CN216518804U

CN216518804U - Combined sealing device for turbopump of liquid rocket engine

Info

Publication number: CN216518804U
Application number: CN202123334724.4U
Authority: CN
Inventors: 王宇擎; 周源; 王陆军; 阴海波
Original assignee: Hebei Qinghang Precision Machinery Manufacturing Co ltd
Current assignee: Hebei Qinghang Precision Machinery Manufacturing Co ltd
Priority date: 2021-12-28
Filing date: 2021-12-28
Publication date: 2022-05-13
Anticipated expiration: 2031-12-28

Abstract

The utility model discloses a combined sealing device for a turbo pump of a liquid rocket engine, which belongs to the technical field of turbo pumps of liquid rocket engines and comprises a rotating shaft and a sealing shell, wherein the sealing shell is arranged on the outer side of the rotating shaft, a spring seat is arranged on the outer side of the rotating shaft and positioned on the inner side of the sealing shell, a dry gas seal is arranged at one end, close to the inner side of the sealing shell, of the spring seat, a spring, a push ring, a moving ring and a static ring are sequentially arranged on the dry gas seal along the inner side direction of the sealing shell through the spring seat, and a sealing gas inlet communicated with the dry gas seal is formed in the outer side of the sealing shell.

Description

Combined sealing device for turbopump of liquid rocket engine

Technical Field

The utility model relates to the technical field of turbopumps of liquid rocket engines, in particular to a combined sealing device for a turbopump of a liquid rocket engine.

Background

The liquid rocket engine refers to a liquid propellant rocket engine, namely a chemical rocket propulsion system using liquid chemical substances as energy sources and working media. The turbopump is an important component of a liquid rocket engine, the engine is the heart of the rocket, and the turbopump is the heart of the engine and mainly used for pressurizing fuel and then sending the pressurized fuel into a combustion chamber of the engine to be combusted to generate thrust. At present, high-temperature gas generated by fuel combustion in a turbopump is easy to leak, so that a sealing structure is deformed, a medium is vaporized, and the effective sealing performance of the sealing after operation is influenced.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a combined sealing device for a turbo pump of a liquid rocket engine, which aims to solve the problems in the background technology.

In order to achieve the purpose, the utility model provides the following technical scheme: the utility model provides a combination sealing device for liquid rocket engine turbo pump, includes pivot and seal housing, seal housing sets up the outside of pivot, the outside of pivot is located seal housing's inboard is provided with the spring holder, the spring holder is close to seal housing inboard one end is provided with the dry gas and seals, the dry gas is sealed has set gradually spring, throw-out collar, rotating ring and quiet ring along seal housing inboard direction by the spring holder, seal housing's the outside seted up with the sealed gas inlet that communicates each other of dry gas seal.

Preferably, one side of the movable ring close to the stationary ring is provided with a sealing end surface structure, the sealing end surface structure comprises a sealing dam and dynamic pressure grooves, and the number of the dynamic pressure grooves is provided with a plurality of groups.

Preferably, the depth of the dynamic pressure grooves is set to be millimeter, and a plurality of groups of the dynamic pressure grooves are arranged on the sealing dam in an annular array.

Preferably, an anti-rotation pin is arranged between the stationary ring and the seal housing.

Preferably, a spring seat sealing ring is arranged between the spring seat and the outer side of the rotating shaft.

Preferably, a moving ring sealing ring is arranged between the moving ring and the push ring, and a static ring sealing ring is arranged between the static ring and the inner side of the sealing shell.

Preferably, an end cover is arranged at one end of the spring seat close to the outer side of the seal housing, and the end cover is installed on the seal housing through a fixing pin.

Compared with the prior art, the utility model has the beneficial effects that:

1. according to the utility model, sealing gas is introduced into the dry gas seal through the sealing gas inlet, so that the movable ring is driven to push the push ring to extrude the spring, a stable gas film sealing surface is formed between the movable ring and the static ring, the movable ring and the static ring are prevented from being contacted to generate friction damage during operation, meanwhile, the sealing gas enters the dynamic pressure groove on the movable ring, the sealing gas is compressed through the rotating dynamic pressure groove, the pressure of the sealing surface is further increased, the gas film sealing surface is not easy to damage, and the sealing performance is further improved.

2. According to the utility model, the spring seat sealing ring is arranged between the spring seat and the rotating shaft, the moving ring sealing ring is arranged between the moving ring and the push ring, and the static ring sealing ring is arranged between the static ring and the sealing shell, so that the sealing is tighter, the sealing performance is improved, and the connection between the dry gas seal and the sealing shell is more stable by arranging the end cover between the dry gas seal and the outer side of the sealing shell.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the sealing moving ring structure of the present invention.

In the figure: 1. a rotating shaft; 2. sealing the housing; 3. sealing with dry gas; 4. a spring seat; 5. a spring; 6. a push ring; 7. a moving ring; 71. sealing the dam; 72. a dynamic pressure groove; 8. a stationary ring; 9. sealing the gas inlet; 10. an anti-rotation pin; 11. a spring seat seal ring; 12. a moving ring sealing ring; 13. a stationary ring seal ring; 14. an end cap; 15. and fixing the pin.

