine disc and the like. On the other hand, in order to reduce the structural weight and enhance the structural reliability, the aeroengine rotor is developed in the light weight and integration direction, and the rotor combined by different materials also brings about the problem of integrated connection.
In the aspect of multi-stage rotor integration, the most widely used technology is to realize the connection of multi-stage rotor components by welding. In the selection of the welding method, TC17 and GH4169 are very different in material composition and structural performance, so that the welding process cannot be directly adopted for connection, and the bolt connection adopted for the connection mode between the titanium alloy and the high-temperature alloy rotor assembly is adopted at present. But bolting increases the weight of the rotor assembly and reduces the reliability of the connection, thereby increasing the overall weight of the engine and reducing the efficiency of the engine.
In recent years, the hot isostatic pressing near net shape forming technology is mature, and the technology combines hot isostatic pressing densification and near net shape forming process control, and can provide a hot blank with required shape, size and structure for subsequent mechanical processing, isothermal forging or heat treatment processes.
The hot isostatic pressing near net shape process has the following advantages over the welding process of typical rotor assemblies:
1) Uniform structure and high mechanical property: the near-net-shaped part by hot isostatic pressing has high density, uniform components and no macroscopic component segregation in the structure, so that the comprehensive mechanical property is excellent, can reach the forging level and is higher than the mechanical property of a welded joint.
2) And the machining procedures are reduced: compared with the machining by adopting the forging piece, the hot isostatic pressing near-net forming part has relatively simple technical process, and only the combined machining is carried out in the assembly, so that the machining procedures of the rotor assembly before welding are reduced.
3) The equipment is simple: the hot isostatic pressing near-net forming technology mainly utilizes hot isostatic pressing equipment, avoids the use of large-scale welding equipment, especially large-scale inertia friction welding equipment, and solves the problem of welding equipment resource shortage.
4) The device is applicable to various structures: for various structures, particularly complex structures, the preparation can be performed by a hot isostatic pressing near net shape forming process.
5) The manufacturing cost is low: the material utilization rate of the hot isostatic pressing near-net formed part is high, the technological process is relatively simple, the technological period is short, and the manufacturing cost is reduced.
The multi-stage rotor assembly of the same kind and different kinds of materials of GH4169 and TC17 alloy is prepared by adopting a hot isostatic pressing near-net forming technology, and two kinds of alloy powder of GH4169 and TC17 are required to be adopted, but when the GH4169 and TC17 alloy powder is combined in a powder state, the mixed powder exists at an interface of the GH4169 and TC17 alloy powder, the component distribution after the mixed powder is difficult to control, and the components, the tissues and the performances at a combining surface cannot be ensured. In addition, the heat treatment systems of the GH4169 alloy and the TC17 alloy are different, and higher requirements are set for the hot isostatic pressing process parameter selection of the whole assembly.
Accordingly, there is a need for improved methods of manufacturing multi-stage rotor assemblies for GH4169 and TC17 alloys of the same or different materials to address the above-described issues.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides the preparation method of the GH4169 and TC17 alloy homogeneous and heterogeneous material multistage rotor assembly, which ensures that the joint surface between multistage rotor parts has good structural uniformity and high overall performance, and the preparation cost is relatively low.
In order to solve the above problems, according to a first aspect of the present invention, there is provided a method of manufacturing a GH4169 and TC17 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk region made of a GH4169 alloy having at least one stage rotor portion and a second disk region made of a TC17 alloy having at least one stage rotor portion, the method comprising the steps of:
Designing a preform for each stage of rotor portion of the rotor assembly;
Preparing a sheath of each stage of the preform, wherein a sheath interface is arranged at the position where each stage of the sheath is connected with the adjacent sheath;
Welding the sheath and the front-stage sheath at the sheath interface from the last-stage sheath, filling alloy powder into the rear-stage sheath in the two-stage sheath to be welded before welding, and compacting by cold pressing, filling alloy powder into the first-stage sheath before welding the first-stage sheath, thereby obtaining a rotor component preform with sequentially connected stages;
performing hot isostatic pressing treatment on the rotor assembly preform at the temperature of 980-1040 ℃ and the pressure of 130-170 MPa for 1.5-3 hours to obtain a rotor assembly blank;
removing the wrap from the rotor assembly blank;
and carrying out heat treatment on the first disc body area and the second disc body area of the rotor assembly blank, wherein the combined area of the first disc body area and the second disc body area and the first disc body area are subjected to heat treatment together, so that a rotor assembly is obtained.
