CN114055076A - Preparation method of multistage rotor assembly of aircraft engine - Google Patents
Preparation method of multistage rotor assembly of aircraft engine Download PDFInfo
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- CN114055076A CN114055076A CN202010783962.4A CN202010783962A CN114055076A CN 114055076 A CN114055076 A CN 114055076A CN 202010783962 A CN202010783962 A CN 202010783962A CN 114055076 A CN114055076 A CN 114055076A
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Abstract
The invention provides a preparation method of a multistage rotor assembly of an aircraft engine, which comprises the following steps: 1) preparing pre-compacts of different parts of the multi-stage rotor assembly; 2) preparing a multistage rotor assembly welded body; 3) a bulk hot isostatic pressing multi-stage rotor assembly weld; and 4) heat treating the multi-stage rotor assembly blank. According to the invention, the lean manufacturing of the multi-stage rotor assembly of the aero-engine is realized through the process of preparing the multi-stage rotor assembly of the aero-engine by hot isostatic pressing, the comprehensive performance of the multi-stage rotor assembly is improved, the preparation process flow is shortened, and the preparation cost is reduced.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a preparation method of a multistage rotor assembly of an aero-engine.
Background
At present, titanium alloys commonly used for rotating parts of aeroengine disks are mainly TA19, TC17 and the like, and are mainly applied to fan disks and low-temperature ends of gas compressors. The TA19 alloy is a high-temperature titanium alloy with good comprehensive performance, the long-term service temperature of the alloy can reach 510 ℃ at most, the high-temperature strength and the creep property of the alloy are superior to those of the TC4 alloy, the alloy is widely used for manufacturing parts such as an aircraft engine casing, a compressor blade, a disc and the like, the production cost is relatively low, the alloy becomes the high-temperature titanium alloy with the demand of the aircraft engine second to Ti64, but the TA19 has the load-holding fatigue sensitivity in a low-temperature high-pressure section, and therefore, the alloy is not suitable for a low-temperature high-pressure environment. TC17 belongs to near-beta type titanium alloy rich in alpha, is used for large-section and high-load-carrying parts such as fans and compressor disks, and has the long-term use temperature of 427 ℃, the low-temperature specific strength of TC17 is high, but the high-temperature creep property is weaker than TA 19.
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 properties (including tensile strength, creep deformation, fatigue performance and the like) of the material properties. In order to fully exert the optimal performance of different titanium alloys TA19 and TC17 in a rotor assembly, the most effective method is to apply the TC17 alloy and the TA19 alloy to different parts in the rotor, namely the TC17 alloy to a disc body and the TA19 to a drum section, so as to form the rotor structure shown in FIG. 1 and exert the optimal performance of different materials by combining the working condition service requirement of the rotor and the performance advantages of different materials. At the same time, however, 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 brings 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 a multi-stage rotor assembly through electron beam welding, inertia friction welding and the like:
1) the electron beam welding belongs to fusion welding, the base metal is melted in the welding process, the welding joint is in a casting structure, crystal grains are thick, the defects of air holes, slag inclusion and the like can be formed due to the fact that the base metal at the welding seam is rapidly solidified after being melted, long-term mechanical properties are lower than those of the base metal, and the risk of failure of the welding seam exists in the long-term use process.
2) Inertia friction welding belongs to solid phase welding, base metal cannot be melted in the welding process, a welding joint belongs to forging structure and welded joint grain refinement, meanwhile, the inertia friction welding process is acted by a top forging force, contact surface materials are extruded out, typical fusion welding defects such as air holes and slag inclusion do not exist in a welding line, and the mechanical property is high. However, the welding precision of the inertia friction welding multistage rotor assembly is related to the equipment precision, the equipment stability and the like, higher requirements are provided for the inertia friction welding equipment, the resources of the large-scale inertia friction welding equipment are limited in China, the manufacturing cost and the difficulty are high, and the welding requirements of the rotor assembly of the aero-engine cannot be met.
Therefore, the welding connection widely adopted by the multistage rotor assembly of the aero-engine at present is reduced in performance or limited by higher equipment resource cost, and the service life and the manufacturing cost of the rotor assembly are influenced.
