CN112145471A - Gas disengaging type combined dynamic sealing device - Google Patents
Gas disengaging type combined dynamic sealing device Download PDFInfo
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- CN112145471A CN112145471A CN202011135669.3A CN202011135669A CN112145471A CN 112145471 A CN112145471 A CN 112145471A CN 202011135669 A CN202011135669 A CN 202011135669A CN 112145471 A CN112145471 A CN 112145471A
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- ring
- corrugated pipe
- shell
- fixedly connected
- shaft
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/106—Shaft sealings especially adapted for liquid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/12—Shaft sealings using sealing-rings
- F04D29/126—Shaft sealings using sealing-rings especially adapted for liquid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Sealing (AREA)
Abstract
The invention discloses a gas disengaging type combined dynamic sealing device, and belongs to the technical field of dynamic sealing of rotary machinery. The gas disengaging type combined dynamic sealing device comprises: the end face sealing mechanism is arranged in the protective shell, can be arranged on the shaft in a sliding manner, and can be contacted with the movable ring; the corrugated pipe seat is sleeved on the shaft; the first end of the corrugated pipe is fixedly connected with the end face sealing mechanism, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat; the air supply mechanism is fixedly connected with the protective shell and is communicated with the air inlet of the corrugated pipe; the floating sealing mechanism is sleeved on the shaft and connected with the air supply mechanism. The gas disengaging type combined dynamic sealing device effectively isolates the propellant in the precooling stage, so that no leakage is realized, the minimum flow loss of the propellant in the working stage can be realized, the efficiency of the turbopump is improved, the dynamic sealing working heating of the floating ring can be cooled, and the safety of the floating ring is ensured.
Description
Technical Field
The invention relates to the technical field of rotary mechanical dynamic sealing, in particular to a gas disengaging type combined dynamic sealing device.
Background
In the liquid rocket engine turbine pump, a dynamic seal is required to effectively separate a low-temperature propellant (fuel or oxidant) from turbine gas, on one hand, in a precooling stage, namely in a non-rotating state of a turbine rotor, the propellant is prevented from entering a turbine side, a turbine rotating part is prevented from frosting and icing under the action of the low-temperature propellant, and a locking fault between the rotating part and a static part occurs.
However, in the prior art, there is no device which can simultaneously achieve effective isolation of the propellant during the precooling stage, preventing the propellant from entering the turbine chamber, and in the operating state, allowing part of the propellant to enter the turbine chamber.
Disclosure of Invention
The invention provides a gas disengaging type combined dynamic sealing device, which solves or partially solves the technical problem that in the prior art, no equipment capable of effectively isolating propellant in a precooling stage and preventing the propellant from entering a turbine cavity and allowing part of the propellant to enter the turbine cavity in a working state is available.
In order to solve the above technical problem, the present invention provides a gas disengaging type combined dynamic sealing device, which is arranged on a shaft, the gas disengaging type combined dynamic sealing device comprising: the device comprises a movable ring, a protective shell, an end face sealing mechanism, a corrugated pipe seat, an air supply mechanism and a floating sealing mechanism; the movable ring is sleeved on the shaft; the end face sealing mechanism is arranged in the protective shell, the end face sealing mechanism is arranged on the shaft in a sliding mode, and the end face sealing mechanism can be in contact with the movable ring; the corrugated pipe seat is sleeved on the shaft; the first end of the corrugated pipe is fixedly connected with the end face sealing mechanism, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat; the air supply mechanism is fixedly connected with the protective shell and is communicated with an air inlet of the corrugated pipe; the floating sealing mechanism is sleeved on the shaft and connected with the gas supply mechanism.
Further, the end face seal mechanism includes: the end faces of the graphite static ring and the graphite static ring seat are sealed; the graphite stationary ring seat is slidably sleeved on the shaft and arranged in the protective shell; the end face seal graphite stationary ring is fixedly arranged in the graphite stationary ring seat, and the end face seal graphite stationary ring can be in contact with the moving ring.