Preferably, the at least one stage rotor portion of the first disk body region is continuously disposed, and the at least one stage rotor portion of the second disk body region is continuously disposed.
Preferably, the first disc area is located at a front stage of the second disc area.
Preferably, the second disc area is located at a front stage of the first disc area.
Preferably, the first disk region includes a two-stage rotor portion and the second disk region includes a one-stage rotor portion.
Preferably, the last stage of the capsule is filled with alloy powder and cold compacted while the first stage of the capsule is filled with alloy powder and cold compacted.
The heat treatment includes solution treatment, wherein the solution treatment of the first tray body region and the bonding region is performed by air cooling after heat preservation for 1 hour to 3 hours at a temperature ranging from 950 ℃ to 980 ℃, and the solution treatment of the second tray body region is performed by air cooling or air cooling after heat preservation for 3 hours to 5 hours at a temperature ranging from 775 ℃ to 835 ℃.
The heat treatment further includes an aging treatment performed after the solution treatment, wherein the aging treatment performed on the first disk body region and the bonding region is air-cooled after maintaining the temperature in the range of 705 ℃ to 735 ℃ for 7 hours to 9 hours and the temperature in the range of 605 ℃ to 635 ℃ for 7 hours to 9 hours, and the aging treatment performed on the second disk body region is air-cooled after maintaining the temperature in the range of 600 ℃ to 695 ℃ for 7 hours to 10 hours.
Preferably, after the heat treatment step, the method further comprises:
Performing flaw detection on the rotor assembly blank; and
And carrying out combined machining and stress relief treatment on the rotor assembly blank.
According to a second aspect of the present invention there is provided a GH4169 and TC17 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk region made of a GH4169 alloy having at least one stage rotor portion and a second disk region made of a TC17 alloy having at least one stage rotor portion, said rotor assembly being prepared using a preparation method as previously described.
According to the invention, the multistage rotor assembly is divided into two alloy areas, the different alloy areas are compacted by a cold pressing method when powder is filled before hot isostatic pressing, and after the hot isostatic pressing, the two different alloy areas and the dissimilar material bonding area are subjected to zonal heat treatment, so that the problems of how to realize bonding of the powder with two components GH4169 and TC17 at an interface and non-uniform heat treatment system of the two materials are effectively solved. Compared with the prior art, the hot isostatic pressing net near forming method of the multistage engine rotor adopted by the invention has the advantages that the rotor prepared by the method can be freely combined in structural form and is not limited by the number of component stages; the final rotor component is formed by hot isostatic pressing once, the uniformity of a joint surface structure is good, the overall performance of the multistage rotor is high, the tensile performance test result of the joint part of the TC17+GH4169 is sigma b not less than 1000MPa, the tensile performance test result of the TC17 alloy is sigma b not less than 1000MPa, the forge piece performance level of the TC17 alloy can be achieved, the tensile performance test result of the GH4169 alloy is sigma b not less than 1300MPa, the forge piece performance level of the GH4169 alloy can be achieved, the lean manufacturing of the multistage rotor component of the same kind and different kinds of materials of the GH4169 and the TC17 alloy is realized, and the service performance of the rotor is improved; in addition, the method adopts cold press molding to the pre-pressed body, so that powder mixing can be avoided, the preparation cost of large welding equipment is reduced, the preparation process flow is shortened, and the preparation difficulty is reduced.
Drawings
The foregoing summary of the invention, as well as the following detailed description of the invention, will be better understood when read in conjunction with the accompanying drawings. It is to be noted that the drawings are merely examples of the claimed invention. In the drawings, like reference numbers indicate identical or similar elements.
