CN118180809A - Manufacturing method of blade ring rotor for turbine engine - Google Patents
Manufacturing method of blade ring rotor for turbine engine Download PDFInfo
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- CN118180809A CN118180809A CN202410210172.5A CN202410210172A CN118180809A CN 118180809 A CN118180809 A CN 118180809A CN 202410210172 A CN202410210172 A CN 202410210172A CN 118180809 A CN118180809 A CN 118180809A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 18
- 239000000956 alloy Substances 0.000 claims abstract description 97
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 96
- 238000003466 welding Methods 0.000 claims abstract description 34
- 238000000034 method Methods 0.000 claims abstract description 26
- 239000000835 fiber Substances 0.000 claims abstract description 24
- 239000002243 precursor Substances 0.000 claims abstract description 18
- 238000005242 forging Methods 0.000 claims abstract description 15
- 239000000463 material Substances 0.000 claims abstract description 10
- 238000004804 winding Methods 0.000 claims abstract description 8
- 238000005520 cutting process Methods 0.000 claims abstract description 4
- 238000010894 electron beam technology Methods 0.000 claims abstract description 4
- 238000007514 turning Methods 0.000 claims abstract description 4
- 239000011248 coating agent Substances 0.000 claims description 5
- 238000000576 coating method Methods 0.000 claims description 5
- 238000003754 machining Methods 0.000 claims description 5
- 238000001513 hot isostatic pressing Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 3
- 238000004806 packaging method and process Methods 0.000 claims description 3
- 239000011253 protective coating Substances 0.000 claims description 3
- 238000005538 encapsulation Methods 0.000 abstract 1
- 239000011159 matrix material Substances 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000010406 interfacial reaction Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Pressure Welding/Diffusion-Bonding (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a manufacturing method of a blade ring rotor for a turbine engine, which comprises the following steps: preparing a precursor wire by adopting Ti2AlNb material coated SiC fiber, preparing an alloy disk forging by adopting a forging process, cutting a cake blank into an alloy inner ring and an alloy outer ring, winding the precursor wire in an annular groove of the alloy inner ring, embedding the alloy inner ring into the alloy outer ring, adopting vacuum electron beam for encapsulation, forming a weight-reducing round hole in the alloy inner ring by turning, and forming a welding mortise at the rim part of the drum ring; the invention has the advantages of light structure weight, high use temperature, high fatigue performance, difficult occurrence of alloy blade falling off and long service life.
Description
Technical Field
The invention belongs to the technical field of manufacturing of turbine and compressor rotor components in turbine engines, and particularly relates to a manufacturing method of a blade ring rotor for a turbine engine.
Background
With the increasing requirements of advanced aviation equipment on power devices, the requirements of the advanced aviation equipment on parts inside the advanced aviation equipment are further required to be increased, wherein the turbine engine has higher requirements on the temperature resistance and the structural weight of the blisk parts used inside the turbine engine in the use process; the integral vane ring structure is an important component in the turbine engine, and the tensile bearing capacity of the component is effectively improved mainly through a mode of a fiber reinforced alloy material matrix, so that the purpose of reducing the volume of a disk body hub material is realized, the weight of the integral vane ring structure is convenient to further reduce, and the use effect of the integral vane ring part directly influences the use performance of the turbine engine.
At present, the existing materials of the whole leaf ring part are mainly titanium alloys such as TC17, TC25G, ti AlNb and the like reinforced by SiC fibers, and the highest use temperature of the whole leaf ring part is often limited by the oxidation resistance temperature of a matrix, and the highest use temperature of the whole leaf ring part is generally not over 700 ℃, is not suitable for use in the environments of 800 ℃ and 900 ℃, and limits the use scene of the whole leaf ring part; when facing the higher demand of using temperature, the present general use needs to achieve the purpose of increasing the highest limit of using temperature by adopting a high-temperature alloy matrix, but the high-temperature alloy matrix increases the using temperature of the whole blade ring part to a certain extent, but because of the interfacial reaction problem between the high-temperature alloy matrix and the SiC fiber titanium alloy, the high-temperature alloy matrix still has a plurality of limits in the practical use process.
Meanwhile, a linear friction welding technology exists in the welding processing field, can realize welding of the same material and different materials, has the characteristics of high structural strength and high fatigue performance, and can be used for connecting a blade and a wheel disc to prepare a blisk; at present, a wheel disc and a blade can be connected into a rotor integral part through a linear friction welding process, but a table is required to be used on a flange part processing boss in the whole connection process, the blade body part of the blade is welded on the boss in the whole process, then the blade shape is milled integrally, the purpose of producing a qualified blade ring rotor part can be achieved, but a welding seam in the whole process route is positioned in a larger stress area of high cycle fatigue vibration, and the fatigue strength and the service life of the blade are greatly reduced.
