CN112302725B - Compact aeroengine high pressure rotor connection structure - Google Patents
Compact aeroengine high pressure rotor connection structure Download PDFInfo
- Publication number
- CN112302725B CN112302725B CN202010988342.4A CN202010988342A CN112302725B CN 112302725 B CN112302725 B CN 112302725B CN 202010988342 A CN202010988342 A CN 202010988342A CN 112302725 B CN112302725 B CN 112302725B
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- pressure
- pressure turbine
- turbine disc
- compression nut
- rear shaft
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
Abstract
The invention provides a compact type aeroengine high-pressure rotor connecting structure, which relates to the technical field of aeroengines and comprises a high-pressure compressor rear shaft neck and a high-pressure turbine disc, wherein the connecting surface of the high-pressure compressor rear shaft neck and the high-pressure turbine disc is provided with a matched tooth-shaped meshing structure for connecting the high-pressure compressor rear shaft neck and the high-pressure turbine disc; the air guide pipe and the compression nut are arranged in the high-pressure turbine disc, a protruding portion of one end of the air guide pipe abuts against the rear shaft neck of the high-pressure compressor, the compression nut is in threaded connection with the other end of the air guide pipe, the side wall of the compression nut abuts against the high-pressure turbine disc, and therefore the protruding portion of the air guide pipe and the compression nut provide pre-tightening force for the toothed meshing structure of the rear shaft neck of the high-pressure compressor and the high-pressure turbine disc. The connecting structure of the invention realizes the stable connection of the rotors, reliably transmits the axial force and the torque and simultaneously improves the assembly and the maintenance.
Description
Technical Field
The utility model relates to an aeroengine technical field especially relates to a compact aeroengine high pressure rotor connection structure.
Background
An aircraft engine is a typical Brayton cycle heat engine and generally comprises components such as a compressor, a combustion chamber and a turbine. The high-temperature and high-pressure gas at the outlet of the combustion chamber drives the turbine to do work to drive the compressor to compress air, and the structure for connecting the compressor rotor and the turbine rotor is called as a rotor connecting structure. For a twin-rotor aircraft engine, the structure connecting the high-pressure compressor rotor and the high-pressure turbine rotor is called a high-pressure rotor connection structure.
High-pressure rotor connection structures are generally required to be capable of stably and reliably transmitting axial loads and torques, and common rotor connection structures are in the form of: a) the bolt connection transmits axial force, friction force and torque transmission and spigot centering; b) the bolt is connected to transmit axial force and the arc-shaped end teeth transmit torque to be centered; c) and the compression nut is connected with the sleeve gear to transmit axial force and sleeve gear torque transmission centering. In some dual-rotor aircraft engine designs, it may be necessary to provide an air duct communicating with the front and rear fulcrum bearing cavities, and at this time, the high-pressure rotor connection structure design must ensure the penetration of the low-pressure connection shaft and the air duct at the inner side, and be limited by the inner diameter of the combustion chamber at the outer side. Due to the structural limitation, the three connection structures are difficult to meet the use requirement, and therefore, a compact connection structure of the high-pressure rotor of the aircraft engine needs to be designed.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide a compact connection structure for a high-pressure rotor of an aircraft engine, which realizes stable connection of the rotors, reliably transmits axial force and torque, and improves assembly performance and maintainability.
In order to achieve the above purpose, the invention provides the following technical scheme:
a compact type aeroengine high-pressure rotor connecting structure comprises a high-pressure compressor rear shaft neck and a high-pressure turbine disc, wherein a connecting surface of the high-pressure compressor rear shaft neck and the high-pressure turbine disc is provided with a matched tooth-shaped meshing structure for connecting the high-pressure compressor rear shaft neck and the high-pressure turbine disc; the air guide pipe and the compression nut are arranged in the high-pressure turbine disc, a protruding portion of one end of the air guide pipe abuts against the rear shaft neck of the high-pressure compressor, the compression nut is in threaded connection with the other end of the air guide pipe, the side wall of the compression nut abuts against the high-pressure turbine disc, and therefore the protruding portion of the air guide pipe and the compression nut provide pre-tightening force for the toothed meshing structure of the rear shaft neck of the high-pressure compressor and the high-pressure turbine disc.