Disclosure of Invention
In order to improve the overall performance of the multi-stage rotor assembly of the aero-engine, reduce the cost of adopting large-sized welding equipment and reduce the preparation difficulty, the invention provides an improved preparation method of the multi-stage rotor assembly of the aero-engine. The method comprises the following steps:
1) pre-compression for preparing different parts of a multi-stage rotor assembly
Dividing the multi-stage rotor assembly into a plurality of different parts, namely a plurality of disc bodies and a plurality of drums, wherein pre-pressed bodies of the disc bodies are prepared through hot isostatic pressing by using TC17 alloy powder filled in a sheath, and pre-pressed bodies of the drums are prepared through hot isostatic pressing by using TA19 alloy powder filled in the sheath, and hot isostatic pressing process parameters of the pre-pressed bodies of the disc bodies and the drums are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 0.5-1 h;
2) preparation of a multistage rotor Assembly welded body
Arranging the plurality of pre-pressing bodies obtained in the step 1) according to the final structure of the multi-stage rotor assembly, removing the sheath at the joint surface of the adjacent pre-pressing bodies, and then forming a multi-stage rotor assembly welding body by welding the sheaths of the adjacent pre-pressing bodies;
3) bulk hot isostatic pressing multi-stage rotor assembly weld
Forming the multi-stage rotor assembly welded body into a multi-stage rotor assembly blank through hot isostatic pressing, wherein the hot isostatic pressing process parameters are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 1.5-3 h;
4) heat treating multi-stage rotor assembly stock
After removing the sheath, firstly carrying out solid solution treatment on a drum barrel area of the multistage rotor assembly blank, then carrying out solid solution treatment on a disc body area of the multistage rotor assembly blank, and finally carrying out aging treatment on the whole multistage rotor assembly blank.
In an exemplary embodiment, the hot isostatic pressing process parameters in step 1) are: the temperature is 850-.
In an exemplary embodiment, the jacket is made of stainless steel (e.g., 304 stainless steel) or carbon steel.
In an exemplary embodiment, the welding in step 2) comprises argon arc welding or plasma arc welding.
In an exemplary embodiment, the hot isostatic pressing process parameters in step 3) are: the temperature is 850-.
In an exemplary embodiment, the solution treatment process parameters of the drum zone of the multi-stage rotor assembly blank in step 4) are: keeping the temperature of 960-990 ℃ for 1-1.5h, and then cooling by air.
In an exemplary embodiment, the solution treatment process parameters of the disk region of the multi-stage rotor assembly blank in step 4) are: heat preservation is carried out for 3.5 to 4.5 hours at the temperature of 788 to 816 ℃, and then air cooling is carried out.
In an exemplary embodiment, the aging process parameters of the entirety of the multi-stage rotor assembly blank in step 4) are: keeping the temperature of 600-620 ℃ for 7.5-8.5h, and then cooling in air.
The hot isostatic pressing near-net forming technology is adopted to prepare the TC17+ TA19 multi-stage rotor assembly combined by dissimilar materials, two alloy powders of TC17 and TA19 are adopted, and when the multi-stage rotor assembly is combined in a powder state, the components of the mixed powders of the TC17 and the TA19 are difficult to control in distribution after the mixed powders exist at an interface, and the components, the structure and the performance of the combined surface cannot be guaranteed. Therefore, the invention adopts twice hot isostatic pressing, wherein the first hot isostatic pressing is the independent preforming of each part of the multi-stage rotor assembly, thus solving the problem of powder mixing at the interface; and then welding the sheath of the adjacent pre-pressing bodies to form a multi-stage rotor assembly welding body. The microstructure of the material at the interface of the TC17 alloy disc body and the TA19 alloy drum barrel cannot be influenced due to only welding the sheath; finally, the second hot isostatic pressing is an integral formation of the multi-stage rotor assembly weld, thereby achieving an effective bond at the interface of the TC17 alloy disk and the TA19 alloy drum.
In addition, because the heat treatment schedules of the TC17 alloy and the TA19 alloy are different, the required structure is obtained by carrying out local solution heat treatment on different alloy areas of the multi-stage rotor assembly blank, and finally, a uniform aging treatment process is designed aiming at the multi-stage rotor assembly blank, so that the structure performance of the whole rotor assembly is optimal.
The invention has the beneficial effects that:
in general, the process for preparing the multi-stage rotor assembly of the aero-engine by the hot isostatic pressing realizes the lean manufacturing of the multi-stage rotor assembly of the aero-engine, improves the comprehensive performance of the multi-stage rotor assembly, shortens the preparation process flow and reduces the preparation cost.
