CN112096652A - Liquid disengaging type dynamic sealing device - Google Patents
Liquid disengaging type dynamic sealing device Download PDFInfo
- Publication number
- CN112096652A CN112096652A CN202010908058.1A CN202010908058A CN112096652A CN 112096652 A CN112096652 A CN 112096652A CN 202010908058 A CN202010908058 A CN 202010908058A CN 112096652 A CN112096652 A CN 112096652A
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- graphite
- pressure
- ring seat
- face
- propellant
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- 238000007789 sealing Methods 0.000 title claims abstract description 96
- 239000007788 liquid Substances 0.000 title claims abstract description 28
- 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 145
- 239000010439 graphite Substances 0.000 claims abstract description 145
- 230000007246 mechanism Effects 0.000 claims abstract description 132
- 239000003380 propellant Substances 0.000 claims abstract description 100
- 230000003068 static effect Effects 0.000 claims description 27
- 230000000903 blocking effect Effects 0.000 claims description 11
- 238000002955 isolation Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000001603 reducing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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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
Abstract
The invention discloses a liquid disengaging type dynamic sealing device, and belongs to the technical field of dynamic sealing of rotary machinery. The liquid-disengaging dynamic sealing device includes: the end face sealing graphite stationary ring is fixedly arranged in the graphite stationary ring seat and can be contacted with the moving ring; the first end of the elastic mechanism is fixedly connected with the graphite stationary 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 stationary ring seat; the floating sealing mechanism is arranged in the pressure mechanism and sleeved on the shaft. The liquid disengaging type dynamic sealing device can realize effective isolation of the propellant during the precooling stage of the turbopump, has no leakage, can realize minimum flow loss of the propellant during the working stage, improves the efficiency of the turbopump, ensures that the dynamic sealing work of the floating ring can be cooled, and ensures 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 disengaging type 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 liquid disengaging type 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 liquid disengaging type dynamic sealing device, which is provided on a shaft, the liquid disengaging type dynamic sealing device comprising: the device comprises a movable ring, an end face sealing shell, an end face sealing mechanism, a pressure mechanism, a propellant supply mechanism, a floating sealing mechanism and a plugging cover; the end face sealing shell is fixedly connected with the plug cover; the movable ring is fixedly arranged on the shaft; the end face sealing mechanism includes: the end face is sealed with a graphite static ring, a graphite static ring seat and an elastic mechanism; the graphite stationary ring seat is slidably sleeved on the shaft and arranged in the end face sealing shell; the end face seal graphite stationary ring is fixedly arranged in the graphite stationary ring seat and can be contacted with the moving ring; the first end of the elastic mechanism is fixedly connected with the graphite stationary 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 sealing 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 stationary ring seat; the floating sealing mechanism is arranged in the pressure mechanism and sleeved on the shaft.
Furthermore, a labyrinth seal is arranged on the end face, facing the shaft, of the graphite stationary ring seat; the clearance between the graphite stationary ring seat and the shaft is 0.06-0.16 mm.
Further, the elastic mechanism includes: a corrugated pipe and a corrugated pipe seat; the corrugated pipe seat is fixedly connected with the end face sealing shell; the first end of the corrugated pipe is fixedly connected with the graphite stationary 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 contacted 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 the pressure shell can be contacted with the plug cover.
Furthermore, a first bulge is fixedly arranged on the end face, facing the graphite stationary ring seat, of the pressure plate; a first groove is formed in the end face, facing the pressure plate, of the graphite stationary ring seat; the projection is slidably disposed within the recess.
Further, the end face, away from the graphite stationary ring seat, of the pressure plate is connected with the floating sealing mechanism through a wave spring; and a spring is arranged between the pressure shell and the blocking cover.
Furthermore, a second groove is formed in the end face, facing the end face sealing shell, of the blocking cover, a first graphite pad is fixedly arranged in the second groove, a second protrusion is fixedly arranged on the end face, facing the blocking cover, of the end face sealing shell, and the second protrusion is in contact with the first graphite pad; the blanking cover orientation the third recess has been seted up on pressure housing's the terminal surface, the third recess internal fixation is provided with the second graphite pad, pressure housing orientation the fixed third arch that is provided with on the terminal surface of blanking cover, the third arch with the contact of second graphite pad.
Further, the propellant supply mechanism includes: propellant delivery lines and valves; 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 stationary ring seat; the valve is disposed on the propellant delivery tube.
