CN115070041A - GH4169 and TC17 same-material and different-material multistage rotor assembly and preparation method thereof - Google Patents
GH4169 and TC17 same-material and different-material multistage rotor assembly and preparation method thereof Download PDFInfo
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- CN115070041A CN115070041A CN202110261044.XA CN202110261044A CN115070041A CN 115070041 A CN115070041 A CN 115070041A CN 202110261044 A CN202110261044 A CN 202110261044A CN 115070041 A CN115070041 A CN 115070041A
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- 239000000463 material Substances 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title claims abstract description 17
- 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 35
- 238000000034 method Methods 0.000 claims abstract description 32
- 238000001513 hot isostatic pressing Methods 0.000 claims abstract description 28
- 238000003466 welding Methods 0.000 claims abstract description 27
- 238000010438 heat treatment Methods 0.000 claims abstract description 23
- 238000003825 pressing Methods 0.000 claims abstract description 19
- 230000032683 aging Effects 0.000 claims abstract description 15
- 238000004519 manufacturing process Methods 0.000 claims abstract description 11
- 238000001816 cooling Methods 0.000 claims description 18
- 238000011049 filling Methods 0.000 claims description 18
- 210000000746 body region Anatomy 0.000 claims description 12
- 238000003754 machining Methods 0.000 claims description 11
- 238000004321 preservation Methods 0.000 claims description 8
- 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 2
- 238000002156 mixing Methods 0.000 abstract description 3
- 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
- 238000005304 joining 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
- 239000011812 mixed powder Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 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
- 238000009792 diffusion process 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
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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
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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
-
- 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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Abstract
The invention provides a GH4169 and TC17 same-material and dissimilar-material multi-stage rotor assembly and a hot isostatic pressing near-net-shape forming preparation method thereof, wherein the multi-stage 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 dissimilar-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 GH4169 and TC17 alloy same-kind and dissimilar-kind material multistage rotor assembly 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 provided for the comprehensive performance of the rotor assembly. On one hand, as the thrust-weight ratio of the engine is increased, the service temperature of the disc part is also continuously increased, so that the powder high-temperature alloy GH4169 alloy and the low-cost TC17 alloy are gradually applied to aeroengine disc rotating parts, 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 applied 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 TC17 and the GH4169 have great differences in material composition and structure performance, the connection cannot be directly carried out by adopting the welding process, and the connection mode between the titanium alloy rotor assembly and the high-temperature alloy rotor assembly adopts a bolt connection 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-shape forming part has high density and uniform components, and no macroscopic component segregation exists in the structure, so that the comprehensive mechanical property is excellent and can reach the level of a forge piece, and the comprehensive mechanical property is higher than that of a welding joint.
2) And (3) reducing machining procedures: compared with the method of machining by adopting forgings, the hot isostatic pressing near-net-shape forming part has the advantages that the technological process is relatively simple, only the assembly is subjected to combined machining, and 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 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 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 GH4169 and TC17 alloy same-material and dissimilar-material multistage rotor assembly, two kinds of alloy powder of GH4169 and TC17 are needed, but when the powder is combined in a powder state, the components of the mixed powder of the GH4169 and the TC17 exist at an interface, the component distribution after the mixed powder is difficult to control, and the components, the structure and the performance at the joint surface cannot be guaranteed. In addition, the heat treatment schedules of the GH4169 and TC17 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 for the GH4169 and TC17 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 GH4169 and TC17 alloy same-material and different-material multi-stage rotor assembly, so that the uniformity of the joint surface structure between the 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 making a GH4169 and TC17 homogeneous, dissimilar material multi-stage rotor assembly having a first disk body region made of a GH4169 alloy with at least one stage rotor portion and a second disk body region made of a TC17 alloy with 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-stage sheath at a sheath interface from a last-stage sheath, filling alloy powder into a rear-stage sheath of two stages of sheaths to be welded before welding, performing cold pressing compaction, and filling alloy powder into a first-stage sheath before welding the first-stage sheath, 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 980-1040 ℃, the pressure of 130-170 MPa and the time of 1.5-3 hours to obtain a rotor assembly blank;
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 body region is located at a preceding stage of the second disk body region.
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.
The heat treatment comprises solution treatment, the solution treatment in the first disc body area and the combination area is air cooling after heat preservation for 1 hour to 3 hours at the temperature of 950 ℃ to 980 ℃, and the solution treatment in the second disc body area is air cooling or air cooling after heat preservation for 3 hours to 5 hours at the temperature of 775 ℃ to 835 ℃.