Specifically, the process for preparing the multi-stage rotor assembly of the aircraft engine by hot isostatic pressing has the following advantages compared with the welding process for preparing the multi-stage rotor assembly of the aircraft engine by electron beam welding and inertia friction welding, which is typical in the prior art:
1) uniform structure and high mechanical property: the rotor component has high density and uniform components, and no macroscopic component segregation exists in the structure, so the comprehensive mechanical property is excellent: can reach the level of forgings and is higher than the mechanical property of welding joints.
2) And (3) reducing machining procedures: compared with the machining of a forged piece, the machining 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 process 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, especially complex structures, can be prepared by the process of the present application. The structure of the multi-stage rotor assembly can be combined by self without limitation of the number of stages of the assembly.
5) The manufacturing cost is low: the process has the advantages of high utilization rate of part materials, relatively simple process, short process period and low manufacturing cost. Furthermore, the pre-pressing can be carried out simultaneously in the hot isostatic pressing equipment, saving manufacturing costs.
Drawings
Fig. 1 is a schematic structural diagram of a fifth-stage rotor assembly of an aircraft engine according to embodiment 1.
FIG. 2 is a schematic structural decomposition and reserve design diagram of a fifth-stage rotor assembly of an aircraft engine according to embodiment 1.
FIG. 3 is a schematic illustration of a pre-compact envelope of an aircraft engine fifth-stage rotor assembly according to embodiment 1.
Fig. 4 is a schematic diagram of the steps of combining pre-compacts of an aircraft engine fifth-stage rotor assembly according to embodiment 1.
Detailed Description
The invention provides a preparation method of an improved multistage rotor assembly of an aircraft engine. The method comprises the following steps:
1) pre-compression for preparing different parts of a multi-stage rotor assembly
Dividing the multi-stage rotor assembly into a plurality of different parts, namely a plurality of disc bodies and a plurality of drum drums, wherein pre-pressing bodies of the disc bodies are prepared by adopting TC17 alloy powder through hot isostatic pressing, pre-pressing bodies of the drum drums are prepared by adopting TA19 alloy powder, TC17 alloy powder and TA19 alloy powder are respectively filled into corresponding sheaths (such as stainless steel or carbon steel), and the sheaths are sealed through welding after covers of the sheaths are covered; and respectively performing hot isostatic pressing preforming, wherein the preforming process parameters are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 0.5-1 h;
2) preparation of a multistage rotor Assembly welded body
Arranging the plurality of pre-pressing bodies obtained in the step 1) according to the final structure of the multi-stage rotor assembly, removing the sheath at the joint surface of the adjacent pre-pressing bodies, and then forming a multi-stage rotor assembly welding body by welding (for example, argon arc welding or plasma arc welding) the sheaths of the adjacent pre-pressing bodies;
3) bulk hot isostatic pressing multi-stage rotor assembly weld
Forming the multi-stage rotor assembly welded body into a multi-stage rotor assembly blank through hot isostatic pressing, wherein the hot isostatic pressing process parameters are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 1.5-3 h;
4) heat treating multi-stage rotor assembly stock
After removing the sheath, firstly carrying out solution treatment on the drum barrel area of the multi-stage rotor assembly blank (for example, heat preservation at 960-990 ℃ for 1-1.5h), then carrying out solution treatment on the disc body area of the multi-stage rotor assembly blank (for example, heat preservation at 788-816 ℃ for 3.5-4.5h), and finally carrying out aging treatment on the whole multi-stage rotor assembly blank (for example, heat preservation at 600-620 ℃ for 7.5-8.5 h).
The following detailed description of certain specific embodiments of a method of manufacturing an aircraft engine fan wear ring in accordance with the present invention is provided to more fully illustrate certain and other features and advantages of the invention. It should be understood that these embodiments are merely illustrative, and the scope of the present invention is not limited thereto.