Therefore, there is a need for a method for manufacturing a rotor blade for a turbine engine, which can solve the technical problems of limited use temperature, inability to use at 900 ℃, low fatigue performance of the rotor blade and short service life of the existing rotor blade for the turbine engine by changing the processing materials and the processing method.
Disclosure of Invention
In view of the above, the present invention provides a method for manufacturing a blade ring rotor for a turbine engine, wherein a method for coating SiC fiber precursor wires with Ti2 panb material is used to reinforce a GH4975A alloy used at 850 ℃, and a GH4049 alloy used at 900 ℃ is welded to a drum ring by a linear friction welding process to form an integral rotor, so that the technical purposes of high fatigue performance and long service life of a rotor blade which is used and processed at 900 ℃ are achieved.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
a method of manufacturing a bling rotor for a turbine engine, comprising the steps of:
Step 1: preparing a drum cylinder ring, preparing a precursor wire by adopting Ti2AlNb materials to coat SiC fibers, preparing an alloy disc forging by adopting a forging process, roughly processing the alloy disc forging into a cake blank, cutting the cake blank into an alloy inner ring and an alloy outer ring at a fiber reinforced part, arranging an annular groove for winding the precursor wire in the alloy inner ring so as to facilitate winding of the precursor wire on the alloy inner ring, then winding the precursor wire in the annular groove of the alloy inner ring, embedding the alloy inner ring into the alloy outer ring, adopting a vacuum electron beam for packaging, carrying out hot isostatic pressing on the packaged cake blank to enable the inside to be compact, forming a fiber reinforced cake blank, forming a drum cylinder ring by turning a weight-reducing round hole in the inside of the alloy inner ring, and processing a welding tenon groove at the rim part of the drum cylinder ring;
step 2: preparing a blade, namely preparing an alloy blade by adopting a forging process, roughly machining a blade body according to the size of the blade, wherein the unilateral allowance is not more than 2mm, and then machining and welding tenons, wherein the clearance between the tenons and the two sides of a mortise of a drum barrel ring is not more than 0.5mm;
Step 3: rotor welding, wherein the tenons of the alloy blades and the mortises of the drum cylinder rings are circumferentially positioned through small clearance fit of not more than 0.5mm, and the alloy blades and the drum cylinder rings are connected into a blade ring rotor blank by adopting a linear friction welding process;
Step 4: and (3) processing the blade ring rotor part, positioning a linear friction welding line, and processing through crack-stopping holes at the two ends of the welding line in the thickness direction to finish the processing.
Further, the drum ring is made of alloy used at 850-900 ℃, the precursor wire is prepared by coating the outer ring of the SiC fiber with a Ti2AlNb protective coating for preventing the SiC fiber from being corroded, and the mortises are uniformly distributed on the outer ring of the drum ring.
Further, the tenons are arranged at the bottoms of the alloy blades, the alloy blades are fixed on the outer circular side wall of the drum barrel through matching connection of the tenons and the mortises, and the alloy blades are welded to the web plate area on the drum barrel through a linear friction welding process.
Further, the crack-stopping holes are positioned on the drum barrel ring and close to the alloy blades, and the crack-stopping holes are arranged at two ends of the positions corresponding to the connection weld joints of the mortises and tenons.
Further, the drum ring uses GH4975A alloy and GH4886 alloy, and the alloy blade uses GH4049 alloy and titanium-aluminum alloy used at 900 ℃.
Further, the inner alloy ring of the drum ring was selected from the Ti2AlNb alloy used at 750 ℃.
Further, the annular groove is 20mm deep and 30mm wide.
Further, there are 72 mortises disposed around the drum ring, each of the mortises being 10mm high and 13mm wide, the tenons being no more than 0.5mm from the corresponding two side mortises.
The present invention uses GH4049 as deformation superalloy with highest temperature for rotor blade, and uses GH4975A deformation superalloy as turbine rotor blade used at 850-950 deg.C, and the drum ring is used for service at 850 deg.C or below, and at the same time the short-time service temperature can be up to 870 deg.C, and because the highest temperature zone of the blade ring rotor for turbine engine is at blade tip, the temperature of blade, rim, web and hub zone is gradually reduced, and the highest temperature difference between blade and rim zone can be up to 50 deg.C, so that according to the above-mentioned condition, the alloy blade adopts GH4049 alloy with higher temperature resistance, and the drum ring adopts SiC fiber precursor wire to reinforce existent GH4975A alloy, and the drum ring is connected with blade by means of linear friction welding technology, so that the invented rotor component of compressor used at 900 deg.C can be implemented.
By adopting the technical scheme, the invention can also bring the following beneficial effects:
1. According to the invention, the Ti2AlNb is added to coat the SiC fiber, so that the interface reaction of the fiber and the high-temperature alloy is avoided, the SiC fiber reinforced GH4975A alloy matrix is realized, the drum ring is prepared, and compared with a homogeneous wheel disc, a larger weight-reducing round hole is conveniently formed in the alloy inner ring of the drum ring, so that the technical aim of reducing the weight by more than 20% in structure is fulfilled.
