CN112096652B - Liquid-release dynamic sealing device - Google Patents
Liquid-release dynamic sealing device Download PDFInfo
- Publication number
- CN112096652B CN112096652B CN202010908058.1A CN202010908058A CN112096652B CN 112096652 B CN112096652 B CN 112096652B CN 202010908058 A CN202010908058 A CN 202010908058A CN 112096652 B CN112096652 B CN 112096652B
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- graphite
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- pressure
- ring seat
- propellant
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- 238000007789 sealing Methods 0.000 title claims abstract description 60
- 239000007788 liquid Substances 0.000 title claims abstract description 30
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 145
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 140
- 239000010439 graphite Substances 0.000 claims abstract description 140
- 230000007246 mechanism Effects 0.000 claims abstract description 133
- 230000003068 static effect Effects 0.000 claims abstract description 115
- 239000003380 propellant Substances 0.000 claims abstract description 106
- 230000000903 blocking effect Effects 0.000 claims description 3
- 238000001816 cooling Methods 0.000 abstract description 11
- 238000010438 heat treatment Methods 0.000 abstract description 3
- 238000002955 isolation Methods 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- 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
-
- 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)
- Sealing Devices (AREA)
- Mechanical Sealing (AREA)
Abstract
The invention discloses a liquid release type dynamic sealing device, and belongs to the technical field of dynamic sealing of rotary machinery. The liquid release type dynamic sealing device comprises: the end face seal graphite static ring is fixedly arranged in the graphite static ring seat, and can be contacted with the movable ring; the first end of the elastic mechanism is fixedly connected with the graphite static ring seat, and the second end of the elastic mechanism is fixedly connected with the end face sealing shell; the propellant supply mechanism is communicated with the end face sealing shell, and a liquid outlet of the propellant supply mechanism is arranged between the pressure mechanism and the graphite static ring seat; the floating sealing mechanism is arranged in the pressure mechanism and sleeved on the shaft. The liquid-disengaging dynamic sealing device can realize the effective isolation of the turbine pump on the propellant in the pre-cooling stage, realize no leakage, realize the minimum flow loss of the propellant in the working stage, improve the efficiency of the turbine pump, ensure that the dynamic sealing working heating of the floating ring can be cooled, and ensure the safety of the floating ring.
Description
Technical Field
The invention relates to the technical field of rotary mechanical dynamic sealing, in particular to a liquid release type dynamic sealing device.
Background
In a liquid rocket engine turbopump, a dynamic seal is needed to effectively separate low-temperature propellant (fuel or oxidant) from turbine gas, so that on one hand, in a precooling stage, namely in a state that a turbine rotor does not rotate, the propellant is prevented from entering a turbine side, a turbine rotating part is frosted and frozen under the action of the low-temperature propellant, a locking fault between the rotating part and a static part occurs, and on the other hand, in a working state, namely in a rotating state of the turbine rotor, only a small amount of propellant flow is allowed to enter the turbine gas side through the dynamic seal, so that excessive propellant loss and waste are avoided, meanwhile, the cooling requirement of the dynamic seal is met, and the dynamic seal is prevented from overheating in the rotating process, so that ablation fault is caused, and the dynamic seal is invalid.
However, in the prior art, there is no device that can simultaneously achieve an effective separation of the propellant during the pre-cooling phase, preventing the propellant from entering the turbine chamber, and in the operating state, letting part of the propellant enter the turbine chamber.
Disclosure of Invention
The invention provides a liquid disengaging dynamic sealing device, which solves or partially solves the technical problems that in the prior art, the device capable of effectively isolating a propellant in a pre-cooling stage and preventing the propellant from entering a turbine cavity is not available at the same time, and in a working state, part of the propellant is allowed to enter the turbine cavity.