FIG. 1 is a schematic illustration of a multi-stage rotor assembly according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of a preform design of the multi-stage rotor assembly shown in FIG. 1;
FIG. 3 is a schematic illustration of a jacket design of the multi-stage rotor assembly shown in FIG. 1;
FIG. 4 is a schematic illustration of the preform preparation of the multi-stage rotor assembly shown in FIG. 1;
Fig. 5 is a schematic view of the multi-stage rotor assembly blank shown in fig. 1.
Reference numerals illustrate:
1: three-stage rotor assembly
1A: first disk area
1B: a second disk body area
1-1: First stage rotor portion
1-2: Second stage rotor portion
1-3: Third stage rotor portion
2-1: First-stage preform
2-2: Second-stage preform
2-3: Third stage preform
3-1: First-stage sheath
3-2: Second-stage sheath
3-3: Third-stage sheath
3-4: Sheath interface
4-1: GH4169 alloy powder
4-2: TC17 alloy powder
5: Reserve amount of
6: Rotor assembly blank
6-1: First-stage blank
6-2: Second grade blank
6-3: Third-stage blank
6-4: Dissimilar material bonding zone
Detailed Description
The detailed features and advantages of the present invention will be readily apparent to those skilled in the art from the following detailed description, claims, and drawings that follow.
Specific examples of components and arrangements are described below for purposes of simplifying the disclosure, and of course, these are merely examples and are not intended to limit the scope of the invention. For example, a first feature described later in this specification may be formed above or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, as well as embodiments in which additional features may be formed between the first and second features, such that no direct contact may be made between the first and second features. In addition, the disclosure may repeat reference numerals and/or letters in the various examples. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, where a first element is described as being coupled or combined with a second element, the description includes embodiments in which the first and second elements are directly coupled or combined with each other, and also includes embodiments in which one or more other intervening elements are added to indirectly couple or combine the first and second elements with each other.
Additionally, it should be appreciated that the positional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the positional or positional relationship shown in the drawings, and merely for convenience in describing the present application and simplifying the description, and such positional terms do not indicate or imply that the apparatus or elements referred to must have a specific orientation or be constructed and operated in a specific orientation, and thus should not be construed as limiting the scope of the present application. Meanwhile, the present application uses specific words to describe embodiments of the present application. The term "inner" and "outer" refers to the inner and outer of the outline of each component, and the terms such as "first" and "second" are used to define the components, only for convenience in distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.
The invention provides a preparation method of a GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly, which comprises a first disk body zone made of GH4169 alloy and a second disk body zone made of TC17 alloy, wherein the first disk body zone is provided with at least one stage of rotor part, and the second disk body zone is provided with at least one stage of rotor part. Preferably, at least one rotor part of the first disc area and the second disc area are continuously arranged, and the first disc area can be arranged at the front stage of the second disc area or at the rear stage of the second disc area.
Firstly, dividing a multi-stage rotor assembly into a plurality of single-stage rotor parts according to structural design and material selection requirements, and designing a hot isostatic pressing prefabricated body of each stage of single-stage rotor part of the rotor assembly according to the process characteristics of near net forming of a hot isostatic pressing process and the processing requirements of a subsequent combined blank, wherein the hot isostatic pressing prefabricated body comprises a preparation scheme and a reserved quantity of the single-stage prefabricated body.
And preparing a sheath of each stage of the prefabricated body according to the structure of each prefabricated body, wherein the sheath structure is basically the same as that of the final rotor assembly, a sheath interface is arranged at the position where each stage of sheath is connected with the adjacent sheath, and the prepared sheath is reserved with the sheath interface.