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 of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Example 1:

referring to fig. 1, the present invention provides a technical solution: the utility model provides a combination sealing device for liquid rocket engine turbo pump, including pivot 1 and seal housing 2, seal housing 2 sets up the outside at pivot 1, the inboard that the outside of pivot 1 is located seal housing 2 is provided with spring holder 4, spring holder 4 is provided with dry gas seal 3 near the one end of seal housing 2 inboard, dry gas seal 3 has set gradually spring 5 along seal housing 2 inboard direction by spring holder 4, throw-out collar 6, rotating ring 7 and quiet ring 8, seal housing 2's the outside is seted up with the sealed gas inlet 9 that 3 communicate each other of dry gas.

In this embodiment, referring to fig. 1 and fig. 2, a sealing end surface structure is disposed on one side of the moving ring 7 close to the stationary ring 8, the sealing end surface structure includes a sealing dam 71 and dynamic pressure grooves 72, the number of the dynamic pressure grooves 72 is provided with a plurality of groups, the depth of the dynamic pressure grooves 72 is set to 5 mm, and the plurality of groups of dynamic pressure grooves 72 are disposed on the sealing dam 71 in an annular array.

In this embodiment, referring to fig. 1, a spring seat sealing ring 11 is disposed between the spring seat 4 and the outer side of the rotating shaft 1, a moving ring sealing ring 12 is disposed between the moving ring 7 and the push ring 6, a stationary ring sealing ring 13 is disposed between the stationary ring 8 and the inner side of the sealing housing 2, and the sealing is tighter by the spring seat sealing ring 11, the moving ring sealing ring 12, and the stationary ring sealing ring 13, so that the sealing performance is improved.

In this embodiment, referring to fig. 1, an end cover 14 is disposed at one end of the spring seat 4 close to the outer side of the sealed housing 2, the end cover 14 is mounted on the sealed housing 2 through a fixing pin 15, and the connection between the dry gas seal and the sealed housing is more stable through the disposed end cover 14.

The working principle is as follows: seal gas is leading-in to the dry gas seal 3 through sealed gas inlet 9 in, and then drive rotating ring 7 and promote throw-out collar 6 and extrude spring 5, make to form a stable air film seal face between rotating ring 7 and the quiet ring 8, rotating ring 7 and quiet ring 8 take place to contact when avoiding operating and produce the friction damage, simultaneously sealed gas gets into the dynamic pressure groove 72 on the rotating ring 7, compress sealed gas through rotatory dynamic pressure groove 72, and then increase the pressure of sealed face, make the sealed face of air film difficult quilt destroy, and then improve the leakproofness.

Example 2:

referring to fig. 1, this embodiment is different from the first embodiment in that: an anti-rotation pin 10 is arranged between the static ring 8 and the sealing shell 2, and the static ring 8 and the sealing shell 2 can be prevented from being damaged by friction in the operation process through the anti-rotation pin 10.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a combination sealing device for liquid rocket engine turbo pump, includes pivot (1) and seal housing (2), its characterized in that: seal housing (2) sets up the outside of pivot (1), the outside of pivot (1) is located seal housing's (2) inboard is provided with spring holder (4), spring holder (4) are close to seal housing's (2) inboard one end is provided with dry gas seal (3), dry gas seal (3) have set gradually spring (5), throw-out collar (6), rotating ring (7) and quiet ring (8) along seal housing (2) inboard direction by spring holder (4), seal housing's (2) the outside seted up with seal gas import (9) that dry gas seal (3) communicate each other.

2. The composite sealing device for a turbo pump of a liquid rocket engine according to claim 1, wherein: one side of the movable ring (7) close to the stationary ring (8) is provided with a sealing end surface structure, the sealing end surface structure comprises a sealing dam (71) and dynamic pressure grooves (72), and the number of the dynamic pressure grooves (72) is provided with a plurality of groups.

3. The combined sealing device for the turbopump of the liquid rocket engine according to claim 2, wherein: the depth of the dynamic pressure grooves (72) is set to be 5 mm, and a plurality of groups of dynamic pressure grooves (72) are arranged on the sealing dam (71) in an annular array.

4. The composite sealing device for a turbo pump of a liquid rocket engine according to claim 1, wherein: an anti-rotation pin (10) is arranged between the static ring (8) and the sealing shell (2).

5. The composite sealing device for a turbo pump of a liquid rocket engine according to claim 1, wherein: a spring seat sealing ring (11) is arranged between the spring seat (4) and the outer side of the rotating shaft (1).

6. The composite sealing device for a turbo pump of a liquid rocket engine according to claim 1, wherein: a moving ring sealing ring (12) is arranged between the moving ring (7) and the push ring (6), and a static ring sealing ring (13) is arranged between the static ring (8) and the inner side of the sealing shell (2).

7. The composite sealing device for a turbo pump of a liquid rocket engine according to claim 1, wherein: one end, close to the outer side of the sealing shell (2), of the spring seat (4) is provided with an end cover (14), and the end cover (14) is installed on the sealing shell (2) through a fixing pin (15).