In order to solve the above technical problems, the present invention provides a liquid release type dynamic sealing device, which is disposed on a shaft, and the liquid release type dynamic sealing device includes: the device comprises a movable ring, an end face seal shell, an end face seal mechanism, a pressure mechanism, a propellant supply mechanism, a floating seal mechanism and a plug cover; the end face sealing shell is fixedly connected with the blanking cover; the movable ring is fixedly arranged on the shaft; the end face sealing mechanism includes: the end face seals the static graphite ring, the static graphite ring seat and the elastic mechanism; the graphite static ring seat is slidably sleeved on the shaft and is arranged in the end face sealing shell; the end face seal graphite static ring is fixedly arranged in the graphite static ring seat, and can be contacted with the movable ring; the first end of the elastic mechanism is fixedly connected with the graphite static ring seat, and the second end of the elastic mechanism is fixedly connected with the end face sealing shell; the pressure mechanism is slidably arranged in the end face seal shell, a first end of the pressure mechanism can be in contact with the graphite static ring seat, and a second end of the pressure mechanism can be in contact with the blanking cover; the propellant supply mechanism is communicated with the end face sealing shell, and a liquid outlet of the propellant supply mechanism is arranged between the pressure mechanism and the graphite static ring seat; the floating sealing mechanism is arranged in the pressure mechanism, and is sleeved on the shaft.
Further, a labyrinth seal is arranged on the end face of the graphite static ring seat facing the shaft; the clearance between the graphite static ring seat and the shaft is 0.06-0.16mm.
Further, the elastic mechanism includes: bellows and bellows seat; the corrugated pipe seat is fixedly connected with the end face seal shell; the first end of the corrugated pipe is fixedly connected with the graphite static ring seat, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat.
Further, the pressure mechanism includes: a pressure plate and a pressure housing; the first end of the pressure plate can be in contact with the graphite static ring seat, and the second end of the pressure plate is fixedly connected with the pressure shell; the pressure shell is slidably arranged in the end face seal shell, and the pressure shell can be in contact with the blanking cover.
Further, a first bulge is fixedly arranged on the end face, facing the graphite static ring seat, of the pressure plate; the end face of the graphite static ring seat, which faces the pressure plate, is provided with a first groove; the protrusion is slidably disposed within the recess.
Further, the end face, away from the graphite static ring seat, of the pressure plate is connected with the floating sealing mechanism through a wave spring; a spring is arranged between the pressure shell and the blanking cover.
Further, a second groove is formed in the end face, facing the end face sealing shell, of the plug cover, a first graphite pad is fixedly arranged in the second groove, a second protrusion is fixedly arranged on the end face, facing the plug cover, of the end face sealing shell, and the second protrusion is in contact with the first graphite pad; the end face of the blanking cover, which faces the pressure shell, is provided with a third groove, a second graphite pad is fixedly arranged in the third groove, the end face of the pressure shell, which faces the blanking cover, is fixedly provided with a third protrusion, and the third protrusion is in contact with the second graphite pad.
Further, the propellant supply mechanism includes: propellant delivery tube and valve; the propellant conveying pipe is communicated with the end face sealing shell, and a liquid outlet of the propellant conveying pipe is arranged between the pressure mechanism and the graphite static ring seat; the valve is arranged on the propellant conveying pipe.
Further, the floating seal mechanism includes: floating ring graphite and floating ring seat; the floating ring graphite is fixedly arranged on the end face, facing the shaft, of the floating ring seat, and the floating ring graphite is sleeved on the shaft; the floating ring seat is arranged in the pressure mechanism.
Further, the distance between the floating ring graphite and the shaft is 0.2-1mm.