2. The alloy blade of the invention selects GH4049 alloy with the use temperature of 900 ℃, and the drum barrel ring selects GH4975A alloy with the use temperature of 850 ℃ to be connected through a linear friction welding process, so that the blade ring rotor for the turbine engine can be used for a long time at the temperature of 900 ℃, and has the advantages of high temperature resistance and long service life.
3. According to the invention, the linear friction welding part is arranged in the radial plate area of the drum barrel ring, so that the drum barrel ring and the alloy blades are integrated, a high Zhou Zhendong large stress area generated at the blade root part by a welding line can be effectively avoided, the service reliability of the structure is improved, meanwhile, the adopted welding structure has the structural characteristics of a mortise and a tenon, the disastrous consequences caused by blade falling caused by failure of a welding joint can be further prevented, and the conditions of welding line crack initiation caused by radial gap of the rim and welding line crack caused by expansion are effectively prevented through the crack stopping hole.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic illustration of the connection of a crack stop hole and a crack stop hole according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of the connection of a tongue and groove to a drum ring in an embodiment of the present invention;
FIG. 4 is a schematic illustration of the connection of an annular groove and an alloy inner ring in an embodiment of the invention;
Wherein: 1. a drum ring; 2. an alloy inner ring; 3. an alloy outer ring; 4. an annular groove; 5. a weight-reducing round hole; 6. a tongue and groove; 7. alloy blades; 8. a tenon; 9. and the crack stop hole.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present invention by way of illustration, and only the components related to the present invention are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
In one embodiment of the present invention, as shown in fig. 1 to 4, a method of manufacturing a bling rotor for a turbine engine is provided, comprising:
Step 1: the method comprises the steps of preparing a drum barrel ring 1, preparing a precursor wire by adopting Ti2AlNb materials to coat SiC fibers, wherein the precursor wire is prepared by coating a Ti2AlNb protective coating for preventing the SiC fibers from being corroded on the outer ring of the SiC fibers;
Adopting a forging process to prepare a GH4975A alloy disc forging, and roughly processing the disc forging into a cake blank, wherein the disc forging can be replaced by a related high-temperature alloy or a Ti2AlNb alloy used at 800 ℃ in actual use, and the alloy inner ring 2 can also select the Ti2AlNb alloy used at 750 ℃ according to the requirement;
cutting a cake blank into an alloy inner ring 2 and an alloy outer ring 3 at a fiber reinforced part, wherein the alloy inner ring 2 is provided with an annular groove 4 for winding a precursor wire, so that the precursor wire is convenient to wind on the alloy inner ring 2, and the annular groove 4 is 20mm deep and 30mm wide;
Winding a precursor wire in an annular groove 4 of the alloy inner ring 2, embedding the alloy inner ring 2 into the alloy outer ring 3, and packaging by adopting a vacuum electron beam;
Performing hot isostatic pressing treatment on the packaged cake blank to enable the interior to be compact, forming a fiber reinforced cake blank, and determining hot isostatic pressing parameters according to the size of the cake blank;
The inside of the alloy inner ring 2 is provided with a weight-reducing round hole 5 by turning, a drum ring 1 is formed, and then, mortises 6 are processed at the rim part of the drum ring 1 according to the structure and the size of a welding part, 72 mortises 6 are arranged around the drum ring 1, and the size of each mortice 6 is 10mm high and 13mm wide.
Step2: the GH4049 alloy blade 7 is prepared by adopting a forging process, and can be replaced by a light high-temperature-resistant titanium-aluminum alloy in actual use.
According to blade size rough machining blade body, unilateral surplus is not more than 2mm, then processing welding tenon 8, the 10mm height and 13mm width of tenon 8, the clearance between tenon 8 and the two sides of mortise 6 of drum ring 1 is not more than 0.5mm, tenon 8 is arranged at the bottom of alloy blade 7, alloy blade 7 is fixed to the excircle lateral wall at drum ring 1 through the matching connection of tenon 8 and mortise 6, alloy blade 7 welds the radials region on drum ring 1 through linear friction welding technology.
Step 3: and (3) rotor welding, wherein the tenons 8 of the alloy blades 7 and the mortises 6 of the drum ring 1 are circumferentially positioned through small clearance fit of not more than 0.5mm, and the alloy blades 7 and the drum ring 1 are connected into a blade ring rotor blank by adopting a linear friction welding process.
Step 4: the processing of the blade ring rotor part, the accurate positioning of the linear friction weld joint, the processing of the through crack stop holes 9 in the thickness direction of the two ends of the weld joint, the electric spark rough processing can be adopted in the actual production, and then the drill bit is adopted to remove the remelting layer, thus completing the processing.