When the sheath and the filling alloy powder are welded, the sheath and the front sheath are welded at the sheath interface from the last sheath in sequence from back to front, the filling alloy powder is filled into the rear sheath in the two-stage sheath to be welded before each sheath is welded, and the alloy powder compacted by the cold pressing method is integrated, so that powder scattering or powder mixing with the next stage can not occur. The first-stage capsule is filled with alloy powder and compacted by cold pressing before the first-stage capsule is welded, and preferably, two-stage preforms at two ends in the rotor assembly are filled first when the powder is filled, namely, the last-stage capsule is filled with alloy powder and compacted by cold pressing, and the first-stage capsule is filled with alloy powder and compacted by cold pressing. And after welding the sleeve of the adjacent stage, filling corresponding alloy powder into the sleeve of the adjacent stage, after cold pressing and compacting again, welding the sleeve of the next adjacent stage at the interface position, refilling the corresponding alloy powder, and the like, and finally connecting the sleeve with the prefabricated body at the other end of the rotor assembly through welding, so as to finish powder filling and cold pressing molding of the whole prefabricated body, and obtaining the rotor assembly prefabricated body with all stages connected in sequence.
And (3) carrying out hot isostatic pressing treatment on the cold-pressed and formed rotor assembly preform at the temperature of 980-1040 ℃ and the pressure of 130-170 MPa for 1.5-3 hours, ensuring plastic deformation and diffusion creep of the powder, and finally forming a rotor assembly blank.
And removing the sheath from the rotor assembly blank to finish the preparation of the GH4169 and TC17 alloy homogeneous and heterogeneous material multistage rotor assembly blank.
Aiming at the problem that the GH4169 and TC17 alloy heat treatment systems are different, the two alloy areas of the multi-stage rotor assembly are required to be subjected to partition heat treatment to obtain the required structure, namely, the first disc area and the second disc area of the rotor assembly blank are subjected to heat treatment respectively, and the dissimilar material combination area of the first disc area and the second disc area is subjected to heat treatment together with the first disc area adopting GH4169 alloy.
Further, the heat treatment includes a solution treatment, and in order to reduce the influence of heat radiation due to an excessive temperature difference, the solution treatment time and aging treatment time of the two materials may be kept uniform or close, and therefore, the solution treatment performed on the first disk region and the dissimilar material joining region using the GH4169 alloy may preferably be a solution treatment in which air cooling is performed after heat-maintaining for 1 hour to 3 hours at a temperature ranging from 950 ℃ to 980 ℃, the aging treatment may preferably be a solution treatment in which air cooling is performed after heat-maintaining for 7 hours to 9 hours at a temperature ranging from 705 ℃ to 735 ℃, followed by an aging treatment in which air cooling is performed after heat-maintaining for 7 hours to 9 hours at a temperature ranging from 605 ℃ to 635 ℃, and the solution treatment performed on the second disk region using the TC17 alloy may preferably be a solution treatment in which air cooling or air cooling is performed after heat-maintaining for 3 hours to 5 hours at a temperature ranging from 775 ℃ to 835 ℃, and the aging treatment may preferably be a aging treatment in which air cooling is performed after heat-maintaining for 7 hours to 10 hours at a temperature ranging from 600 ℃ to 695 ℃.
Preferably, the rotor assembly blank may be inspected for internal quality, preferably by water immersion inspection.
Preferably, the rotor assembly blank is finally subjected to a combination of machining and stress relief.