Further, the gas disengaging type combined dynamic sealing device further comprises: a stop mechanism; the stop mechanism is fixedly connected with the end face sealing mechanism; the stop mechanism may be in contact with the protective case.
Further, the stopper mechanism includes: a stop cover plate and a sealing shell; the sealing shell is fixedly connected with the end face sealing mechanism; the stop cover plate is fixedly connected with the sealing shell, and the stop cover plate can be in contact with the protective shell.
Further, the gas supply mechanism includes: a common housing; the public shell is fixedly connected with the protective shell; a first air supply channel is formed in the public shell and communicated with an air inlet of the corrugated pipe.
Further, the end part of the first air supply channel, which deviates from the corrugated pipe, is fixedly provided with a plug.
Further, the gas supply mechanism further includes: a base housing;
the basic shell is fixedly connected with the public shell; a second air supply channel is formed in the base shell and communicated with the first air supply channel.
Furthermore, a sealing aluminum gasket is arranged at the communication position of the second air supply channel and the first air supply channel.
Further, the floating seal mechanism includes: the plug cover, the graphite ring and the floating ring seat; the blocking cover is fixedly connected with the public shell, and a cavity is formed between the blocking cover and the public shell; the floating ring seat is arranged in the cavity, the graphite ring is fixedly arranged on the end face, facing the shaft, of the floating ring seat, and the graphite ring is sleeved on the shaft.
Further, the floating ring seat is connected with the common shell through a wave spring.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
because the movable ring is sleeved on the shaft, the end face sealing mechanism is arranged in the protective shell, the end face sealing mechanism can be arranged on the shaft in a sliding mode, the end face sealing mechanism can be in contact with the movable ring, the corrugated pipe seat is sleeved on the shaft, the first end of the corrugated pipe is fixedly connected with the end face sealing mechanism, the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat, the air supply mechanism is fixedly connected with the protective shell, the air supply mechanism is communicated with an air inlet of the corrugated pipe, the floating sealing mechanism is sleeved on the shaft and is connected with the air supply mechanism, when a rotor of the turbo pump does not rotate in a precooling stage, air is supplied to the corrugated pipe through the air supply mechanism, the corrugated pipe does stretching movement on the corrugated pipe seat, the end face sealing mechanism is pushed to move towards the movable ring on the shaft until the end face sealing mechanism is attached to the movable ring, the propellant can be effectively isolated in the propelling cavity by, the leakage is avoided, when the working state is realized, when a rotor of the turbopump rotates, the gas supply mechanism stops supplying gas to the bellows, the bellows does retraction movement on the bellows seat, the end face sealing mechanism is pulled to move in the direction back to the moving ring on the shaft, the end face sealing mechanism is separated from the moving ring, the end face sealing mechanism and the moving ring generate an axial gap, the propellant cavity has high pressure and low pressure, the propellant can pass through the axial gap at the moment, flows through the end face sealing mechanism and enters the turbine cavity through the floating sealing mechanism, the minimum flow loss of the propellant in the working stage can be realized, the turbopump efficiency is improved, the floating sealing mechanism is guaranteed to work to generate heat and can be cooled, and the safety of the floating sealing mechanism is guaranteed.
Drawings
Fig. 1 is a schematic structural view of a gas disengaging type combined dynamic sealing device according to an embodiment of the present invention.
Detailed Description
Referring to fig. 1, a gas disengaging type combined dynamic sealing device provided by an embodiment of the present invention is disposed on a shaft 1, and includes: the device comprises a movable ring 2, a protective shell 3, an end face sealing mechanism 4, a corrugated pipe 5, a corrugated pipe seat 6, an air supply mechanism 7 and a floating sealing mechanism 8.
The rotating ring 2 is sleeved on the shaft 1.
The end face sealing mechanism 4 is arranged in the protective shell 3, the end face sealing mechanism 4 is arranged on the shaft 1 in a sliding mode, and the end face sealing mechanism 4 can be in contact with the movable ring 2.