One or more technical solutions provided in the embodiments of the present application at least have the following technical effects or advantages:
Because the end face seal shell is fixedly connected with the blanking cover, the movable ring is fixedly arranged on the shaft, the graphite static ring seat is slidably sleeved on the shaft, the graphite static ring seat is arranged in the end face seal shell, the end face seal graphite static ring is fixedly arranged in the graphite static ring seat, the end face seal graphite static ring can be contacted with the movable ring, the first end of the elastic mechanism is fixedly connected with the graphite static ring seat, the second end of the elastic mechanism is fixedly connected with the end face seal shell, the pressure mechanism is slidably arranged in the end face seal shell, the first end of the pressure mechanism can be contacted with the graphite static ring seat, the second end of the pressure mechanism can be contacted with the blanking cover, the propellant supply mechanism is communicated with the end face seal shell, the liquid outlet of the propellant supply mechanism is arranged between the pressure mechanism and the graphite static ring seat, the floating seal mechanism is arranged in the pressure mechanism, the floating seal mechanism is sleeved on the shaft, therefore, when the rotor of the turbine pump does not rotate in the pre-cooling stage, the elastic mechanism is in an extending state, the elastic mechanism pushes the graphite static ring seat, the graphite static ring seat drives the end face seal graphite static ring to be tightly attached to the movable ring, the propellant supply mechanism keeps a closed state, the end face seal can effectively isolate the propellant in the propulsion cavity, the effective isolation of the propellant of the turbine pump in the pre-cooling stage can be realized, no leakage is realized, when the rotor of the turbine pump rotates in the working state, the propellant supply mechanism is opened, a certain flow of propellant with the pressure similar to that of the propellant cavity is introduced, the propellant acts on the pressure mechanism, the pressure mechanism drives the graphite static ring seat to move together, the pressure mechanism contacts with the blocking cover, the graphite static ring seat drives the end face seal graphite static ring to generate an axial gap with the movable ring, and the pressure of the turbine cavity is low due to the high pressure of the propellant cavity, at the moment, the propellant flows through the axial gap and then flows through the graphite static ring seat and enters the turbine cavity through the floating sealing mechanism, and part of the propellant introduced through the propellant supply mechanism also passes through the gap between the pressure mechanism and the graphite static ring seat and enters the turbine cavity together with the propellant flowing from the propellant cavity through the floating sealing mechanism, 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 working heating of the floating sealing mechanism can be cooled, and the safety of the floating sealing mechanism is ensured.
Drawings
Fig. 1 is a schematic structural diagram of a liquid release type dynamic sealing device according to an embodiment of the present invention.
Detailed Description
Referring to fig. 1, a liquid release type dynamic sealing device provided in an embodiment of the present invention is disposed on a shaft 1, and the liquid release type dynamic sealing device includes: the movable ring 2, the end face seal housing 3, the end face seal mechanism 4, the pressure mechanism 5, the propellant supply mechanism 6, the floating seal mechanism 7 and the blanking cover 8.
The moving ring 2 is fixedly provided on the shaft 1.
The end face seal mechanism 4 includes: the end face seal graphite static ring 4-1, the graphite static ring seat 4-2 and the elastic mechanism 4-3.
The graphite static ring seat 4-2 is slidably sleeved on the shaft 1, and the graphite static ring seat 4-2 is arranged in the end face seal housing 3.
The end face seal graphite static ring 4-1 is fixedly arranged in the graphite static ring seat 4-2, and the end face seal graphite static ring 4-1 can be contacted with the movable ring 2.
The first end of the elastic mechanism 4-3 is fixedly connected with the graphite static ring seat 4-2, and the second end of the elastic mechanism is fixedly connected with the end face seal housing 3.
The pressure mechanism 5 is slidably arranged in the end face seal housing 3, a first end of the pressure mechanism 5 can be in contact with the graphite static ring seat 3-2, and a second end of the pressure mechanism 5 can be in contact with the blanking cover 8.
The propellant supply mechanism 6 is communicated with the end face seal housing 3, and a liquid outlet of the propellant supply mechanism 6 is arranged between the pressure mechanism 5 and the graphite static ring seat 4-2.
The floating sealing mechanism 7 is arranged in the pressure mechanism 5, and the floating sealing mechanism 7 is sleeved on the shaft 1.
