CN112228386B

CN112228386B - Compressor and aircraft engine

Info

Publication number: CN112228386B
Application number: CN202011461878.7A
Authority: CN
Inventors: 王家广; 茅威; 严冬青; 江奔; 吴志青
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-12-14
Filing date: 2020-12-14
Publication date: 2021-03-16
Anticipated expiration: 2040-12-14
Also published as: CN112228386A

Abstract

The invention relates to a compressor and an aero-engine, wherein the compressor comprises a casing (10), a stationary blade and a sealing ring (30), the casing (10) is provided with a mounting hole (11), the stationary blade comprises a blade body and a shaft neck (20) connected with the blade body, the shaft neck (20) is mounted in the mounting hole (11), the periphery of the shaft neck (20) is provided with a first sealing part (21), the sealing ring (30) is arranged in the mounting hole (11) and sleeved on the periphery of the shaft neck (20), the inner side of the sealing ring (30) is provided with a second sealing part (311), and the first sealing part (21) and the second sealing part (311) are matched with each other to form a labyrinth sealing structure. According to the invention, through the labyrinth seal structure, gas leakage between the shaft neck and the mounting hole can be reduced, pneumatic loss is reduced, and the working efficiency of the gas compressor is improved.

Description

Compressor and aircraft engine

Technical Field

The invention relates to the technical field of aero-engines, in particular to a gas compressor and an aero-engine.

Background

At present, for a multistage high-pressure compressor of an aeroengine at home and abroad, in order to improve the surge margin under the full working condition, a stator blade is mostly set to be an adjustable structure. The adjustable stationary blade comprises a blade and shaft necks positioned at the upper end and the lower end of the blade, the shaft neck at the upper end of the blade is arranged in the mounting hole of the stator casing, and a bushing is arranged between the shaft neck at the upper end and the mounting hole of the casing.

In the installation process of the adjustable stationary blade, in order to avoid the over-constraint condition, the inner diameter of the bushing and the outer diameter of the shaft neck and the outer diameter of the bushing and the inner diameter of the installation hole of the casing are in clearance fit, the clearance fit inevitably brings about leakage of high-temperature and high-pressure gas in a main runner of the high-pressure gas compressor, the leaked high-temperature and high-pressure gas reduces the efficiency of the high-pressure gas compressor on one hand, and on the other hand, the working environment of parts outside the casing is worse.

It is noted that the information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information constitutes prior art already known to a person skilled in the art.

Disclosure of Invention

The embodiment of the invention provides a gas compressor and an aeroengine, which can reduce gas leakage at the installation position of a stationary blade in the gas compressor.

According to an aspect of the present invention, there is provided a compressor comprising:

the casing is provided with a mounting hole;

the fixed blade comprises a blade body and a shaft neck connected with the blade body, the shaft neck is arranged in the mounting hole, and a first sealing part is arranged on the periphery of the shaft neck; and

and the sealing ring is arranged in the mounting hole and sleeved on the periphery of the shaft neck, a second sealing part is arranged on the inner side of the sealing ring, and the first sealing part and the second sealing part are mutually matched to form a labyrinth sealing structure.

In some embodiments, the first seal portion includes a plurality of first grooves and a first land between two adjacent first grooves.

In some embodiments, the first groove extends from an outer side of the journal in a direction proximate to the axis of the journal.

In some embodiments, the second sealing portion includes a plurality of second grooves and second bosses located between adjacent two of the second grooves, the first bosses being inserted into the second grooves, and the second bosses being inserted into the first grooves.

In some embodiments, the seal ring includes a ring body and a skeleton disposed within the ring body, the skeleton having a hardness greater than a hardness of the ring body.

In some embodiments, the frame includes a support ring and a support plate disposed inside the support ring.

In some embodiments, the second seal portion includes a plurality of second grooves and a second boss located between two adjacent second grooves, and the support plate extends from the support ring to an interior of the second boss.

In some embodiments, the skeleton includes a plurality of support plates arranged at intervals in a circumferential direction of the support ring or connected in a ring shape in the circumferential direction of the support ring.

In some embodiments, the backbone includes a plurality of support plates spaced along the axis of the journal.

In some embodiments, the seal ring has an opening in a circumferential direction to bring an outer side face of the seal ring into press contact with a hole wall of the mounting hole by deformation of the seal ring.

In some embodiments, the compressor further includes a first bushing and a second bushing, the first bushing and the second bushing being disposed between the bore wall of the mounting bore and the journal, and the seal ring being located between the first bushing and the second bushing in an axial direction of the journal.

According to another aspect of the invention, an aircraft engine is provided, comprising the compressor.

Based on the technical scheme, in the embodiment of the invention, the sealing ring is arranged between the periphery of the shaft neck and the hole wall of the mounting hole, the inner side of the sealing ring is provided with the second sealing part, and the second sealing part and the first sealing part arranged on the periphery of the shaft neck are matched with each other to form the labyrinth sealing structure.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention.

Fig. 1 is a partial structural schematic diagram of an embodiment of a compressor according to the present invention.

Fig. 2 is a partially enlarged view of fig. 1.