Further, the floating seal mechanism includes: floating ring graphite and a 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 0.2-1 mm.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
because the end face sealing shell is fixedly connected with the plug cover, the movable ring is fixedly arranged on the shaft, the graphite stationary ring seat is slidably sleeved on the shaft, the graphite stationary ring seat is arranged in the end face sealing shell, the end face sealing graphite stationary ring is fixedly arranged in the graphite stationary ring seat, the end face sealing graphite stationary ring can be contacted with the movable ring, the first end of the elastic mechanism is fixedly connected with the graphite stationary ring seat, 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 sealing shell, the first end of the pressure mechanism can be contacted with the graphite stationary ring seat, the second end of the pressure mechanism can be contacted with the plug cover, the propellant supply mechanism is communicated with the end face sealing shell, the liquid outlet of the propellant supply mechanism is arranged between the pressure mechanism and the graphite stationary ring seat, the floating sealing mechanism is arranged in the pressure mechanism, and the floating sealing mechanism is sleeved on the shaft, when the rotor of the turbine pump does not rotate in a precooling stage, the elastic mechanism is in a stretching state, the elastic mechanism pushes the graphite stationary ring seat, the graphite stationary ring seat drives the end face sealing graphite stationary ring to be tightly attached to the movable ring, the propellant supply mechanism keeps a closing state, the end face sealing 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 a working state, the propellant supply mechanism is opened, a certain flow of propellant with the pressure similar to the pressure of the propellant cavity is introduced, the propellant acts on the pressure mechanism, the pressure mechanism drives the graphite stationary ring seat to move together, the pressure mechanism is contacted with the plugging cover, the graphite stationary ring seat drives the end face sealing graphite stationary ring and the movable ring to generate an axial gap, and the propellant passes through the axial gap at the moment, the static ring seat of graphite of flowing through again enters into the turbine chamber through floating seal mechanism, the propellant that introduces through propellant feed mechanism also has partly through the gap between pressure mechanism and the static ring seat of graphite, the propellant that flows with the propellant chamber flows and comes together the rethread floating seal mechanism and enters into the turbine chamber, can realize the minimum flow loss of working phase propellant, improve turbopump efficiency, and guarantee that the floating seal mechanism work generates heat and can be cooled off, guarantee the security of floating seal mechanism.
Drawings
Fig. 1 is a schematic structural view of a liquid-disengaging dynamic sealing device according to an embodiment of the present invention.
Detailed Description
Referring to fig. 1, a liquid-disengaging dynamic sealing device provided by an embodiment of the present invention is disposed on a shaft 1, and includes: the sealing device comprises a movable ring 2, an end face sealing shell 3, an end face sealing mechanism 4, a pressure mechanism 5, a propellant supply mechanism 6, a floating sealing mechanism 7 and a plugging cover 8.
The rotating ring 2 is fixedly arranged on the shaft 1.
The end face seal mechanism 4 includes: the end face sealing graphite stationary ring 4-1, the graphite stationary ring seat 4-2 and the elastic mechanism 4-3.
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 3.
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.
The first end of the elastic mechanism 4-3 is fixedly connected with the graphite stationary ring seat 4-2, and the second end of the elastic mechanism is fixedly connected with the end face sealing shell 3.
The pressure mechanism 5 is slidably disposed in the end face sealing housing 3, a first end of the pressure mechanism 5 may contact with the graphite stationary ring seat 3-2, and a second end of the pressure mechanism 5 may contact with the blanking cover 8.
The propellant supply mechanism 6 is communicated with the end face sealing shell 3, and a liquid outlet of the propellant supply mechanism 6 is arranged between the pressure mechanism 5 and the graphite stationary 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 embodiment of the application, the movable ring 2 is fixedly arranged on the shaft 1, the graphite stationary ring seat 4-2 is slidably sleeved on the shaft 1, the graphite stationary ring seat 4-2 is arranged in the end face seal housing 3, the end face seal graphite stationary ring 4-1 is fixedly arranged in the graphite stationary ring seat 4-2, the end face seal graphite stationary 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 stationary ring seat 4-2, 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, the first end of the pressure mechanism 5 can be contacted with the graphite stationary ring seat 3-2, the second end of the pressure mechanism 5 can be contacted with the blocking cover 8, the propellant supply mechanism 6 is communicated with the end face seal housing 3, the liquid outlet of the propellant supply mechanism 6 is arranged between the pressure mechanism 5 and the graphite stationary ring seat 4-2, the floating sealing mechanism 7 is arranged in the pressure mechanism 5, the floating sealing mechanism 7 is sleeved on the shaft 1, so that when a rotor of the turbopump does not rotate in a precooling stage, the elastic mechanism 4-3 is in a stretching 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 sealing graphite static ring 4-1 to be tightly attached to the movable ring 2, the propellant supply mechanism 6 keeps a closing state, the propellant can be effectively isolated in the propelling cavity by end face sealing, the effective isolation of the turbopump on the propellant in the precooling stage can be realized, no leakage is realized, when the rotor of the turbopump rotates in a working state, the propellant supply mechanism 6 is opened, the propellant with a certain flow rate close to the pressure of the propellant cavity is introduced, the propellant acts on the pressure mechanism 5, and the pressure mechanism 5 drives the graphite static ring seat 4-2 to move together, the pressure mechanism 5 contacts the plug cover 8, the graphite stationary ring seat 4-2 drives the end face sealing graphite stationary ring 4-1 and the moving ring 2 to generate an axial gap, as the pressure of the propellant cavity is high and the pressure of the turbine cavity is low, the propellant flows through the graphite stationary ring seat 4-2 through the axial gap and then enters the turbine cavity through the floating sealing mechanism 7, a part of the propellant introduced through the propellant supply mechanism 6 also passes through the gap between the pressure mechanism 5 and the graphite stationary ring seat 4-2, and then 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 turbopump is improved, the heat generated during the working of the floating sealing mechanism 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.
