CN115070043A - GH4065A and GH4169 same-material and different-material multistage rotor assembly and preparation method thereof - Google Patents
GH4065A and GH4169 same-material and different-material multistage rotor assembly and preparation method thereof Download PDFInfo
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- CN115070043A CN115070043A CN202110261095.2A CN202110261095A CN115070043A CN 115070043 A CN115070043 A CN 115070043A CN 202110261095 A CN202110261095 A CN 202110261095A CN 115070043 A CN115070043 A CN 115070043A
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- 239000000463 material Substances 0.000 title claims abstract description 32
- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 60
- 239000000956 alloy Substances 0.000 claims abstract description 60
- 239000000843 powder Substances 0.000 claims abstract description 34
- 238000000034 method Methods 0.000 claims abstract description 29
- 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 23
- 238000003825 pressing Methods 0.000 claims abstract description 18
- 230000032683 aging Effects 0.000 claims abstract description 14
- 238000004519 manufacturing process Methods 0.000 claims abstract description 12
- 238000001816 cooling Methods 0.000 claims description 19
- 210000000746 body region Anatomy 0.000 claims description 16
- 238000011049 filling Methods 0.000 claims description 12
- 238000003754 machining Methods 0.000 claims description 11
- 238000004321 preservation Methods 0.000 claims description 10
- 238000005056 compaction Methods 0.000 claims description 7
- 230000035882 stress Effects 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 2
- 239000011541 reaction mixture Substances 0.000 claims 1
- 238000002156 mixing Methods 0.000 abstract description 5
- 238000000465 moulding Methods 0.000 abstract description 3
- 238000004904 shortening Methods 0.000 abstract description 2
- 239000006104 solid solution Substances 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000005242 forging Methods 0.000 description 3
- 238000007689 inspection 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
- 230000014509 gene expression Effects 0.000 description 2
- 238000007654 immersion Methods 0.000 description 2
- 238000005304 joining 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
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000010275 isothermal forging Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 238000012545 processing 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
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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
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
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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
- 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
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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
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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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
- 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)
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- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a GH40 4065A and GH4169 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, the different alloy areas are compacted by a cold pressing method when powder is filled in the different alloy areas before hot isostatic pressing, and after the hot isostatic pressing, the two different alloy areas and a heterogeneous material combination area are subjected to partitioned solid solution heat treatment and aging treatment, so that the prepared rotor assembly can be freely combined in the 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 multistage rotor is high, the lean manufacturing of the GH4065A and GH4169 alloy multistage rotor assembly made of the same or different materials is realized, and the use performance of the rotor is improved; in addition, the method adopts cold press molding to the pre-pressing body, thereby not only avoiding powder mixing, but also reducing the preparation cost of large-scale welding equipment, shortening the preparation process flow and reducing the preparation difficulty.
Description
Technical Field
The invention relates to a manufacturing technology of an aircraft engine rotor, in particular to a dissimilar alloy multistage rotor assembly and a preparation method thereof.
Background
The rotor of the aircraft engine operates at high temperature, high pressure and high rotating speed, and parts bear thermal load, pneumatic load, centrifugal load and the like, so that higher requirements are put forward for the comprehensive performance of the rotor assembly. On one hand, the service temperature of the disc part is continuously increased along with the increase of the thrust-weight ratio of the engine, so that the powdered high-temperature alloy GH4065A alloy and the low-cost GH4169 alloy are gradually applied to rotary parts of an aircraft engine disc, 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 aero-engine rotor is developed to be light and integrated, and the rotor made of different material combinations also causes the problem of integrated connection.
In the aspect of multi-stage rotor integration, the most widely used process at present is to realize the connection of the multi-stage rotor assembly by welding. In the selection of the welding method, as the difference of the GH4169 and the GH4065A in material composition and structure performance is large, the connection cannot be directly carried out by adopting the welding process, and the bolt connection is adopted for the connection mode between the titanium alloy and the high-temperature alloy rotor assembly at present. However, the bolted connection increases the weight of the rotor assembly and reduces the reliability of the connection, thereby increasing the overall weight of the engine and reducing engine efficiency.