The heat treatment further 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 bonding area is carried out after the heat preservation for 7 hours to 9 hours at the temperature of 705 ℃ to 735 ℃, the heat preservation for 7 hours to 9 hours at the temperature of 605 ℃ to 635 ℃ and then air cooling, and the aging treatment carried out on the second disc body area is carried out after the heat preservation for 7 hours to 10 hours at the temperature of 600 ℃ to 695 ℃ and then air cooling.
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 GH4169 and TC17 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of GH4169 alloy having at least one rotor section and a second disk body region of TC17 alloy having at least one rotor section, the rotor assembly being prepared by a method as hereinbefore described.
The multistage rotor assembly is divided into two alloy areas, the different alloy areas are compacted through a cold pressing method when powder is filled in the different alloy areas before hot isostatic pressing, and the two different alloy areas and a dissimilar material combination area are subjected to zoned heat treatment after the hot isostatic pressing, so that the problems of how to combine powder with two components of GH4169 and TC17 at an interface and the problem of non-uniformity of heat treatment systems 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 multistage rotor is high, the result of a tensile performance test on a TC17+ GH4169 joint is that sigma b is more than or equal to 1000MPa, the result of the tensile performance test on a TC17 alloy is that sigma b is more than or equal to 1000MPa, the result of the tensile performance test on the GH4169 alloy can reach the forging performance level of TC17 alloy and the result of sigma b is more than or equal to 1300MPa, the forging performance level of the GH4169 alloy can be reached, the lean manufacturing of the multistage rotor assembly made of the same-kind and different-kind materials of GH4169 and TC17 alloys is realized, and the use performance of the rotor is improved; and 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 a preform preparation for 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: a first disc 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-stage sheath
3-3: third-level sheath
3-4: sheath interface
4-1: GH4169 alloy powder
4-2: TC17 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 on or above a second feature in a description that follows, 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 may be formed between the first and second features, such that there may be no direct contact between the first and second features. 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 such as "forward, rearward, above, downward, left, right," "transverse, vertical, horizontal," and "top, bottom," etc. are typically indicated based on the positional or orientational relationships illustrated in the drawings for convenience in describing the invention and to simplify the description, and that these positional terms are not intended to indicate and imply that the device or element so referred to must have a particular orientation or be constructed and operated in a particular orientation without contrary intention, and therefore are not to be construed as limiting 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 to "one embodiment," "an embodiment," and/or "some embodiments" means a feature, structure, or characteristic described in connection with at least one embodiment of the 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 method for preparing a GH4169 and TC17 same-material and different-material multi-stage rotor assembly, which comprises a first disk body area made of GH4169 alloy and a second disk body area made of TC17 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 reserved amount of the single-stage preforms.
And 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 where each stage of sheath is connected with the adjacent 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, preferably, filling two-stage preforms 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, and simultaneously filling the alloy powder into the first-stage sheath, and performing cold pressing compaction. And after welding with the sheath of the adjacent stage, filling the sheath of the adjacent stage with corresponding alloy powder, after cold pressing and compacting again, welding the sheath of the next adjacent stage at the interface position, filling the corresponding alloy powder again, and so on, 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, thereby obtaining the rotor assembly preform with each stage connected in sequence.
And (3) carrying out hot isostatic pressing treatment on the rotor assembly preform subjected to cold pressing forming at the temperature of 980-1040 ℃, the pressure of 130-170 MPa and the time of 1.5-3 hours, ensuring plastic deformation and diffusion creep of powder, and finally forming a rotor assembly blank.
And (4) removing the sheath from the rotor assembly blank to finish the preparation of the GH4169 and TC17 alloy same-material and different-material multi-stage rotor assembly blank.