The corrugated pipe seat 6 is sleeved on the shaft 1.
The first end of the corrugated pipe 5 is fixedly connected with the end face sealing mechanism 4, and the second end of the corrugated pipe 5 is fixedly connected with the corrugated pipe seat 6.
The floating sealing mechanism 8 is sleeved on the shaft 1, and the floating sealing mechanism 8 is connected with the air supply mechanism 7.
In the embodiment of the application, the movable ring 2 is sleeved on the shaft 1, the end face sealing mechanism 4 is arranged in the protective shell 3, the end face sealing mechanism 4 is slidably arranged on the shaft 1, the end face sealing mechanism 4 can be contacted with the movable ring 2, the corrugated tube seat 6 is sleeved on the shaft 1, the first end of the corrugated tube 5 is fixedly connected with the end face sealing mechanism 4, the second end of the corrugated tube 5 is fixedly connected with the corrugated tube seat 6, the gas supply mechanism 7 is fixedly connected with the protective shell 3, the gas supply mechanism 7 is communicated with the gas inlet of the corrugated tube 5, the floating sealing mechanism 8 is sleeved on the shaft 1, and the floating sealing mechanism 8 is connected with the gas supply mechanism 7, so that when a rotor of the turbine pump does not rotate in a precooling stage, gas is supplied to the corrugated tube 5 through the gas supply mechanism 7, the corrugated tube 5 does stretching movement on the corrugated tube seat 6, and the end face sealing mechanism 4 is, until the end face sealing mechanism 4 is attached to the moving ring 2, the propellant can be effectively isolated in the propelling cavity by end face sealing, the propellant can be effectively isolated by the turbo pump in the precooling stage, no leakage is realized, when the rotor of the turbo pump rotates in the working state, the gas supply mechanism 7 stops supplying gas to the corrugated pipe 5, the corrugated pipe 5 retracts on the corrugated pipe seat 6, the end face sealing mechanism 4 is pulled to move on the shaft 1 in the direction back from the moving ring 2, the end face sealing mechanism 4 is separated from the moving ring 2, the end face sealing mechanism 4 and the moving ring 2 generate an axial gap, the propellant cavity pressure is high, the pressure of the turbine cavity is low, the propellant flows through the axial gap, flows through the end face sealing mechanism 4 and enters the turbine cavity through the floating sealing mechanism 8, the minimum flow loss of the propellant in the working stage can be realized, and the efficiency of the turbo pump is improved, and the floating sealing mechanism is ensured to work, generate heat and can be cooled, and the safety of the floating sealing mechanism is ensured.
Specifically, the end face seal mechanism 4 includes: the end face is sealed with a graphite stationary ring 4-1 and a graphite stationary ring seat 4-2.
The graphite stationary ring seat 4-2 is slidably sleeved on the shaft 1, and the graphite stationary ring seat 4-2 is arranged in the end face sealing shell.
The end face seal graphite stationary ring 4-1 is fixedly arranged in the graphite stationary ring seat 4-2, and the end face seal graphite stationary ring 4-1 can be contacted with the moving ring 2.
When the rotor of the turbine pump does not rotate in the precooling stage, the air supply mechanism 7 supplies air to the corrugated pipe 5, the corrugated pipe 5 makes extension movement on the corrugated pipe seat 6 to push the graphite stationary ring seat 4-2 to move towards the moving ring 2 on the shaft 1 until the end face sealed graphite stationary ring 4-1 is attached to the moving ring 2, the end face seal can effectively isolate the propellant in the propelling cavity, the effective isolation of the propellant in the precooling stage of the turbine pump can be realized, no leakage is realized, when the rotor of the turbine pump rotates in the working state, the air supply mechanism 7 stops supplying air to the corrugated pipe 5, the corrugated pipe 5 makes retraction movement on the corrugated pipe seat 6, the graphite stationary ring seat 4-2 is pulled to move towards the direction away from the moving ring 2 on the shaft 1, the end face sealed graphite stationary ring 4-1 is separated from the moving ring 2, and the end face sealed graphite stationary ring 4-1 and the moving ring 2 generate an axial gap, because the propellant cavity pressure is high, and the turbine cavity pressure is low, the propellant flows through the end face sealing mechanism 4 through the axial gap at the moment, and then enters the turbine cavity through the floating sealing mechanism 8, so that the minimum flow loss of the propellant in the working stage can be realized, the efficiency of the turbopump is improved, the heat generated by the floating sealing mechanism during working can be cooled, and the safety of the floating sealing mechanism is ensured.