In the concrete implementation mode of the application, as the movable ring 2 is fixedly arranged on the shaft 1, the graphite static ring seat 4-2 is slidably sleeved on the shaft 1, the graphite static ring seat 4-2 is arranged in the end face seal shell 3, the end face seal graphite static ring 4-1 is fixedly arranged in the graphite static ring seat 4-2, the end face seal graphite static ring 4-1 can be contacted with the movable ring 2, the first end of the elastic mechanism 4-3 is fixedly connected with the graphite static ring seat 4-2, the second end of the elastic mechanism is fixedly connected with the end face seal shell 3, the pressure mechanism 5 is slidably arranged in the end face seal shell 3, the first end of the pressure mechanism 5 can be contacted with the graphite static ring seat 3-2, the second end of the pressure mechanism 5 can be contacted with the blanking cover 8, the propellant supply mechanism 6 is communicated with the end face seal shell 3, the liquid outlet of the propellant supply mechanism 6 is arranged between the pressure mechanism 5 and the graphite static ring seat 4-2, the floating seal mechanism 7 is arranged in the pressure mechanism 5, the floating seal mechanism 7 is sleeved on the shaft 1, therefore, when the rotor of the turbine pump does not rotate in the pre-cooling stage, the elastic mechanism 4-3 is in an extending state, the elastic mechanism 4-3 pushes the graphite static ring seat 4-2, the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 to be tightly attached to the movable ring 2, the propellant supply mechanism 6 is kept in a closed state, the end face seal can effectively isolate the propellant in the propulsion cavity, the turbine pump can effectively isolate the propellant in the pre-cooling stage, no leakage is realized, when the rotor of the turbine pump rotates in the working state, the propellant supply mechanism 6 is opened, and a certain flow of propellant with the pressure close to the pressure of the propellant cavity is introduced, the propellant acts on the pressure mechanism 5, the pressure mechanism 5 drives the graphite static ring seat 4-2 to move together, the pressure mechanism 5 is contacted with the blanking cover 8, the graphite static ring seat 4-2 drives the end face to seal the graphite static ring 4-1 and the movable ring 2 to generate an axial gap, the propellant cavity is high in pressure, the pressure of the turbine cavity is low, at the moment, the propellant passes through the axial gap and flows through the graphite static ring seat 4-2 and enters the turbine cavity through the floating sealing mechanism 7, part of the propellant introduced through the propellant supply mechanism 6 also passes through the gap between the pressure mechanism 5 and the graphite static ring seat 4-2, and enters the turbine cavity through the floating sealing mechanism 7 together with the propellant flowing from the propellant cavity, 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 working heating of the floating sealing mechanism can be cooled, and the safety of the floating sealing mechanism is ensured.
When the rotor of the turbine pump rotates in a working state, the end face seal graphite static ring 4-1 is not in contact with the movable ring 2, friction is not generated between the end face seal graphite static ring 4-1 and the movable ring 2, the service lives of the end face seal graphite static ring 4-1 and the movable ring 2 are guaranteed, and equipment loss is reduced.
Specifically, a labyrinth seal is arranged on the end face of the graphite static ring seat 4-2 facing the shaft 1; the clearance between the graphite static ring seat 4-2 and the shaft 1 is 0.06-0.16mm, the function of throttling and reducing pressure is achieved through labyrinth seal, the flow loss of the propellant is small, and the utilization efficiency of the propellant can be effectively ensured.
Specifically, the elastic mechanism 4-3 includes: bellows 4-31 and bellows holder 4-32.
The bellows seats 4-32 are fixedly connected with the end face seal housing 3.
The first end of the corrugated pipe 4-31 is fixedly connected with the graphite static ring seat 4-2, and the second end of the corrugated pipe 4-31 is fixedly connected with the corrugated pipe seat 4-32.
When the rotor of the turbine pump does not rotate in the pre-cooling stage, the corrugated pipe 4-31 stretches, the second end of the corrugated pipe 4-31 pushes the corrugated pipe seat 4-32, and the first end of the corrugated pipe 4-31 pushes the graphite static ring seat 4-2, so that the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 to be tightly attached to the movable ring 2. When the rotor of the turbine pump rotates in a working state, the pressure mechanism 5 drives the graphite static ring seat 4-2 to move together, and the graphite static ring seat 4-2 compresses the corrugated pipe 4-31, so that an axial gap is formed between the end face seal graphite static ring 4-1 and the movable ring 2.