In recent years, hot isostatic pressing near net shape technology has matured, and the technology combines hot isostatic pressing densification and near net shape process control to provide a hot blank with required shape, size and structure for subsequent machining, isothermal forging or heat treatment.
The hot isostatic pressing near-net-shape process has the following advantages over the welding process of a typical rotor assembly:
1) uniform structure and high mechanical property: the hot isostatic pressing near-net forming part has high density and uniform components, and no macroscopic component segregation exists in the structure, so the comprehensive mechanical property is excellent and can reach the level of a forging piece, and is higher than the mechanical property of a welding joint.
2) And (3) reducing machining procedures: compared with the machining by adopting a forged piece, the hot isostatic pressing near-net forming part has a relatively simple process, only performs combined machining in the assembly, and reduces the machining procedures of the rotor assembly before welding.
3) The equipment is simple: the hot isostatic pressing near-net forming technology mainly utilizes hot isostatic pressing equipment, avoids the use of large welding equipment, particularly large inertia friction welding equipment, and solves the problem of resource shortage of the welding equipment.
4) The method is applicable to various structures: various structures, particularly complex structures, can be prepared by hot isostatic pressing near net shape forming processes.
5) The manufacturing cost is low: the hot isostatic pressing near-net-shape part has high material utilization rate, relatively simple process and short process period, and reduces the manufacturing cost.
The hot isostatic pressing near-net forming technology is adopted to prepare the GH4065A and GH4169 alloy multi-stage rotor assembly made of the same or different materials, two kinds of alloy powder of GH40 4065A and GH4169 are adopted, but when the powder is combined in a powder state, the powder mixing and component distribution after the powder mixing are difficult to control at an interface of the GH4065A and the GH4169 powder, and the components, the structure and the performance at the joint surface cannot be guaranteed. In addition, the heat treatment schedules of the GH4065A and GH4169 alloys are different, and higher requirements are provided for the selection of hot isostatic pressing process parameters of the whole assembly.
Accordingly, there is a need for improved methods of making multi-stage rotor assemblies of the same and different materials of GH4065A and GH4169 alloys to address the above-mentioned problems.
Disclosure of Invention
The invention aims to solve the technical problem that aiming at the defects of the prior art, the invention provides the preparation method of the GH4065A and GH4169 alloy multi-stage rotor assembly made of the same or different materials, so that the uniformity of joint surface structures among multi-stage rotor parts is good, the overall performance is high, 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 GH4065A and GH4169 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region made of a GH40 4065A alloy having at least one stage rotor portion and a second disk body region made of a GH4169 alloy having at least one stage rotor portion, the method comprising the steps of:
designing a preform for each rotor section of the rotor assembly;
preparing a sheath of each level of the prefabricated body, wherein a sheath interface is arranged at the position, connected with an adjacent sheath, of each level of the sheath;
welding the sheath and a preceding sheath at a sheath interface from the last sheath, filling alloy powder into a rear sheath of two to-be-welded sheaths before welding, performing cold pressing compaction, and filling alloy powder into a first sheath before welding the first sheath, and performing cold pressing compaction, so as to obtain a rotor assembly preform with each stage connected in sequence;
carrying out hot isostatic pressing treatment on the rotor assembly preform at the temperature of 1160-;
removing the sheath 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 combination 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 rotor part of the first disk body area is arranged continuously, and the at least one rotor part of the second disk body area is arranged continuously.
Preferably, the first disk area is located in a previous stage of the second disk area.
Preferably, the second disk region is located at a preceding stage of the first disk region.
Preferably, the first disk body section includes a two-stage rotor portion, and the second disk body section includes a one-stage rotor portion.
Preferably, the final stage of the sheath is filled with alloy powder and cold compacted, and the first stage of the sheath is filled with alloy powder and cold compacted.
Preferably, the heat treatment includes solution treatment, and the solution treatment performed on the first disk body region and the bonding region is air cooling or furnace cooling after heat preservation for 1 hour to 3 hours at a temperature of 1040 ℃ to 1080 ℃, and the solution treatment performed on the second disk body region is air cooling after heat preservation for 1 hour to 3 hours at a temperature of 950 ℃ to 980 ℃.