When the rotor of the turbopump rotates in a working state, the end face seal graphite static ring 4-1 is not in contact with the moving ring 2, friction cannot be generated between the end face seal graphite static ring 4-1 and the moving ring 2, the service life of the end face seal graphite static ring 4-1 and the moving ring 2 is guaranteed, and equipment loss is reduced.
The clearance between the graphite stationary ring seat 4-2 and the shaft 1 is 0.06-0.16mm, so that the smooth flow of the propellant is ensured.
Specifically, the gas disengaging type combined dynamic sealing device further comprises: a stop mechanism 9.
The stop mechanism 9 is fixedly connected with the end face sealing mechanism 4.
The stop mechanism 9 may be in contact with the protective casing 3.
The stopper mechanism 9 includes: a stop cover plate 9-1 and a sealing shell 9-2.
The sealing shell 9-2 is fixedly connected with the end face sealing mechanism 4. In the embodiment, the sealing shell 9-2 can be fixedly connected with the graphite stationary ring seat 4-2 of the end face sealing mechanism 4 through argon arc welding, so that the connection stability is ensured.
The stop cover plate 9-1 is fixedly connected with the sealing shell 9-2. In the embodiment, the movable cover plate 9-1 can be fixedly connected with the sealing shell 9-2 through a straight-head screw 10, so that the disassembly and the assembly are convenient. The stop cover 9-1 may be in contact with the protective casing 3.
When the rotor of the turbine pump rotates in a working state, the gas supply mechanism 7 stops supplying gas to the corrugated pipe 5, the corrugated pipe 5 retracts on the corrugated pipe seat 6, the stop cover plate 9-1 stops the stop cover plate 9-1 through the protective shell 3 when reaching the protective shell 3, the corrugated pipe 5 is limited, the corrugated pipe 5 is in a certain stretching state, the stretching rate is about 10% -15%, and the corrugated pipe 5 is in the stretching state no matter whether the rotor is in the rotating state or not, so that the corrugated pipe 5 is prevented from being unstable due to flowing disturbance of propellant liquid in a free state.
Specifically, the air supply mechanism 7 includes: a common housing 7-1.
The common shell 7-1 is fixedly connected with the protective shell 3. In the embodiment, the common shell 7-1 can be fixedly connected with the protective shell 3 through a straight-head screw 10, so that the disassembly and the assembly are convenient.
A first air supply channel is arranged in the common shell 7-1 and is communicated with an air inlet of the corrugated pipe 5.
The end part of the first air supply channel, which is far away from the corrugated pipe 5, is fixedly provided with a plug 11 for plugging the common shell 7-1. In the embodiment, the plug 11 and the common shell 7-1 are welded by argon arc welding, so that the connection stability is ensured.
The gas supply mechanism 7 further includes: a base housing 7-2.
The basic housing 7-2 is fixedly connected with the common housing 7-1. In the embodiment, the base shell 7-2 can be fixedly connected with the common shell 7-1 through the spring pad 12 and the bolt fastener 13, so that the assembly and disassembly are convenient.
And a second air supply channel is arranged in the basic shell 7-2 and is communicated with the first air supply channel.
A sealing aluminum gasket 14 is arranged at the communication position of the second gas supply channel and the first gas supply channel to prevent inert gas in the first gas supply channel and the second gas supply channel from leaking.