In response to the different heat treatment regimes of the two alloys GH4169 and TC17, it is necessary to zoned heat treat the two alloy regions of the multi-stage rotor assembly to obtain the desired texture, i.e., heat treat the first and second disk regions of the rotor assembly blank separately, and heat treat the dissimilar material joining regions of the first and second disk regions together with the first disk region using the GH4169 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 may be kept to be the same or close to each other, and therefore, the solution treatment performed on the first tray body region and the dissimilar material joining region using the GH4169 alloy may preferably be solution treatment by air cooling after heating to a temperature in the range of 950 ℃ to 980 ℃ for 1 hour to 3 hours, the aging treatment may preferably be aging treatment by air cooling after heating to a temperature in the range of 705 ℃ to 705 ℃ for 7 hours to 9 hours, followed by heat preservation at a temperature in the range of 605 ℃ to 635 ℃ for 7 hours to 9 hours, the solution treatment performed on the second tray body region using the TC17 alloy may preferably be solution treatment by air cooling or air cooling after heating to a temperature in the range of 775 ℃ to 835 ℃ for 3 hours to 5 hours, the aging treatment may preferably be an aging treatment in which the steel sheet is heated to a temperature in the range of 600 to 695 ℃ and kept at the temperature for 7 to 10 hours and then air-cooled.
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 area 1a and a second disk body area 1b, the first disk body area 1a comprises a second-stage rotor portion 1-2 and a third-stage rotor portion 1-3 which are made of GH4169 alloy, the second disk body area 1b comprises a first-stage rotor portion 1-1 which is made of TC17 alloy, and the three-stage rotor assembly 1 is prepared by hot isostatic pressing near-net-shape 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, filling GH4169 alloy powder 4-1 into the third-stage jacket 3-3, simultaneously filling TC17 alloy powder 4-2 into the first-stage jacket 3-1, compacting by a cold pressing method, welding the third-stage jacket 3-3 and the second-stage jacket 3-2 at the jacket interface 3-4, filling TC17 alloy powder 4-2 into the second-stage jacket 3-2 after welding, welding the second-stage jacket 3-2 and the first-stage jacket 3-1 at the jacket interface 3-4 after compacting by cold pressing again, and obtaining 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 three-stage rotor assembly blank 6 at a temperature of 990 ℃ to 1020 ℃, a pressure of 140MPa to 150MPa and a time of 2 hours to 2.5 hours, 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 785 ℃ to 815 ℃, preserving heat for 4 hours, then carrying out air cooling, meanwhile, heating a second-stage blank 6-2, a third-stage blank 6-3 and a dissimilar material combining area 6-4 to a temperature range of 970 ℃ to 980 ℃, preserving heat for 1 hour to 2 hours, then carrying out air cooling, and completing solution treatment; then heating the first-stage blank 6-1 to the temperature range of 620-650 ℃, preserving heat for 9 hours, then carrying out air cooling, simultaneously heating the second-stage blank 6-2, the third-stage blank 6-3 and the dissimilar material combining area 6-4 to the temperature range of 720-730 ℃, preserving heat for 7-9 hours, then preserving heat for 7-9 hours at the temperature range of 620-630 ℃, and then carrying out air cooling, thus finishing the 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 material type GH4169 and TC17 prepared by the method of preparation as hereinbefore described.
The GH4169 and TC17 multi-stage rotor assembly made of the same and different materials can be favorably 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 GH4169 and TC17 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of a GH4169 alloy having at least one rotor section and a second disk body region of a TC17 alloy having at least one rotor section, 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 980-1040 ℃, the pressure of 130-170 MPa and the time of 1.5-3 hours to obtain a rotor assembly blank;
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 claimed 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 located at a 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 according to claim 1, wherein the reaction mixture is heated,
the heat treatment comprises solution treatment, the solution treatment in the first disc body area and the combination area is air cooling after heat preservation for 1 hour to 3 hours at the temperature of 950 ℃ to 980 ℃, and the solution treatment in the second disc body area is air cooling or air cooling after heat preservation for 3 hours to 5 hours at the temperature of 775 ℃ to 835 ℃.
8. A method according to claim 7, wherein the step of preparing the composition,
the heat treatment further 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 by keeping the temperature for 7 hours to 9 hours at the temperature of 705 ℃ to 735 ℃, keeping the temperature for 7 hours to 9 hours at the temperature of 605 ℃ to 635 ℃, and then carrying out air cooling, and the aging treatment carried out on the second disc body area is carried out by keeping the temperature for 7 hours to 10 hours at the temperature of 600 ℃ to 695 ℃ and then carrying out air cooling.
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 GH4169 and TC17 homogeneous, heterogeneous material multi-stage rotor assembly having a first disk body region of GH4169 alloy with at least one stage rotor portion and a second disk body region of TC17 alloy with at least one stage rotor portion, prepared using the method of preparation of claims 1-9.
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