Fig. 3 is a schematic structural diagram of a seal ring in an embodiment of the compressor of the present invention.

In the figure: 10. a case; 11. mounting holes; 20. a journal; 21. a first seal portion; 30. a seal ring; 31. a ring body; 311. a second seal portion; 32. a framework; 321. a support ring; 322. a support plate; 33. an opening; 40. a first bushing; 50. a second bushing.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "central," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the invention and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the scope of the invention.

As shown in fig. 1 and 2, in some embodiments of the compressor provided by the present invention, the compressor includes a casing 10, a stationary blade and a sealing ring 30, the casing 10 is provided with a mounting hole 11, the stationary blade includes a blade body and a journal 20 connected to the blade body, the journal 20 is mounted in the mounting hole 11, the outer periphery of the journal 20 is provided with a first sealing portion 21, the sealing ring 30 is disposed in the mounting hole 11 and is sleeved on the outer periphery of the journal 20, the inner side of the sealing ring 30 is provided with a second sealing portion 311, and the first sealing portion 21 and the second sealing portion 311 cooperate to form a labyrinth structure.

In the above embodiment, the sealing ring 30 is disposed between the outer periphery of the journal 20 and the wall of the mounting hole 11, the second sealing portion 311 is disposed inside the sealing ring 30, and the second sealing portion 311 cooperates with the first sealing portion 21 disposed on the outer periphery of the journal 20 to form a labyrinth sealing structure, so that the sealing structure can reduce gas leakage between the journal 20 and the mounting hole 11, reduce aerodynamic loss, and improve the working efficiency of the compressor.

The labyrinth seal structure has good sealing effect and is simple to manufacture and install.

In some embodiments, the first sealing portion 21 includes a plurality of first grooves and a first boss located between adjacent two first grooves. Through setting up first recess and first boss, be convenient for form labyrinth seal structure.

In some embodiments, the first groove extends from an outer side of the journal 20 in a direction proximate to the axis of the journal 20. The first sealing portion 21 is arranged on the periphery of the shaft neck 20 and is formed by digging a groove inwards from the outer side surface of the shaft neck 20, so that the shaft neck 20 is convenient to reform, no new part needs to be added on the shaft neck 20, and the whole structure of the shaft neck 20 is high in strength and good in reliability after the first sealing portion 21 is arranged.

In some embodiments, the second sealing portion 311 includes a plurality of second grooves and second bosses located between two adjacent second grooves, the first bosses being inserted into the second grooves, and the second bosses being inserted into the first grooves.

Through inserting first boss in the second recess, and the second boss inserts in the first recess, can increase the resistance that gas flows in labyrinth structure, improve the effect of obturating.

In some embodiments, a gap is formed between the top of the first boss and the bottom of the second groove, and a gap is also formed between the top of the second boss and the bottom of the first groove, so that the occurrence of abrasion is avoided.

In some embodiments, seal ring 30 includes a ring body 31 and a skeleton 32 disposed within ring body 31, the skeleton 32 having a hardness greater than a hardness of ring body 31.

The ring body 31 has a low hardness, which facilitates the installation of the sealing ring 30. The rigidity of skeleton 32 is great, can improve the overall structure intensity of sealing ring 30, improves the effect of obturating.

In some embodiments, ring body 31 is made of a non-metallic material having low hardness and high self-lubricity, wear resistance, corrosion resistance, high temperature resistance, and the like, such as polytetrafluoroethylene, rubber, and the like.

In some embodiments, the backbone 32 is made of a harder, higher material to increase the overall structural strength of the seal ring 30.

In some embodiments, the armature 32 is made of an elastomeric material. The framework 32 is made of elastic materials and can elastically deform, the deformed sealing ring 30 is installed between the shaft neck 20 and the hole wall of the installation hole 11, and the sealing ring 30 can be in close contact with the outer side face of the shaft neck 20 and the hole wall of the installation hole 11 through elastic potential energy stored after deformation, so that the sealing effect is improved.

Further, the frame 32 is made of an elastic material having excellent fatigue resistance and sag resistance, such as spring steel (65 Mn).

In some embodiments, the ring 31 is bonded or injection molded to the frame 32 to form a unitary body.

As shown in fig. 2, in some embodiments, the frame 32 includes a support ring 321 and a support plate 322 disposed inside the support ring 321. The support ring 321 is an annular structure that serves as a main body support for the framework 32. The support plate 322 is attached to the inner side of the support ring 321, and the support capability of the support ring 321 can be increased.

In some embodiments, the second sealing portion 311 includes a plurality of second grooves and a second boss located between two adjacent second grooves, and the support plate 322 extends from the support ring 321 to the inside of the second boss. One side of backup pad 322 is connected with support ring 321, and the one side of keeping away from support ring 321 of backup pad 322 extends to the inside of second boss, can support the second boss like this, improves the structural strength of second boss, avoids the second boss to take place to warp under great air pressure and influence the effect of obturating.

In some embodiments, the frame 32 includes a plurality of support plates 322, and the plurality of support plates 322 are spaced apart along the circumference of the support ring 321 or connected in a ring shape along the circumference of the support ring 321.