When the rotor of the turbo pump rotates in the operating state, the inert gas (such as argon or nitrogen) sequentially passes through the second gas supply passage and the first gas supply passage and enters the bellows 5, and the bellows 5 is pushed to extend.
Specifically, the floating seal mechanism 8 includes: 8-1 parts of a blocking cover, 8-2 parts of a graphite ring and 8-3 parts of a floating ring seat.
The blocking cover 8-1 is fixedly connected with the common shell 7-1. In the embodiment, the blocking cover 8-1 can be fixedly connected with the common shell 7-1 through a straight-head screw 10, so that the blocking cover is convenient to disassemble and assemble. The blanking cap 8-1 forms a cavity with the common housing 7-1.
The floating ring seat 8-3 is arranged in the cavity, the graphite ring 8-2 is fixedly arranged on the end face, facing the shaft 1, of the floating ring seat 8-3, and the graphite ring 8-2 is sleeved on the shaft 1.
When the rotor of the turbine pump rotates in a working state, the propellant flows through the end face sealing mechanism 4 through the axial gap and enters the turbine cavity through the graphite ring 8-2, so that the minimum flow loss of the propellant in the working stage can be realized, the efficiency of the turbine pump is improved, the floating sealing mechanism is guaranteed to work and generate heat and can be cooled, and the safety of the floating sealing mechanism is guaranteed.
The floating ring seat 8-3 is connected with the common shell 7-1 through the wave spring 15, so that the end face, facing the plugging cover 8-1, of the floating ring 8-2 is tightly attached to the plugging cover 8-1, propellant is guaranteed to flow from an inner hole of the floating ring to a turbine cavity, and the throttling and pressure reducing effects are achieved.
The distance between the floating ring graphite 7-1 and the shaft 1 is 0.2-1mm, the floating ring graphite 7-1 plays a role in throttling and pressure reduction, the flow loss of the propellant is less, the utilization efficiency of the propellant can be effectively ensured, and the floating ring graphite is well cooled.
The first end of the corrugated pipe 5, the sealing shell 9-2 and the public shell 7-1 are formed by electron beam welding, and the second end of the corrugated pipe 5, the graphite stationary ring seat 4-2 and the corrugated pipe seat 6 are formed by electron beam welding, so that the connection stability is ensured.
In order to more clearly describe the embodiments of the present invention, the following description is made in terms of the method of using the embodiments of the present invention.
When the rotor of the turbopump does not rotate, a certain pressure of inert gas, such as nitrogen or helium, is introduced into the pipe cavity of the corrugated pipe 5 consisting of the double-layer corrugated pipes from the inside to the outside of the second gas supply channel and the first gas supply channel. At the moment, the graphite stationary ring seat 4-2 is pushed by the bellows 5, so that the graphite stationary ring seat 4-2 is pushed to drive the end face seal graphite stationary ring 4-1 to move towards the moving ring 2, and the bellows 5 continues to extend until the end face seal graphite stationary ring 4-1 is tightly attached to the moving ring 2. The end face seal can effectively isolate the propellant in the left propelling cavity and prevent the propellant from leaking to the right turbine cavity.
When the turbo pump rotates, the second gas supply passage and the first gas supply passage do not supply the inert gas to the lumen of the bellows 5 any more, and the gas is removed, and the bellows 5 rebounds. The stop cover 9-1 will contact the protective shell 3, forming a stop, thus ensuring that the bellows 5 is still in a state of tensile elongation, which is about 10% -15%. At the moment, an axial gap exists between the movable ring 2 and the end face seal graphite static ring 4-1, and due to the fact that the pressure of a propellant cavity is high and the pressure of a turbine cavity is low, the propellant passes through the axial gap, sequentially passes through the end face seal graphite static ring 4-1 and the floating ring graphite 7-1 and finally flows to the turbine cavity. Due to the throttling and pressure reducing effects of the floating ring graphite 7-1, the propellant has less flow loss, can effectively ensure the utilization efficiency of the propellant, and has good cooling effect on the floating ring.