Specifically, the pressure mechanism 5 includes: the pressure plate 5-1 and the pressure housing 5-2.
The first end of the pressure plate 5-1 can be in contact with the graphite static ring seat 4-2, and the second end of the pressure plate 5-1 is fixedly connected with the pressure shell 5-2. In this embodiment, the second end of the pressure plate 5-1 may be fixedly connected to the pressure housing 5-2 by the socket head cap screw 14 and the spring washer 11, so as to ensure the stability of connection.
The pressure shell 5-2 is slidably disposed within the face seal housing 3, and the pressure shell 5-2 is contactable with the blanking cover 8.
The end face of the pressure plate 5-1 facing the graphite static ring seat 4-2 is fixedly provided with a first bulge.
The end surface of the graphite static ring seat 4-2 facing the pressure plate 5-1 is provided with a first groove.
The protrusion is slidably disposed within the recess.
The end surface of the pressure plate 5-1, which is away from the graphite static ring seat 4-2, is connected with the floating sealing mechanism 7 through a wave spring 9.
A spring 10 is arranged between the pressure shell 5-2 and the blanking cover 8.
When the rotor of the turbine pump rotates in the working state, the propellant supply mechanism 6 is opened, propellant with a certain flow rate which is similar to the pressure of the propellant cavity is introduced, the propellant enters the end face seal shell 3, reaches between the pressure mechanism 5 and the graphite static ring seat 4-2 and acts on the pressure plate 5-1, a first bulge on the pressure plate 5-1 hooks the first groove, the graphite static ring seat 4-2 is pulled, and the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 and the movable ring 2 to generate an axial gap. Meanwhile, the end face compression wave spring 9 of the pressure plate 5-1, which is away from the graphite static ring seat 4-2, is in contact with the floating sealing mechanism 7, and the pressure shell 5-2 compresses the spring 10 and the blanking cover 8. When the rotor of the turbine pump does not rotate in the pre-cooling stage, the propellant supply mechanism 6 is closed, and at the moment, the propellant cannot flow into the end face seal housing 3 through the propellant supply mechanism 6 any more, and reaches between the pressure mechanism 5 and the graphite stationary ring seat 4-2, the pressure is reduced along with the propellant supply mechanism, the wave spring 9 and the spring 10 stretch, the pressure plate 5-1 and the pressure housing 5-2 are respectively pushed, and the first groove is not hooked by the first protrusion on the pressure plate 5-1, so that the graphite stationary ring seat 4-2 is convenient to reset.
The end face of the end face seal shell 3 facing the blanking cover 8 is provided with a second groove, a first graphite pad 12 is fixedly arranged in the second groove, the end face of the end face seal shell 3 facing the blanking cover 8 is fixedly provided with a second protrusion, the second protrusion is in contact with the first graphite pad 12, and the end face seal shell 3 and the blanking cover 8 are sealed through the first graphite pad 12.
Wherein, blanking cover 8 accessible anti-rotation pin 15 and terminal surface seal housing 3 fixed connection guarantee the stability of connection.
The end face of the blanking cover 8, which faces the pressure shell 5-2, is provided with a third groove, a second graphite pad 13 is fixedly arranged in the third groove, the end face of the pressure shell 5-2, which faces the blanking cover 8, is fixedly provided with a third protrusion, the third protrusion is in contact with the second graphite pad 13, the blanking cover 8 and the pressure shell 5-2 are sealed, meanwhile, buffering can be carried out, and part safety is guaranteed.
Specifically, the propellant supply mechanism 6 includes: propellant delivery tube 6-1 and valve 6-2.
The propellant conveying pipe 6-1 is communicated with the end face sealing shell 3, and a liquid outlet of the propellant conveying pipe 6-1 is arranged between the pressure mechanism 5 and the graphite static ring seat 4-2.
The valve 6-2 is provided on the propellant feed tube 6-1.