The sealing ring is arranged on the outer side of the toothed meshing structure of the high-pressure compressor rear shaft neck and the high-pressure turbine disc and used for separating an inner cavity and an outer cavity of the high-pressure rotor.
Furthermore, the cross section of the sealing ring is Z-shaped, and one side extending edge of the sealing ring is tightly attached to the rear shaft neck of the high-pressure compressor, and the other side extending edge of the sealing ring is tightly attached to the high-pressure turbine disc.
Further, the graphite runway and the bearing inner ring are sequentially sleeved on one side of the high-pressure turbine disc, the outer side of the bearing inner ring is abutted to the side wall of the compression nut, so that the compression nut provides lateral pre-tightening force for the bearing inner ring and the graphite runway, and the bearing inner ring and the graphite runway are fixed on the high-pressure turbine disc.
Furthermore, the side wall of the compression nut is in a boss shape, the side wall convex surface of the compression nut is abutted with the high-pressure turbine disc, and the side wall concave surface of the compression nut is abutted with the bearing inner ring.
Furthermore, the graphite runway also comprises an elastic ring which is sleeved between the bearing inner ring and the graphite runway.
Furthermore, a plurality of bosses are uniformly arranged on the surfaces of the two sides of the elastic ring, and the bosses on the surfaces of the two sides are arranged in a staggered mode.
Further, still include the bush, the bush cover is located between bearing inner ring and the elastic ring.
The invention discloses a compact type aeroengine high-pressure rotor connecting structure, which has the beneficial effects that: the high-pressure rotor connecting structure is compact in structure, and overcomes the technical defect that the traditional high-pressure rotor connecting structure is limited by the inner diameter of an external combustion chamber and the outer diameter of an internal air conduit. The invention adopts the air conduit as the long bolt to simplify the structure, and selects the structure of the circular arc end tooth torque transmission to be matched with the limitation of the inner diameter of the combustion chamber, thereby completing the rotor connection in a limited space. The use of a compression nut also simplifies the design of the connection, but at the same time requires the inner ring of the bearing to be protected from working safely, so that an elastic ring is designed to solve this problem. Compared with the traditional connection structure, the structure is more compact, and only one threaded connection structure is arranged, so that the structure also has the advantages of convenience in assembly and disassembly and convenience in maintenance.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the connection structure of a high-pressure rotor of a compact aircraft engine according to the invention;
FIG. 2 is another schematic view of the compact aircraft engine high pressure rotor connection of the present invention;
FIG. 3 is a partial schematic view of the structure at A in FIG. 1;
FIG. 4 is a partial schematic view of FIG. 1 at C;
FIG. 5 is a partial schematic view of the tooth-like engagement structure at B in FIG. 1;
FIG. 6 is a schematic structural diagram of a sealing ring in the high-pressure rotor connecting structure of the compact aero-engine of the present invention;
FIG. 7 is a schematic view of an elastic ring structure in the compact aero-engine high-pressure rotor connection structure according to the present invention;
fig. 8 is a schematic structural diagram of a compression nut in the compact aircraft engine high-pressure rotor connection structure.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure of the present disclosure. It is to be understood that the embodiments described are only a few embodiments of the present disclosure, and not all embodiments. The disclosure may be carried into practice or applied to various other specific embodiments, and various modifications and changes may be made in the details within the description and the drawings without departing from the spirit of the disclosure. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended 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 disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects 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. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be further noted that the drawings provided in the following embodiments are only schematic illustrations of the basic concepts of the present disclosure, and the drawings only show the components related to the present disclosure rather than the numbers, shapes and dimensions of the components in actual implementation, and the types, the numbers and the proportions 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 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.
As shown in fig. 1 to 8, the embodiment of the present disclosure provides a compact aircraft engine high-pressure rotor connection structure, including a high-pressure compressor rear journal 1 and a high-pressure turbine disk 4, where a tooth-shaped engagement structure 3 adapted to a connection surface of the high-pressure compressor rear journal 1 and the high-pressure turbine disk 4 is arranged, as shown in fig. 5, for connecting the high-pressure compressor rear journal 1 and the high-pressure turbine disk 4; the high-pressure turbine disc type air compressor further comprises an air guide pipe 10 and a compression nut 9, wherein a protruding portion at one end of the air guide pipe 10 abuts against the rear shaft neck 1 of the high-pressure compressor, the compression nut 9 is in threaded connection with the other end of the air guide pipe 10, and the side wall of the compression nut 9 abuts against the high-pressure turbine disc 4, so that the protruding portion of the air guide pipe 10 and the compression nut 9 provide pre-tightening force for the toothed meshing structures 3 of the rear shaft neck 1 of the high-pressure compressor and the high-pressure turbine disc 4.