Preferably, the heat treatment further comprises an aging treatment, the aging treatment is performed after the solution treatment, the aging treatment performed on the first tray body area and the bonding area is performed by air cooling after heat preservation for 6 hours to 12 hours at a temperature ranging from 740 ℃ to 770 ℃, and the aging treatment performed on the second tray body area is performed by air cooling after heat preservation for 7 hours to 9 hours at a temperature ranging from 705 ℃ to 735 ℃ and heat preservation for 7 hours to 9 hours at a temperature ranging from 605 ℃ to 635 ℃.
Preferably, the method further comprises the following steps after the heat treatment step:
carrying out 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 GH4065A and GH4169 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of GH40 4065A alloy having at least one stage of rotor portion and a second disk body region of GH4169 alloy having at least one stage of rotor portion, prepared by a method as hereinbefore 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 being filled with powder before hot isostatic pressing, and the two different alloy areas and the dissimilar material combining area are subjected to zoned heat treatment after the hot isostatic pressing, so that the problems of how to combine powder of GH4065A and GH4169 at the interface and non-uniformity of heat treatment regimes of the two materials are effectively solved. Compared with the prior art, the hot isostatic pressing net-approximate-forming method of the multistage engine rotor is adopted, and the prepared rotor can be freely combined in the structural form and is not limited by the number of stages of components; the final rotor assembly is formed by one-time hot isostatic pressing, the uniformity of a joint surface structure is good, the overall performance of the multi-stage rotor is high, the result of a tensile performance test on a joint of GH4169+ GH4065A is that sigma b is more than or equal to 1000MPa, the result of the tensile performance test on GH4169 alloy is that sigma b is more than or equal to 1000MPa, the performance level of a forging piece of GH4169 alloy can be reached, the result of the tensile performance test on GH4065A alloy is that sigma b is more than or equal to 1300MPa, the performance level of the forging piece of GH4065A alloy can be reached, the lean manufacturing of the multi-stage rotor assembly made of the same-class and different-class materials of GH40 4065A and GH4169 alloy is realized, and the use performance of the rotor is improved; in addition, the method adopts cold press molding to the pre-pressing body, thereby not only avoiding powder mixing, but also reducing the preparation cost of large-scale welding equipment, shortening the preparation process flow and reducing the preparation difficulty.
Drawings
The foregoing summary, as well as the following detailed description of the invention, will be better understood when read in conjunction with the appended drawings. It is to be noted that the appended drawings are intended as examples of the claimed invention. In the drawings, like reference characters designate the same or similar elements.
FIG. 1 is a schematic view of a multi-stage rotor assembly according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of a preform design for the multi-stage rotor assembly shown in FIG. 1;
FIG. 3 is a jacket design schematic of the multi-stage rotor assembly of FIG. 1;
FIG. 4 is a schematic illustration of 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 of fig. 1.
The reference numbers illustrate:
1: three stage rotor assembly
1 a: first disk body area
1 b: second disk body area
1-1: first stage rotor section
1-2: second stage rotor section
1-3: third stage rotor section
2-1: first stage preform
2-2: second-stage preform
2-3: third-stage preform
3-1: first-level jacket
3-2: second-level jacket
3-3: third-level sheath
3-4: sheath interface
4-1: GH4065A alloy powder
4-2: GH4169 alloy powder
5: amount of reserve
6: rotor assembly blank
6-1: first stage blank
6-2: second stage blank
6-3: third grade blank
6-4: dissimilar material binding zone
Detailed Description
The detailed features and advantages of the present invention are described in detail in the detailed description which follows, and will be sufficient for anyone skilled in the art to understand the technical content of the present invention and to implement the present invention, and the related objects and advantages of the present invention will be easily understood by those skilled in the art from the description, claims and drawings disclosed in the present specification.
Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. 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, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
Further, it is to be understood that the positional or orientational relationships indicated by the terms "front, rear, upper, lower, left, right", "transverse, vertical, horizontal" and "top, bottom" and the like are generally based on the positional or orientational relationships illustrated in the drawings and are provided for convenience in describing the invention and for simplicity in description, and that these terms are not intended to indicate and imply that the referenced devices or elements must be in a particular orientation or be constructed and operated in a particular orientation without departing from the scope of the invention. Also, this application uses specific language to describe embodiments of the application. The terms "inside" and "outside" refer to the inner and outer parts relative to the outline of each part itself, and the terms "first" and "second" are used to define the parts, and are used only for the convenience of distinguishing the corresponding parts, and the terms do not have any special meaning unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
The invention provides a preparation method of a GH40 4065A and GH4169 same and different material multi-stage rotor assembly, which comprises a first disk body area made of GH4065A alloy and a second disk body area made of GH4169 alloy, wherein the first disk body area is provided with at least one stage of rotor part, and the second disk body area is provided with at least one stage of rotor part. Preferably, at least one rotor portion of the first disk area and the second disk area is continuously arranged, and the first disk area can be arranged at the front stage of the second disk area and can also be arranged at the rear stage of the second disk area.
Firstly, dividing the multi-stage rotor assembly into a plurality of single-stage rotor parts according to the structural design and material selection requirements, and designing a hot isostatic pressing preform of each stage of single-stage rotor part of the rotor assembly according to the process characteristics of the hot isostatic pressing process near-net-shape forming and the processing requirements of a subsequent combined blank, wherein the hot isostatic pressing preform comprises a preparation scheme and the reservation of the single-stage preform.
Preparing a sheath of each stage of preform according to the structure of each preform, wherein the sheath structure is basically the same as that of the final rotor assembly, a sheath interface is arranged at the position, connected with the adjacent sheath, of each stage of sheath, and the sheath interface is reserved in the prepared sheath.
The welding of the jackets and the filling of the alloy powder can adopt a sequence from back to front, the welding of the jackets and the preceding-stage jackets at the jacket interface is started from the last-stage jacket, the alloy powder is filled in the later-stage jacket of the two-stage jackets to be welded before the welding of each-stage jacket and is compacted by cold pressing, and the alloy powder compacted by the cold pressing method is integrated, so that the powder scattering or the powder mixing with the next stage cannot occur. And filling alloy powder into the first-stage sheath before welding the first-stage sheath, and performing cold pressing compaction on the first-stage sheath, preferably, filling two stages of prefabricated bodies at two ends in the rotor assembly when filling the powder, namely filling the alloy powder into the last-stage sheath, performing cold pressing compaction on the alloy powder, and performing cold pressing compaction on the first-stage sheath. And finally, connecting the sheath with the preform at the other end of the rotor assembly by welding to complete powder filling and cold press molding of the whole preform, and obtaining the rotor assembly preform with each stage of sequential connection.
And carrying out hot isostatic pressing treatment on the rotor assembly preform subjected to cold pressing forming at the temperature of 1160-.
And (4) removing the sleeve from the rotor assembly blank to finish the preparation of the GH4065A and GH4169 alloy homogeneous and heterogeneous material multistage rotor assembly blank.
In response to the different heat treatment regimes of the two alloys GH4065A and GH4169, it is necessary to heat treat the two alloy regions of the multi-stage rotor assembly zoned to achieve the desired texture, i.e. heat treat the first and second disk regions of the rotor assembly blank separately, heat treat the dissimilar material joining regions of the first and second disk regions together with the first disk region 1-1 of the GH40 4065A alloy.
Further, the heat treatment includes solution treatment, and in order to reduce the influence of heat radiation due to an excessive temperature difference, the solution treatment time and the aging treatment time of the two materials can be kept uniform or close to each other, and therefore, the solution treatment of the first plate body region and the dissimilar material bonding region using the GH4065A alloy can be preferably performed by air cooling or furnace cooling after heating to a temperature in the range of 1040 ℃ to 1080 ℃ for 1 hour to 3 hours, the aging treatment can be preferably performed by air cooling after heating to a temperature in the range of 740 ℃ to 770 ℃ for 6 hours to 12 hours, the solution treatment of the second plate body region using the GH4169 alloy can be preferably performed by air cooling after heating to a temperature in the range of 950 ℃ to 980 ℃ for 1 hour to 3 hours, and the aging treatment can be preferably performed by heating to a temperature in the range of 705 ℃ to 980 ℃ for 7 hours to 9 hours, Keeping the temperature in the range of 605-635 ℃ for 7-9 hours, and then carrying out air cooling aging treatment.