The support plate 322 may have an arc shape, and a plurality of arc-shaped support plates 322 are arranged at intervals along the circumference of the support ring 321. The plurality of support plates 322 may be connected to form a ring structure, and the support plane of the support plates 322 is perpendicular to the axial direction of the support ring 321.

In some embodiments, the framework 32 includes a plurality of support plates 322, the plurality of support plates 322 being spaced apart along the axial direction of the journal 20. That is, in the axial direction, the inner side of the support ring 321 is arranged with a multi-layered support plate 322 to support the plurality of second bosses provided in the axial direction.

As shown in fig. 3, in some embodiments, the seal ring 30 has an opening 33 in the circumferential direction to bring the outer side face of the seal ring 30 into press contact with the hole wall of the mounting hole 11 by deformation of the seal ring 30. The sealing ring 30 can be more easily fitted around the outer circumference of the journal 20 via this opening 33. Moreover, through the arrangement of the opening 33, the sealing ring 30 can be squeezed to accumulate elastic potential energy in the circumferential direction, under the action of the elastic potential energy, the outer side surface of the sealing ring 30 is in closer contact with the hole wall of the mounting hole 11, leakage of high-temperature and high-pressure gas is prevented, and the sealing effect is improved.

In some embodiments, the compressor further includes a first bushing 40 and a second bushing 50, the first bushing 40 and the second bushing 50 being disposed between the bore wall of the mounting bore 11 and the journal 20, and the seal ring 30 being located between the first bushing 40 and the second bushing 50 in the axial direction of the journal 20.

By providing the first bushing 40 and the second bushing 50, the journal 20 may be supported while facilitating a reduction in wear between the journal 20 and the wall of the mounting hole 11.

The first and

second bushings

40, 50 may be made of a soft metal or non-metal material that is easily ground.

Through the description of the multiple embodiments of the compressor, the compressor can form a labyrinth passage through the matching of the first sealing part and the second sealing part, and generates larger resistance to airflow, so that the leakage flow is greatly reduced; and the sealing ring is provided with an opening, the outer side surface of the sealing ring can be continuously contacted with the inner wall surface of the mounting hole through micro deformation of the sealing ring, so that high-temperature and high-pressure gas is prevented from being leaked from the interface, the defect that the adjustable stationary blade shaft neck of the gas compressor leaks gas in the main runner is effectively overcome, and the efficiency of the gas compressor is improved.

Based on the compressor, the invention further provides an aircraft engine which comprises the compressor.

The positive technical effects of the compressor in the above embodiments are also applicable to an aircraft engine, and are not described herein again.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made without departing from the principles of the invention, and these modifications and equivalents are intended to be included within the scope of the claims.

Claims

1. A compressor, comprising:

a casing (10) provided with a mounting hole (11);

a vane including a blade body and a journal (20) connected to the blade body, the journal (20) being mounted in the mounting hole (11), an outer periphery of a portion of the journal (20) extending in an axial direction being provided with a first seal portion (21); and

the sealing ring (30) is arranged in the mounting hole (11) and sleeved on the periphery of the shaft neck (20), a second sealing part (311) is arranged on the inner side of the sealing ring (30), and the first sealing part (21) and the second sealing part (311) are matched with each other to form a labyrinth sealing structure;

further comprising a first bushing (40) and a second bushing (50), the first bushing (40) and the second bushing (50) being disposed between a bore wall of the mounting bore (11) and the journal (20), and the seal ring (30) being located between the first bushing (40) and the second bushing (50) in an axial direction of the journal (20);

sealing ring (30) include ring body (31) and set up skeleton (32) inside ring body (31), skeleton (32) are including support ring (321) and set up support plate (322) of support ring (321) inboard, second sealing (311) include a plurality of second recesses and be located adjacent two the second boss between the second recess, support plate (322) certainly support ring (321) extend to the inside of second boss.

2. An air compressor according to claim 1, characterized in that the first sealing portion (21) comprises a plurality of first grooves and a first boss located between two adjacent first grooves.

3. An air compressor according to claim 2, characterized in that the first groove extends from the outer side of the journal (20) towards a direction close to the axis of the journal (20).

4. The compressor of claim 2, wherein the first boss is inserted into the second groove and the second boss is inserted into the first groove.

5. Compressor according to claim 1, characterized in that the skeleton (32) has a hardness greater than that of the ring body (31).

6. Compressor according to claim 1, characterized in that the skeleton (32) comprises a plurality of support plates (322), the support plates (322) being arranged at intervals along the circumference of the support ring (321) or connected in a ring shape along the circumference of the support ring (321).

7. Compressor according to claim 1, characterized in that the skeleton (32) comprises a plurality of support plates (322), the support plates (322) being arranged at intervals in the axial direction of the journal (20).

8. Compressor according to claim 1, characterized in that the sealing ring (30) has an opening (33) in the circumferential direction for bringing the outer side face of the sealing ring (30) into pressing contact with the bore wall of the mounting bore (11) by deformation of the sealing ring (30).

9. An aircraft engine, characterized in that it comprises a compressor as claimed in any one of claims 1 to 8.