When the turbopump stops rotating, a certain pressure of inert gas is led into a pipe cavity of the corrugated pipe 5 consisting of the double-layer corrugated pipes inwards and outwards by the second gas supply channel and the first gas supply channel, so that the movable ring 2 and the end face sealing graphite static ring 4-1 are tightly attached, and the propellant is effectively isolated in a propellant cavity on the left side.
Finally, it should be noted that the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to examples, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the claims of the present invention.
Claims (10)
1. A gas disengaging type combined dynamic sealing device is arranged on a shaft and is characterized by comprising: the device comprises a movable ring, a protective shell, an end face sealing mechanism, a corrugated pipe seat, an air supply mechanism and a floating sealing mechanism;
the movable ring is sleeved on the shaft;
the end face sealing mechanism is arranged in the protective shell, the end face sealing mechanism is arranged on the shaft in a sliding mode, and the end face sealing mechanism can be in contact with the movable ring;
the corrugated pipe seat is sleeved on the shaft;
the first end of the corrugated pipe is fixedly connected with the end face sealing mechanism, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat;
the air supply mechanism is fixedly connected with the protective shell and is communicated with an air inlet of the corrugated pipe;
the floating sealing mechanism is sleeved on the shaft and connected with the gas supply mechanism.
2. The gas disengaging type combined dynamic seal device according to claim 1, wherein the end face seal mechanism includes: the end faces of the graphite static ring and the graphite static ring seat are sealed;
the graphite stationary ring seat is slidably sleeved on the shaft and arranged in the protective shell;
the end face seal graphite stationary ring is fixedly arranged in the graphite stationary ring seat, and the end face seal graphite stationary ring can be in contact with the moving ring.
3. The gas disengaging unitized dynamic seal of claim 1, further comprising: a stop mechanism;
the stop mechanism is fixedly connected with the end face sealing mechanism;
the stop mechanism may be in contact with the protective case.
4. The gas disengaging composite dynamic seal of claim 3, wherein said stop mechanism comprises: a stop cover plate and a sealing shell;
the sealing shell is fixedly connected with the end face sealing mechanism;
the stop cover plate is fixedly connected with the sealing shell, and the stop cover plate can be in contact with the protective shell.
5. The gas disengaging type combined dynamic seal device according to claim 1, wherein the gas supply mechanism comprises: a common housing;
the public shell is fixedly connected with the protective shell;
a first air supply channel is formed in the public shell and communicated with an air inlet of the corrugated pipe.
6. The gas disengaging type combined dynamic sealing device according to claim 5, wherein:
the first gas supply channel deviates from the end part of the corrugated pipe is fixedly provided with a plug.
7. The gas disengaging type combined dynamic seal device according to claim 5, wherein the gas supply mechanism further comprises: a base housing;
the basic shell is fixedly connected with the public shell;
a second air supply channel is formed in the base shell and communicated with the first air supply channel.
8. The gas disengaging type combined dynamic sealing device according to claim 7, wherein:
and a sealing aluminum gasket is arranged at the communication position of the second gas supply channel and the first gas supply channel.
9. The gas disengaging compound dynamic seal of claim 5, wherein the floating seal mechanism comprises: the plug cover, the graphite ring and the floating ring seat;
the blocking cover is fixedly connected with the public shell, and a cavity is formed between the blocking cover and the public shell;
the floating ring seat is arranged in the cavity, the graphite ring is fixedly arranged on the end face, facing the shaft, of the floating ring seat, and the graphite ring is sleeved on the shaft.