Further, the high-pressure turbine disc comprises a graphite runway 5 and a bearing inner ring 8, wherein the graphite runway 5 and the bearing inner ring 8 are sleeved on one side of the high-pressure turbine disc 4, one side of the bearing inner ring 8 abuts against the side wall of the compression nut 9, so that the compression nut 9 provides lateral pre-tightening force for the bearing inner ring 8 and the graphite runway 5, and the bearing inner ring 8 and the graphite runway 5 are fixed on the high-pressure turbine disc 4.
In order to ensure that the gland nut 9 can provide sufficient pre-tightening force to the toothed meshing structure 3 at the connecting surface of the high-pressure compressor rear journal 1 and the high-pressure turbine disk 4 and at the same time protect the thin-walled bearing inner ring 8 from excessive pre-tightening force, in a preferred embodiment, the side wall of the gland nut 9 is in a boss shape, as shown in fig. 8, and the side wall convex surface of the gland nut 9 abuts against the high-pressure turbine disk 4 and the side wall concave surface of the gland nut 9 abuts against the bearing inner ring 8.
In a preferred embodiment, the high-pressure rotor further comprises a sealing ring 2, as shown in fig. 6, wherein the sealing ring 2 is arranged outside the toothed meshing structure 3 of the high-pressure compressor rear journal 1 and the high-pressure turbine disc 4 and used for separating an inner cavity and an outer cavity of the high-pressure rotor. Specifically, the section of the sealing ring 2 is Z-shaped, and one side of the sealing ring 2 is tightly attached to the rear shaft neck 1 of the high-pressure compressor, and the other side of the sealing ring is tightly attached to the high-pressure turbine disc 4.
In another preferred embodiment, the graphite runway further comprises an elastic ring 6, and the elastic ring 6 is sleeved between the bearing inner ring 8 and the lug of the graphite runway 5. Specifically, a plurality of bosses are uniformly arranged on the surfaces of the two sides of the elastic ring 6, and the bosses on the surfaces of the two sides are arranged in a staggered manner. Further preferably, the bearing further comprises a bushing 7, and the bushing 7 is sleeved between the bearing inner ring 8 and the elastic ring 6.
High pressure rotor connection structures often need to be exposed to the effects of thermal, pneumatic and mechanical loads under different operating conditions during engine operation. Therefore, in order to ensure that the connection structure always works stably under various working conditions, the Z-shaped sealing ring 2 and the elastic ring 6 are designed in the embodiment of the invention, and the two elastic elements have lower rigidity. The Z-seal 2 is responsible for separating the inner and outer cavities of the high pressure rotor to prevent overheating of the air duct 10. In order to ensure that the Z-shaped sealing ring 2 is always effectively attached, the Z-shaped sealing ring 2 is designed into a Z-shaped structure with lower rigidity, and the Z-shaped sealing ring is always effectively attached in the working process. In order to ensure that the compression nut 9 effectively pre-tightens the bearing inner ring 8 and the toothed meshing structure 3 simultaneously in the screwing process and the bearing inner ring 8 does not bear overlarge axial pre-tightening force, the part elastic ring 6 is arranged. The elastic ring 6 is designed into a circular ring structure with bosses on both sides, as shown in fig. 7, the elastic ring is an elastic element with lower rigidity and is responsible for protecting the thin-walled bearing inner ring 8 from bearing too high axial pre-tightening force. In addition, in order to ensure that the bearing inner ring 8 is not subjected to local loading by the lug of the elastic ring 6 under the influence of form and position tolerance to cause local bulging, a bushing 7 with a circular ring structure is arranged between the two.