Example 1:
the embodiment prepares an aeroengine five-stage rotor assembly, and the preparation method comprises the following steps:
the method comprises the following steps: according to the structure and material selection characteristics of the titanium alloy five-stage rotor assembly, the rotor assembly is divided into five parts, including two drum parts and three disc parts. In addition, according to the characteristics of the hot isostatic pressing process and the processing requirements of subsequent combined blanks, the reserved amount is considered (see figure 2);
step two: designing and manufacturing a five-part 304 stainless steel sheath for the rotor assembly, the sheath structure being substantially identical to that of the final rotor assembly (see fig. 3);
step three: respectively filling TC17 powder and TA19 powder into a sheath with corresponding structures, welding and sealing, and then respectively performing hot isostatic pressing preforming, wherein the preforming process parameters are as follows: the temperature is 840 ℃, the pressure is 120MPa, and the time is 1h, so that precompresses of three disc bodies and precompresses of two drums are obtained;
step four: combining the prepresses in sequence, removing the sheath from the joint surface of the adjacent prepresses, and then connecting the sheaths of the adjacent prepresses by welding to form the structure of the multistage rotor assembly, wherein the sheath is welded by argon arc welding (see fig. 4) in order to ensure the welding accessibility in consideration of the structural characteristics;
step five: carrying out hot isostatic pressing treatment on the combined five-stage rotor assembly welded body, ensuring plastic deformation and diffusion creep of powder, and finally forming a multi-stage rotor assembly blank, wherein the hot isostatic pressing specific parameters are as follows: the temperature is 840 ℃, the pressure is 120MPa, and the time is 3 h;
step six: performing combined machining on the five-stage rotor assembly blank to remove the sheath;
step seven: carrying out local heat treatment on different alloy areas of the five-stage rotor assembly, firstly carrying out solid solution treatment (keeping the temperature at 960 ℃ for 1.5h, air cooling) on a TA19 alloy area, then carrying out solid solution treatment (keeping the temperature at 788 ℃ for 4.5h, air cooling) on a TC17 alloy area, and finally carrying out aging treatment (keeping the temperature at 600 ℃ for 8.5h, air cooling) on the whole assembly;
step eight: carrying out water immersion flaw detection on the five-stage rotor assembly blank, and checking the internal quality;
step nine: and (4) performing combined machining on the five-stage rotor assembly blank, and performing stress relief treatment in the machining process to finally finish the preparation of the five-stage rotor assembly.
Example 2:
the embodiment prepares a seven-stage rotor assembly of an aircraft engine, and the preparation method comprises the following steps:
the method comprises the following steps: according to the structure and material selection characteristics of the titanium alloy seven-stage rotor assembly, the rotor assembly is divided into 7 parts, including 4 drum parts and 3 disc parts. In addition, according to the characteristics of the hot isostatic pressing process and the processing requirements of subsequent combined blanks, the reserved amount is considered;
step two: designing and manufacturing 7 parts of 304 stainless steel sheath of the rotor assembly, wherein the structure of the sheath is basically the same as that of the final rotor assembly;
step three: respectively filling TC17 powder and TA19 powder into a sheath with corresponding structures, welding and sealing, and then respectively performing hot isostatic pressing preforming, wherein the preforming process parameters are as follows: the temperature is 880 ℃, the pressure is 140MPa, and the time is 0.75h, so that 3 discs of pre-pressed bodies and 4 drums of pre-pressed bodies are obtained;
step four: combining the prepresses in sequence, removing the sheath at the joint surface of the adjacent prepresses, and then connecting the sheaths of the adjacent prepresses by welding to form the structure of the multistage rotor assembly, wherein the sheath is welded by argon arc welding in order to ensure the welding accessibility in consideration of the structural characteristics;
step five: carrying out hot isostatic pressing treatment on the combined seven-stage rotor assembly welded body, ensuring plastic deformation and diffusion creep of powder, and finally forming a multi-stage rotor assembly blank, wherein the hot isostatic pressing specific parameters are as follows: the temperature is 880 ℃, the pressure is 140MPa, and the time is 2.25 h;
step six: performing combined machining on the seven-stage rotor assembly blank to remove the sheath;
step seven: carrying out local heat treatment on different alloy areas of the seven-stage rotor assembly, firstly carrying out solid solution treatment (heat preservation at 975 ℃ for 1h and air cooling) on a TA19 alloy area, then carrying out solid solution treatment (heat preservation at 802 ℃ for 4h and air cooling) on a TC17 alloy area, and finally carrying out aging treatment (heat preservation at 610 ℃ for 8h and air cooling) on the whole assembly;
step eight: carrying out water immersion flaw detection on the seven-stage rotor assembly blank, and checking the internal quality;
step nine: and (4) performing combined machining on the seven-stage rotor assembly blank, and performing stress relief treatment in the machining process to finally finish the preparation of the seven-stage rotor assembly.