In a word, the invention has the advantages of light structure weight, high use temperature, high fatigue performance, difficult occurrence of alloy blade falling and long service life.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present invention should be included in the present invention. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (8)
1. A method of manufacturing a bling rotor for a turbine engine, comprising the steps of:
Step 1: preparing a drum cylinder ring (1), preparing a precursor wire by coating SiC fibers with Ti2AlNb materials, preparing an alloy disc forging by adopting a forging process, roughly processing the alloy disc forging into a cake blank, cutting the cake blank into an alloy inner ring (2) and an alloy outer ring (3) at a fiber reinforced part, arranging an annular groove (4) for winding the precursor wire on the alloy inner ring (2) conveniently, winding the precursor wire in the annular groove (4) of the alloy inner ring (2), embedding the alloy inner ring (2) into the alloy outer ring (3), adopting a vacuum electron beam for packaging, carrying out hot isostatic pressing treatment on the packaged cake blank to enable the inside to be compact, forming a fiber reinforced cake blank, forming a drum cylinder ring (1) by turning a weight-reducing round hole (5) in the alloy inner ring (2), and processing a welding tenon groove (6) at the rim part of the drum cylinder ring (1);
Step 2: preparing an alloy blade (7), preparing the alloy blade (7) by adopting a forging process, roughly machining a blade body according to the blade size, wherein the unilateral allowance is not more than 2mm, then machining and welding a tenon (8), and enabling the clearance between the tenon (8) and the two sides of a tenon groove (6) of a drum barrel ring (1) to be not more than 0.5mm;
Step 3: rotor welding, wherein the rabbets (8) of the alloy blades (7) and the mortises (6) of the drum ring (1) are circumferentially positioned through small clearance fit of not more than 0.5mm, and the alloy blades (7) and the drum ring (1) are connected into a blade ring rotor blank by adopting a linear friction welding process;
step 4: and (3) processing the blade ring rotor part, positioning a linear friction welding line, and processing through crack-stopping holes (9) at the two ends of the welding line in the thickness direction to finish the processing.
2. A method of manufacturing a bling rotor for a turbine engine as in claim 1, wherein: the drum ring (1) is made of alloy used at 850-900 ℃, the precursor wire is prepared by coating a Ti2AlNb protective coating for preventing SiC fibers from being corroded on the outer ring of the SiC fibers, and the mortises (6) are uniformly distributed on the outer ring of the drum ring (1).
3. A method of manufacturing a bling rotor for a turbine engine as in claim 2, wherein: the tenon (8) is arranged at the bottom of the alloy blade (7), the alloy blade (7) is fixed to the outer circular side wall of the drum barrel ring (1) through the matching connection of the tenon (8) and the tenon groove (6), and the alloy blade (7) is welded to the radial plate area on the drum barrel ring (1) through a linear friction welding process.
4. A method of manufacturing a bling rotor for a turbine engine as in claim 3, wherein: the crack-stopping holes (9) are positioned at positions, close to the alloy blades (7), on the drum barrel ring (1), and the crack-stopping holes (9) are arranged at two ends of the positions, corresponding to the positions of the connecting weld joints of the mortises (6) and the tenons (8).
5. A method of manufacturing a bling rotor for a turbine engine as in claim 4, wherein: the drum ring (1) adopts GH4975A alloy and GH4886 alloy, and the alloy blade (7) adopts GH4049 alloy and titanium aluminum alloy which are used at 900 ℃.
6. A method of manufacturing a bling rotor for a turbine engine as in claim 5, wherein: the alloy inner ring (2) of the drum ring (1) is selected from Ti2AlNb alloy used at 750 ℃.
7. A method of manufacturing a bling rotor for a turbine engine as in claim 6, wherein: the size of the annular groove (4) is 20mm deep and 30mm wide.
8. A method of manufacturing a bling rotor for a turbine engine as in claim 7, wherein: the number of mortises (6) arranged around the drum ring (1) is 72, the size of each mortises (6) is 10mm high and 13mm wide, the height of each tenon (8) is 10mm high and 13mm wide, and the gap between each tenon (8) and the corresponding mortises (6) at two sides is not more than 0.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410210172.5A CN118180809A (en) | 2024-02-26 | 2024-02-26 | Manufacturing method of blade ring rotor for turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410210172.5A CN118180809A (en) | 2024-02-26 | 2024-02-26 | Manufacturing method of blade ring rotor for turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118180809A true CN118180809A (en) | 2024-06-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410210172.5A Pending CN118180809A (en) | 2024-02-26 | 2024-02-26 | Manufacturing method of blade ring rotor for turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118180809A (en) |
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2024
- 2024-02-26 CN CN202410210172.5A patent/CN118180809A/en active Pending
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