10. The gas disengaging type combined dynamic sealing device according to claim 9, wherein:
the floating ring seat is connected with the public shell through a wave spring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011135669.3A CN112145471B (en) | 2020-10-22 | 2020-10-22 | Gas disengaging type combined dynamic sealing device |
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|---|---|---|---|
| CN202011135669.3A CN112145471B (en) | 2020-10-22 | 2020-10-22 | Gas disengaging type combined dynamic sealing device |
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| CN112145471B CN112145471B (en) | 2022-05-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294257A (en) * | 2022-01-17 | 2022-04-08 | 北京化工大学 | Static pressure isolation sealing assembly and method for double-corrugated-pipe type turbo pump |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3495840A (en) * | 1968-01-22 | 1970-02-17 | Borg Warner | Mechanical seal start-up lubricating arrangement |
| EP0222262B1 (en) * | 1985-11-08 | 1990-07-18 | EG & G SEALOL: Société à Responsabilité Limitée dite | Sealing arrangement for a turbo pump |
| US20160177963A1 (en) * | 2013-07-22 | 2016-06-23 | Snecma | Centrifugal pump, in particular for supplying power to rocket engines |
| CN107939722A (en) * | 2017-11-30 | 2018-04-20 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN207647828U (en) * | 2017-11-30 | 2018-07-24 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN109162955A (en) * | 2018-08-28 | 2019-01-08 | 北京航天动力研究所 | Combine automatic disengaging dynamic sealing device in a kind of engine turbine pumps labyrinth |
| US20190032604A1 (en) * | 2012-04-17 | 2019-01-31 | Florida Turbine Technologies, Inc. | Turbopump with a single piece housing and a smooth enamel glass surface |
| CN109737094A (en) * | 2018-11-13 | 2019-05-10 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and gas-turbine-pump combination for turbine pump |
| CN209586768U (en) * | 2018-11-13 | 2019-11-05 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and turbine pump installation for turbine pump |
| CN110985433A (en) * | 2019-12-30 | 2020-04-10 | 蓝箭航天空间科技股份有限公司 | Adjustable and controllable dynamic sealing device for turbine pump and turbine pump set |
| CN213574784U (en) * | 2020-10-22 | 2021-06-29 | 航天科工火箭技术有限公司 | Gas disengaging type combined dynamic sealing device |
-
2020
- 2020-10-22 CN CN202011135669.3A patent/CN112145471B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3495840A (en) * | 1968-01-22 | 1970-02-17 | Borg Warner | Mechanical seal start-up lubricating arrangement |
| EP0222262B1 (en) * | 1985-11-08 | 1990-07-18 | EG & G SEALOL: Société à Responsabilité Limitée dite | Sealing arrangement for a turbo pump |
| US20190032604A1 (en) * | 2012-04-17 | 2019-01-31 | Florida Turbine Technologies, Inc. | Turbopump with a single piece housing and a smooth enamel glass surface |
| US20160177963A1 (en) * | 2013-07-22 | 2016-06-23 | Snecma | Centrifugal pump, in particular for supplying power to rocket engines |
| CN107939722A (en) * | 2017-11-30 | 2018-04-20 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN207647828U (en) * | 2017-11-30 | 2018-07-24 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN109162955A (en) * | 2018-08-28 | 2019-01-08 | 北京航天动力研究所 | Combine automatic disengaging dynamic sealing device in a kind of engine turbine pumps labyrinth |
| CN109737094A (en) * | 2018-11-13 | 2019-05-10 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and gas-turbine-pump combination for turbine pump |
| CN209586768U (en) * | 2018-11-13 | 2019-11-05 | 陕西蓝箭航天技术有限公司 | Dynamic sealing device and turbine pump installation for turbine pump |
| CN110985433A (en) * | 2019-12-30 | 2020-04-10 | 蓝箭航天空间科技股份有限公司 | Adjustable and controllable dynamic sealing device for turbine pump and turbine pump set |
| CN213574784U (en) * | 2020-10-22 | 2021-06-29 | 航天科工火箭技术有限公司 | Gas disengaging type combined dynamic sealing device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294257A (en) * | 2022-01-17 | 2022-04-08 | 北京化工大学 | Static pressure isolation sealing assembly and method for double-corrugated-pipe type turbo pump |
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