Example 3:
the embodiment prepares a nine-stage rotor assembly of an aircraft engine, and the preparation method comprises the following steps:
the method comprises the following steps: according to the structure and material selection characteristics of the titanium alloy nine-stage rotor assembly, the rotor assembly is divided into 9 parts, including 5 drum parts and 4 disc parts. In addition, according to the characteristics of the hot isostatic pressing process and the processing requirements of subsequent combined blanks, the reserved amount is considered;
step two: designing and manufacturing 9 parts of 304 stainless steel sheaths of the rotor assembly, wherein the structure of the sheaths is basically the same as that of the final rotor assembly;
step three: respectively filling TC17 powder and TA19 powder into a sheath with corresponding structures, welding and sealing, and then respectively performing hot isostatic pressing preforming, wherein the preforming process parameters are as follows: the temperature is 920 ℃, the pressure is 160MPa, and the time is 0.5h, so that precompresses of 4 disc bodies and precompresses of 5 drums are obtained;
step four: combining the prepresses in sequence, removing the sheath at the joint surface of the adjacent prepresses, and then connecting the sheaths of the adjacent prepresses by welding to form the structure of the multistage rotor assembly, wherein the structure characteristics are considered, and plasma arcs are adopted to weld the sheaths to ensure the welding accessibility;
step five: carrying out hot isostatic pressing treatment on the combined nine-stage rotor assembly welded body, ensuring plastic deformation and diffusion creep of powder, and finally forming a multi-stage rotor assembly blank, wherein the hot isostatic pressing specific parameters are as follows: the temperature is 920 ℃, the pressure is 160MPa, and the time is 1.5 h;
step six: performing combined machining on the nine-stage rotor assembly blank to remove the sheath;
step seven: carrying out local heat treatment on different alloy areas of the nine-stage rotor assembly, firstly carrying out solid solution treatment (heat preservation at 990 ℃ for 1h, air cooling) on a TA19 alloy area, then carrying out solid solution treatment (heat preservation at 816 ℃ for 3.5h, air cooling) on a TC17 alloy area, and finally carrying out aging treatment (heat preservation at 620 ℃ for 7.5h, air cooling) on the whole assembly;
step eight: carrying out water immersion flaw detection on the nine-stage rotor assembly blank, and checking the internal quality;
step nine: and (4) performing combined machining on the nine-stage rotor assembly blank, and performing stress relief treatment in the machining process to finally finish the preparation of the nine-stage rotor assembly.
Example 4:
the embodiment prepares a five-stage rotor assembly of an aircraft engine, and the preparation method is similar to that of embodiment 1, except that: (1) the preforming process parameters in the third step are as follows: the temperature is 850 ℃, the pressure is 130MPa, and the time is 1 h; (2) in the fifth step, the specific parameters of the hot isostatic pressing are as follows: the temperature is 850 ℃, the pressure is 130MPa, and the time is 3 h.
Example 5:
the embodiment prepares a nine-stage rotor assembly of an aircraft engine, and the preparation method is similar to that of embodiment 3, except that: (1) the preforming process parameters in the third step are as follows: the temperature is 890 ℃, the pressure is 150MPa, and the time is 0.5 h; (2) in the fifth step, the hot isostatic pressing specific parameters are as follows: the temperature is 890 ℃, the pressure is 150MPa, and the time is 1.5 h.
The multistage rotors prepared according to examples 1-3 were tested for high overall performance: tensile properties were tested by sampling the TC17+ TA19 junctions of the multi-stage rotors, σbThe pressure is more than or equal to 900MPa, and the performance level of a TC17+ TA19 welding joint can be achieved; tensile property test is carried out on samples of TC17 alloy disc bodies of the multistage rotorsbThe pressure is more than or equal to 1000MPa, and the performance level of a forging of TC17 alloy can be achieved; tensile property test was performed on samples of TA19 alloy drums for multi-stage rotors, σbNot less than 900MPa, can reach the forging performance level of TA19 alloy.
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. Unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which these exemplary embodiments belong. The terminology used in the description herein is for the purpose of describing exemplary embodiments only and is not intended to be limiting of exemplary embodiments. Accordingly, the overall inventive concept is not intended to be limited to the specific embodiments described herein. Although preferred methods and materials are described herein, other methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present invention.