Preferably, the rotor assembly blank is inspected for internal quality by inspection, and preferably, the inspection is performed by water immersion inspection.
Preferably, the rotor assembly blank is finally subjected to a combined machining and stress relief treatment.
As shown in fig. 1, taking a three-stage rotor assembly 1 as an example, the three-stage rotor assembly comprises a first disk body region 1a and a second disk body region 1b, the first disk body region 1a comprises a second-stage rotor part 1-2 and a third-stage rotor part 1-3 which are selected from GH4065A alloy, the second disk body region 1b comprises a first-stage rotor part 1-1 which is selected from GH4169 alloy, and the three-stage rotor assembly 1 is prepared by hot isostatic pressing near-net forming and comprises the following steps:
the method comprises the following steps: as shown in fig. 2, the rotor assembly is divided into three sections, i.e., three stages of single-stage rotor sections 1-1, 1-2, 1-3, and the preforms of the respective single-stage rotor sections, 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, jackets 3-1, 3-2, 3-3 of each stage of prefabricated bodies 2-1, 2-2, 2-3 of the three-stage rotor are designed and manufactured, and jacket interfaces 3-4 are reserved at the interface positions of adjacent jackets;
step three: as shown in fig. 4, firstly, the third-stage jacket 3-3 is filled with GH4065A alloy powder 4-1, and the first-stage jacket 3-1 is filled with GH4169 alloy powder 4-2, the third-stage jacket 3-3 and the second-stage jacket 3-2 are welded at the jacket interface 3-4 by a cold pressing method, and then the GH4169 alloy powder 4-2 is filled into the second-stage jacket 3-2 after welding, and the second-stage jacket 3-2 and the first-stage jacket 3-1 are welded at the jacket interface 3-4 after cold pressing and compacting again, so as to obtain a three-stage rotor assembly preform;
step four: carrying out hot isostatic pressing treatment on the combined three-stage rotor assembly preform, wherein the hot isostatic pressing technological parameters are as follows: obtaining a third-level rotor assembly blank 6 at 1170-1190 ℃, 145-155MPa and 1.5-2h, as shown in FIG. 5;
step five: performing combined machining or chemical treatment on the three-stage rotor assembly blank 6 to remove the sheath;
step six: heat treating the first stage blank 6-1 while simultaneously heat treating the second stage blank 6-2, the third stage blank 6-3 and the dissimilar material joining zone 6-4, comprising: firstly, heating a first-stage blank 6-1 to a temperature range of 960 ℃ to 970 ℃, preserving heat for 1 hour to 2 hours, then carrying out air cooling, meanwhile, heating a second-stage blank 6-2, a third-stage blank 6-3 and a dissimilar material combination area 6-4 to a temperature range of 1040 ℃ to 1080 ℃, preserving heat for 1.5 hours, then carrying out air cooling, and completing solution treatment; then heating the first-stage blank 6-1 to a temperature range of 720-730 ℃, preserving heat for 7-9 hours, then preserving heat for 7-9 hours at a temperature range of 620-630 ℃, and then carrying out air cooling, meanwhile, heating the second-stage blank 6-2, the third-stage blank 6-3 and the dissimilar material combining area 6-4 to a temperature range of 750-770 ℃, preserving heat for 6-12 hours, and carrying out air cooling to finish aging treatment;
step eight: carrying out water immersion flaw detection on the third-stage rotor assembly blank 6;
step nine: and (4) carrying out combined machining on the three-stage rotor assembly blank 6, and carrying out stress relief treatment in the machining process.
According to a second aspect of the present invention, there is provided a multi-stage rotor assembly 1 of the same or different materials as GH4065A and GH4169, prepared by the method of preparation as hereinbefore described.
The GH4065A and GH4169 homogeneous and heterogeneous material multistage rotor assembly can be advantageously applied to engines with high-performance and light-weight requirements such as aircraft engines.