As shown in fig. 1, taking a three-stage rotor assembly 1 as an example, which includes a first disk region 1a and a second disk region 1b, the first disk region 1a includes a second-stage rotor portion 1-2 and a third-stage rotor portion 1-3 made of GH4169 alloy, and the second disk region 1b includes a first-stage rotor portion 1-1 made of TC17 alloy, the three-stage rotor assembly 1 is prepared by hot isostatic pressing near net forming, and includes the steps of:
Step one: as shown in fig. 2, the rotor assembly is divided into three parts, i.e., three-stage single-stage rotor parts 1-1, 1-2, 1-3, and the preforms of each single-stage rotor part, i.e., the first-stage preform 2-1, the second-stage preform 2-2, and the third-stage preform 2-3, are designed in consideration of the reserved amount 5 of the preforms 2-1, 2-2, 2-3;
Step two: as shown in fig. 3, the sheaths 3-1, 3-2, 3-3 of the respective stage preforms 2-1, 2-2, 2-3 of the three stage rotor are designed and manufactured, and the sheath interfaces 3-4 are reserved at the interface positions with the adjacent sheaths;
Step three: as shown in fig. 4, firstly, filling GH4169 alloy powder 4-1 into a third-stage sheath 3-3, simultaneously filling TC17 alloy powder 4-2 into a first-stage sheath 3-1, compacting by a cold pressing method, welding the third-stage sheath 3-3 and a second-stage sheath 3-2 at a sheath interface 3-4 position, filling TC17 alloy powder 4-2 into the second-stage sheath 3-2 after welding, and welding the second-stage sheath 3-2 and the first-stage sheath 3-1 at the sheath interface 3-4 after cold pressing compaction again to obtain a three-stage rotor assembly preform;
Step four: performing hot isostatic pressing treatment on the combined three-stage rotor assembly preform, wherein the hot isostatic pressing process parameters are as follows: the temperature is 990 ℃ to 1020 ℃, the pressure is 140MPa to 150MPa, and the time is 2 hours to 2.5 hours, so that a three-stage rotor assembly blank 6 is obtained, as shown in figure 5;
Step five: subjecting the tertiary rotor assembly blank 6 to a combination process or chemical treatment to remove the sheath;
Step six: heat treating the first stage blank 6-1 while heat treating the second stage blank 6-2, the third stage blank 6-3 and the dissimilar material bonding zone 6-4, comprising: firstly, heating a first-stage blank 6-1 to a temperature range of 785 ℃ to 815 ℃ for heat preservation for 4 hours, then performing air cooling, and simultaneously, heating a second-stage blank 6-2, a third-stage blank 6-3 and a dissimilar material bonding zone 6-4 to a temperature range of 970 ℃ to 980 ℃ for heat preservation for 1 hour to 2 hours, and then performing air cooling to complete solution treatment; then heating the first-stage blank 6-1 to a temperature range of 620-650 ℃ for heat preservation for 9 hours, then performing air cooling, and simultaneously heating the second-stage blank 6-2, the third-stage blank 6-3 and the dissimilar material bonding zone 6-4 to a temperature range of 720-730 ℃ for heat preservation for 7-9 hours, then performing air cooling after heat preservation for 7-9 hours in a temperature range of 620-630 ℃, so as to finish ageing treatment;
step eight: carrying out water immersion flaw detection on the three-stage rotor assembly blank 6;
Step nine: the three-stage rotor assembly blank 6 is subjected to a combination process, in which a stress relief treatment is performed.
According to a second aspect of the present invention there is provided a GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly 1 prepared by a method as hereinbefore described.
The GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly can be favorably applied to engines with high performance and light weight requirements such as aeroengines.
The terms and expressions which have been employed herein are used as terms of description and not of limitation. The use of these terms and expressions is not meant to exclude any equivalents of the features shown and described (or portions thereof), and it is recognized that various modifications are possible and are intended to be included within the scope of the claims. Other modifications, variations, and alternatives, such as replacement of components of different specifications, are also possible. Accordingly, the claims should be looked to in order to cover all such equivalents.
Also, it should be noted that while the present application has been described with reference to the particular embodiments presently, it will be appreciated by those skilled in the art that the above embodiments are provided for illustration only and that various equivalent changes or substitutions may be made without departing from the spirit of the application, and therefore, the changes and modifications to the above embodiments shall fall within the scope of the claims of the present application as long as they are within the true spirit of the application.
Claims (10)
1. A method of making a GH4169 and TC17 material multistage rotor assembly having a first disk region made of a GH4169 alloy having at least one stage rotor portion and a second disk region made of a TC17 alloy having at least one stage rotor portion, said method comprising the steps of:
designing a reserved amount of a single-stage preform of each stage rotor part of the rotor assembly;
Preparing a sheath of each stage of the preform, wherein a sheath interface is arranged at the position where each stage of the sheath is connected with the adjacent sheath;
Welding the sheath and the front-stage sheath at the sheath interface from the last-stage sheath, filling alloy powder into the rear-stage sheath in the two-stage sheath to be welded before welding, and compacting by cold pressing, filling alloy powder into the first-stage sheath before welding the first-stage sheath, thereby obtaining a rotor component preform with sequentially connected stages;
performing hot isostatic pressing treatment on the rotor assembly preform at the temperature of 980-1040 ℃ and the pressure of 130-170 MPa for 1.5-3 hours to obtain a rotor assembly blank;
removing the wrap from the rotor assembly blank;
and carrying out heat treatment on the first disc body area and the second disc body area of the rotor assembly blank, wherein the combined area of the first disc body area and the second disc body area and the first disc body area are subjected to heat treatment together, so that a rotor assembly is obtained.