In the mounting process of the structure, the graphite runway 5, the elastic ring 6, the bushing 7 and the bearing inner ring 8 are sequentially mounted on the high-pressure turbine disc 4 to form a high-pressure turbine rotor, and the air guide pipe 10 is mounted inside the rear shaft neck 1 of the high-pressure compressor to form the high-pressure compressor rotor. Then, the Z-shaped sealing ring 2 is arranged on the rear shaft neck 1 of the high-pressure compressor, the high-pressure turbine rotor is further arranged, and finally the compression nut 9 is arranged and screwed. The air guide pipe 10 is also used as a long bolt to take charge of tensioning the high-pressure compressor rotor and the high-pressure turbine rotor, and provides enough pretightening force for the toothed meshing structure 3 after being matched and screwed with the compression nut 9, so that stable torque transmission and centering are guaranteed.
The key point of the invention is that the design of the connecting structure is developed on the premise of not highlighting the outlines of the established compressor rotor and the high-pressure turbine rotor, thereby achieving the optimal solution in space. The toothed meshing structure 3 tensioned by the compression nut 9 can ensure that the external profile of the connecting structure is as small as possible, and the air duct 10 structure can ensure effective utilization of the internal space of the connecting structure after being used as a long bolt.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (8)
1. A compact type aeroengine high-pressure rotor connecting structure is characterized by comprising a high-pressure compressor rear shaft neck and a high-pressure turbine disc, wherein the connecting surface of the high-pressure compressor rear shaft neck and the high-pressure turbine disc is provided with a matched tooth-shaped meshing structure for connecting the high-pressure compressor rear shaft neck and the high-pressure turbine disc; the air guide pipe and the compression nut are arranged in the high-pressure turbine disc, a protruding portion of one end of the air guide pipe abuts against the rear shaft neck of the high-pressure compressor, the compression nut is in threaded connection with the other end of the air guide pipe, the side wall of the compression nut abuts against the high-pressure turbine disc, and therefore the protruding portion of the air guide pipe and the compression nut provide pre-tightening force for the toothed meshing structure of the rear shaft neck of the high-pressure compressor and the high-pressure turbine disc.
2. The compact aircraft engine high-pressure rotor connection structure as claimed in claim 1, further comprising a sealing ring, wherein the sealing ring is disposed outside the tooth-shaped meshing structure of the high-pressure compressor rear journal and the high-pressure turbine disc, and is used for separating an inner cavity and an outer cavity of the high-pressure rotor.
3. The compact type aircraft engine high-pressure rotor connection structure as claimed in claim 2, wherein the cross section of the sealing ring is Z-shaped, and one side extending edge of the sealing ring is tightly attached to the rear shaft neck of the high-pressure compressor, and the other side extending edge of the sealing ring is tightly attached to the high-pressure turbine disc.
4. The compact type aircraft engine high-pressure rotor connection structure as claimed in claim 3, further comprising a graphite runway and a bearing inner ring which are sequentially sleeved on one side of the high-pressure turbine disc, wherein the outer side of the bearing inner ring abuts against the side wall of the compression nut, so that the compression nut provides lateral pre-tightening force for the bearing inner ring and the graphite runway, and the bearing inner ring and the graphite runway are fixed on the high-pressure turbine disc.
5. The compact aircraft engine high pressure rotor connection of claim 4, wherein the compression nut sidewall is boss-shaped, and wherein the compression nut sidewall convex surface abuts the high pressure turbine disk and the compression nut sidewall concave surface abuts the bearing inner ring.
6. The compact aircraft engine high pressure rotor connection of claim 5, further comprising an elastic ring, said elastic ring being fitted between said bearing inner ring and said graphite raceway.
7. The compact aircraft engine high-pressure rotor connection structure as defined in claim 6, wherein a plurality of bosses are uniformly formed on both side surfaces of the elastic ring, and the bosses on both side surfaces are arranged in a staggered manner.
8. The compact aircraft engine high pressure rotor connection of claim 7, further comprising a bushing sleeved between the bearing inner ring and the elastomeric ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988342.4A CN112302725B (en) | 2020-09-18 | 2020-09-18 | Compact aeroengine high pressure rotor connection structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988342.4A CN112302725B (en) | 2020-09-18 | 2020-09-18 | Compact aeroengine high pressure rotor connection structure |
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| CN112302725A CN112302725A (en) | 2021-02-02 |
| CN112302725B true CN112302725B (en) | 2022-07-26 |
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| CN202010988342.4A Active CN112302725B (en) | 2020-09-18 | 2020-09-18 | Compact aeroengine high pressure rotor connection structure |
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| CN115949670B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Elastic structure for axial compression of bearing |
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