When the rotor of the turbine pump rotates in the working state, the valve 6-2 is opened, a certain flow of propellant with the pressure similar to that of the propellant cavity is introduced, the propellant enters the end face seal shell 3 through the propellant conveying pipe 6-1, reaches between the pressure plate 5-1 and the graphite static ring seat 4-2, and acts on the pressure plate 5-1.
Specifically, the floating seal mechanism 7 includes: floating ring graphite 7-1 and floating ring seat 7-2.
The floating ring graphite 7-1 is fixedly arranged on the end face of the floating ring seat 7-2, facing the shaft 1, and the floating ring graphite 7-1 is sleeved on the shaft 1.
The floating ring seat 7-2 is provided in the pressure mechanism 5.
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 depressurization, the flow loss of the propellant is small, the utilization efficiency of the propellant can be effectively ensured, and the floating ring graphite has a good cooling effect.
In order to more clearly describe the embodiments of the present invention, the following description is made on the method of using the embodiments of the present invention.
When the rotor of the turbine pump does not rotate, the corrugated pipe 4-31 stretches, the second end of the corrugated pipe 4-31 pushes the corrugated pipe seat 4-32, the first end of the corrugated pipe 4-31 pushes the graphite static ring seat 4-2, and the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 to be tightly attached to the movable ring 2, and the valve 6-2 keeps a closed state. The end face seal is effective to isolate the propellant from the propellant cavity at this point.
When the rotor of the turbine pump rotates, the valve 6-2 is opened, propellant with a certain flow rate, which is similar to the pressure of the propellant cavity, is introduced, the propellant enters the end face seal shell 3 through the propellant conveying pipe 6-1, reaches between the pressure plate 5-1 and the graphite static ring seat 4-2, acts on the pressure plate 5-1, the first protrusion on the pressure plate 5-1 hooks the first groove, the graphite static ring seat 4-2 is pulled, the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 and the movable ring 2 to generate an axial gap, and at the moment, the corrugated pipe 4-31 contracts. The end face compression wave spring 9 of the pressure plate 5-1, which is away from the graphite static ring seat 4-2, is contacted with the floating ring seat 7-2, and the compression spring 10 of the pressure shell 5-2 is contacted with the blanking cover 8. Meanwhile, the pressure plate 5-1 moves with the graphite static ring seat 4-2, the end face sealing graphite static ring 4-1 and the movable ring 2 generate an axial gap, and the propellant cavity is high in pressure and the turbine cavity is low in pressure, so that the propellant passes through the axial gap, flows through the labyrinth seal and enters the turbine cavity through the floating ring seal formed by the floating ring graphite 7-1 and the floating ring seat 7-2. The propellant introduced through the propellant delivery tube 6-1 also has a portion passing through the gap between the pressure plate 5-1 and the stationary graphite ring seat 4-2 and entering the turbine chamber through the floating ring seal together with the propellant flowing from the propellant chamber. The flow loss of the propellant is less due to the throttling and depressurization effects of the labyrinth seal and the floating ring, so that the utilization efficiency of the propellant can be effectively ensured, and the floating ring is well cooled.
When the rotor stops rotating, the valve 6-2 is closed, at the moment, the propellant can not flow in through the propellant conveying pipe 6-1, the pressure is reduced along with the propellant, the corrugated pipe 4-31 stretches, the second end of the corrugated pipe 4-31 pushes the corrugated pipe seat 4-32, the first end of the corrugated pipe 4-31 pushes the graphite static ring seat 4-2, the graphite static ring seat 4-2 drives the end face seal graphite static ring 4-1 to be tightly attached to the movable ring 2, and the valve 6-2 keeps a closed state. At this point, the end face seal may effectively isolate the propellant from the propellant cavity.
Finally, it should be noted that the above-mentioned embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same, 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 and equivalents may be made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention, and all such modifications and equivalents are intended to be encompassed in the scope of the claims of the present invention.