2. The method according to claim 1, wherein,
The at least one stage rotor portion of the first disk body region is continuously disposed, and the at least one stage rotor portion of the second disk body region is continuously disposed.
3. The method according to claim 2, wherein,
The first disc area is located at a front stage of the second disc area.
4. The method according to claim 2, wherein,
The second disc body area is positioned at the front stage of the first disc body area.
5. The method of manufacturing according to claim 1, wherein the first disk region comprises a two-stage rotor portion and the second disk region comprises a one-stage rotor portion.
6. The method according to claim 1, wherein,
And filling alloy powder into the sheath at the last stage and cold-pressing the sheath at the same time, and filling alloy powder into the sheath at the first stage and cold-pressing the sheath at the same time.
7. The method according to claim 1, wherein,
The heat treatment includes solution treatment, wherein the solution treatment of the first tray body region and the bonding region is performed by air cooling after heat preservation for 1 hour to 3 hours at a temperature ranging from 950 ℃ to 980 ℃, and the solution treatment of the second tray body region is performed by air cooling or air cooling after heat preservation for 3 hours to 5 hours at a temperature ranging from 775 ℃ to 835 ℃.
8. The method according to claim 7, wherein,
The heat treatment further includes an aging treatment performed after the solution treatment, wherein the aging treatment performed on the first disk body region and the bonding region is air-cooled after maintaining the temperature in the range of 705 ℃ to 735 ℃ for 7 hours to 9 hours and the temperature in the range of 605 ℃ to 635 ℃ for 7 hours to 9 hours, and the aging treatment performed on the second disk body region is air-cooled after maintaining the temperature in the range of 600 ℃ to 695 ℃ for 7 hours to 10 hours.
9. The method according to claim 1, further comprising, after the heat treatment step:
Performing flaw detection on the rotor assembly blank; and
And carrying out combined machining and stress relief treatment on the rotor assembly blank.
10. A GH4169 and TC17 material multi-stage rotor assembly having a first disk region made of a GH4169 alloy having at least one stage rotor portion and a second disk region made of a TC17 alloy having at least one stage rotor portion, said rotor assembly being prepared using the preparation method according to any one of claims 1-9.
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| US20080124210A1 (en) * | 2006-11-28 | 2008-05-29 | Peter Wayte | Rotary assembly components and methods of fabricating such components |
| GB2459653A (en) * | 2008-04-29 | 2009-11-04 | Rolls Royce Plc | Manufacture of an article by hot isostatic pressing |
| GB0913924D0 (en) * | 2009-08-11 | 2009-09-16 | Rolls Royce Plc | Developments in or relating to drum rotors |
| US10036254B2 (en) * | 2015-11-12 | 2018-07-31 | Honeywell International Inc. | Dual alloy bladed rotors suitable for usage in gas turbine engines and methods for the manufacture thereof |
| US10385433B2 (en) * | 2016-03-16 | 2019-08-20 | Honeywell International Inc. | Methods for processing bonded dual alloy rotors including differential heat treatment processes |
| US10718041B2 (en) * | 2017-06-26 | 2020-07-21 | Raytheon Technologies Corporation | Solid-state welding of coarse grain powder metallurgy nickel-based superalloys |
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| US4270256A (en) * | 1979-06-06 | 1981-06-02 | General Motors Corporation | Manufacture of composite turbine rotors |
| CN103447759A (en) * | 2013-08-09 | 2013-12-18 | 钢铁研究总院 | Method for using hot isostatic pressing to produce double-alloy blisk |
| EP3187283A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
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