The terms and expressions which have been employed herein are used as terms of description and not of limitation. The use of such terms and expressions is not intended to exclude any equivalents of the features shown and described (or portions thereof), and it is recognized that various modifications may be made within the scope of the claims. Other modifications, variations, and alternatives, such as the replacement of components of different specifications, may also exist. Accordingly, the claims should be looked to in order to cover all such equivalents.
Also, it should be noted that although the present invention has been described with reference to the current specific embodiments, it should be understood by those skilled in the art that the above embodiments are merely illustrative of the present invention, and various equivalent changes or substitutions may be made without departing from the spirit of the present invention, and therefore, it is intended that all changes and modifications to the above embodiments be included within the scope of the claims of the present application.
Claims (10)
1. A method of making a GH4065A and GH4169 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of GH4065A alloy having at least one rotor portion and a second disk body region of GH4169 alloy having at least one rotor portion, the method comprising the steps of:
designing a preform for each rotor section of the rotor assembly;
preparing a sheath of each level of the prefabricated body, wherein a sheath interface is arranged at the position, connected with an adjacent sheath, of each level of the sheath;
welding the sheath and a preceding sheath at a sheath interface from the last sheath, filling alloy powder into a rear sheath of two to-be-welded sheaths before welding, performing cold pressing compaction, and filling alloy powder into a first sheath before welding the first sheath, and performing cold pressing compaction, so as to obtain a rotor assembly preform with each stage connected in sequence;
carrying out hot isostatic pressing treatment on the rotor assembly preform at the temperature of 1160-;
removing the sheath 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 combination 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. A method of making a rotor assembly as claimed in claim 1,
the rotor part of the first disk body is continuously arranged, and the rotor part of the second disk body is continuously arranged.
3. A method of manufacturing as defined in claim 2,
the first disk area is located at a preceding stage of the second disk area.
4. A method of manufacturing as claimed in claim 2,
the second disk body area is positioned at the preceding stage of the first disk body area.
5. A method of making as set forth in claim 1 wherein said first disk section includes a two-stage rotor portion and said second disk section includes a one-stage rotor portion.
6. A method according to claim 1, wherein the reaction mixture is heated,
and filling alloy powder into the sheath at the last stage and performing cold pressing, and simultaneously filling alloy powder into the sheath at the first stage and performing cold pressing and compacting.
7. A method of manufacturing as defined in claim 1,
the heat treatment comprises solution treatment, the first disc body area and the solution treatment carried out in the combination area are subjected to air cooling or furnace cooling after heat preservation for 1 hour to 3 hours at the temperature of 1040 ℃ to 1080 ℃, and the solution treatment carried out in the second disc body area is subjected to air cooling after heat preservation for 1 hour to 3 hours at the temperature of 950 ℃ to 980 ℃.
8. A method according to claim 7, wherein the step of preparing the composition,
the heat treatment also comprises aging treatment, the aging treatment is carried out after the solution treatment, the aging treatment carried out on the first disc body area and the combination area is carried out after heat preservation for 6 hours to 12 hours at the temperature of 740 ℃ to 770 ℃, and then air cooling is carried out, meanwhile, the aging treatment carried out on the second disc body area is carried out after heat preservation for 7 hours to 9 hours at the temperature of 705 ℃ to 735 ℃, and heat preservation for 7 hours to 9 hours at the temperature of 605 ℃ to 635 ℃, and then air cooling is carried out.
9. The method of claim 1, further comprising, after the heat treating step:
carrying out flaw detection on the rotor assembly blank; and
and carrying out combined machining and stress relief treatment on the rotor assembly blank.
10. A GH4065A and GH4169 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of GH4065A alloy having at least one stage rotor portion and a second disk body region of GH4169 alloy having at least one stage rotor portion, prepared by the method of preparation of claims 1-9.
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Cited By (1)
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| CN117206527A (en) * | 2023-08-14 | 2023-12-12 | 西安欧中材料科技有限公司 | Preparation method and application of high-temperature alloy ring piece with short process and high material utilization rate |
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