Unless otherwise indicated, all numbers expressing quantities of ingredients, chemical and molecular properties, reaction conditions, and so forth, used in the specification and claims are to be understood as being modified in all instances by the term "about". Accordingly, unless indicated to the contrary, the numerical parameters set forth in the specification and attached claims are approximations that may vary depending upon the desired properties sought to be obtained by the exemplary embodiments herein. At the very least, and not as an attempt to limit the application of the doctrine of equivalents to the number of equivalents, each numerical parameter should at least be construed in light of the number of reported significant digits and ordinary rounding approaches.
Notwithstanding that the numerical ranges and parameters setting forth the broad scope of the exemplary embodiments are approximations, the numerical values set forth in the specific examples are reported as precisely as possible. Any numerical value, however, inherently contains certain errors necessarily resulting from the standard deviation found in their respective testing measurements. Every numerical range given throughout this specification and claims will include every narrower numerical range that falls within such broader numerical range, as if such narrower numerical ranges were all expressly written herein. Further, any numerical values reported in the examples can be used to define the upper or lower endpoints of the broader compositional ranges disclosed herein.
Claims (8)
1. A method of making an aircraft engine multi-stage rotor assembly, the method comprising the steps of:
1) pre-compression for preparing different parts of a multi-stage rotor assembly
Dividing the multi-stage rotor assembly into a plurality of different parts, namely a plurality of disc bodies and a plurality of drums, wherein pre-pressed bodies of the disc bodies are prepared through hot isostatic pressing by using TC17 alloy powder filled in a sheath, and pre-pressed bodies of the drums are prepared through hot isostatic pressing by using TA19 alloy powder filled in the sheath, and hot isostatic pressing process parameters of the pre-pressed bodies of the disc bodies and the drums are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 0.5-1 h;
2) preparation of a multistage rotor Assembly welded body
Arranging the plurality of pre-pressing bodies obtained in the step 1) according to the final structure of the multi-stage rotor assembly, removing the sheath at the joint surface of the adjacent pre-pressing bodies, and then forming a multi-stage rotor assembly welding body by welding the sheaths of the adjacent pre-pressing bodies;
3) bulk hot isostatic pressing multi-stage rotor assembly weld
Forming the multi-stage rotor assembly welded body into a multi-stage rotor assembly blank through hot isostatic pressing, wherein the hot isostatic pressing process parameters are as follows: the temperature is 840 ℃ and 920 ℃, the pressure is 120 ℃ and 160MPa, and the time is 1.5-3 h;
4) heat treating multi-stage rotor assembly stock
After removing the sheath, firstly carrying out solid solution treatment on a drum barrel area of the multistage rotor assembly blank, then carrying out solid solution treatment on a disc body area of the multistage rotor assembly blank, and finally carrying out aging treatment on the whole multistage rotor assembly blank.
2. The method of claim 1, wherein the hot isostatic pressing process parameters in step 1) are: 850-.
3. The method of claim 1, wherein the wrap is made of stainless steel or carbon steel.
4. The method of claim 1, wherein the welding in step 2) comprises argon arc welding or plasma arc welding.
5. The method of claim 1, wherein the hot isostatic pressing process parameters in step 3) are: 850-.
6. The method of claim 1, wherein the solution treatment process parameters of the drum zone of the multi-stage rotor assembly blank in step 4) are: keeping the temperature of 960-990 ℃ for 1-1.5h, and then cooling by air.
7. The method of claim 1 wherein the solution treatment process parameters of the disk regions of the multi-stage rotor assembly blank in step 4) are: heat preservation is carried out for 3.5 to 4.5 hours at the temperature of 788 to 816 ℃, and then air cooling is carried out.
8. The method of claim 1, wherein the overall aging process parameters of the multi-stage rotor assembly blank in step 4) are: keeping the temperature of 600-620 ℃ for 7.5-8.5h, and then cooling in air.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5106012A (en) * | 1989-07-10 | 1992-04-21 | Wyman-Gordon Company | Dual-alloy disk system |
| 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 |
| CN103691952A (en) * | 2014-01-06 | 2014-04-02 | 钢铁研究总院 | Preparation method of functional gradient performance coil |
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2020
- 2020-08-06 CN CN202010783962.4A patent/CN114055076B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5106012A (en) * | 1989-07-10 | 1992-04-21 | Wyman-Gordon Company | Dual-alloy disk system |
| 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 |
| CN103691952A (en) * | 2014-01-06 | 2014-04-02 | 钢铁研究总院 | Preparation method of functional gradient performance coil |
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| CN114055076B (en) | 2023-02-28 |
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