Claims (8)
1. A liquid release type dynamic sealing device provided on a shaft, characterized in that the liquid release type dynamic sealing device comprises: the device comprises a movable ring, an end face seal shell, an end face seal mechanism, a pressure mechanism, a propellant supply mechanism, a floating seal mechanism and a plug cover;
the end face sealing shell is fixedly connected with the blanking cover;
The movable ring is fixedly arranged on the shaft;
The end face sealing mechanism includes: the end face seals the static graphite ring, the static graphite ring seat and the elastic mechanism;
the graphite static ring seat is slidably sleeved on the shaft and is arranged in the end face sealing shell;
the end face seal graphite static ring is fixedly arranged in the graphite static ring seat, and can be contacted with the movable ring;
The first end of the elastic mechanism is fixedly connected with the graphite static ring seat, and the second end of the elastic mechanism is fixedly connected with the end face sealing shell;
The pressure mechanism is slidably arranged in the end face seal shell, a first end of the pressure mechanism can be in contact with the graphite static ring seat, and a second end of the pressure mechanism can be in contact with the blanking cover;
The propellant supply mechanism is communicated with the end face sealing shell, and a liquid outlet of the propellant supply mechanism is arranged between the pressure mechanism and the graphite static ring seat;
The floating sealing mechanism is arranged in the pressure mechanism and sleeved on the shaft;
The pressure mechanism includes: a pressure plate and a pressure housing;
the first end of the pressure plate can be in contact with the graphite static ring seat, and the second end of the pressure plate is fixedly connected with the pressure shell;
the pressure shell is slidably arranged in the end face sealing shell and can be in contact with the blanking cover;
the end face of the end face sealing shell facing the blocking cover is provided with a second groove, a first graphite pad is fixedly arranged in the second groove, the end face of the end face sealing shell facing the blocking cover is fixedly provided with a second protrusion, and the second protrusion is in contact with the first graphite pad;
The end face of the blanking cover, which faces the pressure shell, is provided with a third groove, a second graphite pad is fixedly arranged in the third groove, the end face of the pressure shell, which faces the blanking cover, is fixedly provided with a third protrusion, and the third protrusion is in contact with the second graphite pad.
2. The liquid shedding dynamic sealing device of claim 1, wherein:
The end face of the graphite static ring seat, which faces the shaft, is provided with a labyrinth seal;
the clearance between the graphite static ring seat and the shaft is 0.06-0.16mm.
3. The liquid shedding dynamic seal device of claim 1, wherein the elastic mechanism comprises: bellows and bellows seat;
The corrugated pipe seat is fixedly connected with the end face seal shell;
The first end of the corrugated pipe is fixedly connected with the graphite static ring seat, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat.
4. The liquid shedding dynamic sealing device of claim 1, wherein:
a first bulge is fixedly arranged on the end face of the pressure plate, which faces the graphite static ring seat;
The end face of the graphite static ring seat, which faces the pressure plate, is provided with a first groove;
The protrusion is slidably disposed within the recess.
5. The liquid shedding dynamic sealing device of claim 1, wherein:
The end face, away from the graphite static ring seat, of the pressure plate is connected with the floating sealing mechanism through a wave spring;
A spring is arranged between the pressure shell and the blanking cover.
6. The liquid break-away dynamic sealing device of claim 1, wherein said propellant supply mechanism comprises: propellant delivery tube and valve;
the propellant conveying pipe is communicated with the end face sealing shell, and a liquid outlet of the propellant conveying pipe is arranged between the pressure mechanism and the graphite static ring seat;
The valve is arranged on the propellant conveying pipe.
7. The liquid shedding dynamic seal device of claim 1, wherein the floating seal mechanism comprises: floating ring graphite and floating ring seat;
the floating ring graphite is fixedly arranged on the end face, facing the shaft, of the floating ring seat, and the floating ring graphite is sleeved on the shaft;
The floating ring seat is arranged in the pressure mechanism.
8. The liquid shedding dynamic sealing device of claim 7, wherein:
The distance between the floating ring graphite and the shaft is 0.2-1mm.
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