Specifically, a labyrinth seal is arranged on the end face of the graphite stationary ring seat 4-2 facing the shaft 1; the clearance between the graphite stationary ring seat 4-2 and the shaft 1 is 0.06-0.16mm, the labyrinth seal plays a role in throttling and pressure reduction, the flow loss of the propellant is less, and the utilization efficiency of the propellant can be effectively ensured.
Specifically, the elastic mechanism 4-3 includes: bellows 4-31 and bellows seat 4-32.
The corrugated pipe seats 4-32 are fixedly connected with the end face sealing shell 3.
The first end of the corrugated pipe 4-31 is fixedly connected with the graphite stationary 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 precooling stage, the corrugated pipe 4-31 extends, 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 stationary ring seat 4-2, so that the graphite stationary ring seat 4-2 drives the end face sealing graphite stationary ring 4-1 to be tightly attached to the moving ring 2. When the rotor of the turbine pump rotates in a working state, the pressure mechanism 5 drives the graphite stationary ring seat 4-2 to move together, and the graphite stationary ring seat 4-2 compresses the corrugated pipe 4-31, so that the end face of the graphite stationary ring 4-1 is sealed to form an axial gap with the moving ring 2.
Specifically, the pressure mechanism 5 includes: a pressure plate 5-1 and a pressure housing 5-2.
A first end of the pressure plate 5-1 can be in contact with the graphite stationary ring seat 4-2, and a second end of the pressure plate 5-1 is fixedly connected with the pressure shell 5-2. In the present embodiment, the second end of the pressure plate 5-1 can be fixedly connected to the pressure housing 5-2 through the socket head cap screw 14 and the spring washer 11, so as to ensure the stability of the connection.
The pressure shell 5-2 can be arranged in the end face sealing shell 3 in a sliding mode, and the pressure shell 5-2 can be in contact with the plug cover 8.
The end surface of the pressure plate 5-1 facing the graphite stationary ring seat 4-2 is fixedly provided with a first bulge.
The end face, facing the pressure plate 5-1, of the graphite stationary ring seat 4-2 is provided with a first groove.
The projection is slidably disposed in the groove.
The end face of the pressure plate 5-1, which is far away from the graphite stationary ring seat 4-2, is connected with a floating sealing mechanism 7 through a wave spring 9.
A spring 10 is arranged between the pressure shell 5-2 and the blocking cover 8.
When the rotor of the turbopump rotates in a working state, the propellant supply mechanism 6 is opened, a certain flow of propellant with the pressure similar to that of a propellant cavity is introduced, the propellant enters the end face sealing shell 3 and reaches a position between the pressure mechanism 5 and the graphite static ring seat 4-2 to act 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, and the graphite static ring seat 4-2 drives the end face sealing graphite static ring 4-1 to generate an axial gap with the moving ring 2. Meanwhile, the end face of the pressure plate 5-1, which is far away from the graphite stationary ring seat 4-2, compresses the wave spring 9 to be in contact with the floating sealing mechanism 7, and the pressure shell 5-2 compresses the spring 10 and the plugging cover 8. When the rotor of the turbopump does not rotate in the precooling stage, the propellant supply mechanism 6 is closed, the propellant cannot flow into the end face sealing shell 3 through the propellant supply mechanism 6 at the moment and reaches a position between the pressure mechanism 5 and the graphite stationary ring seat 4-2, the pressure is reduced, the wave spring 9 and the spring 10 extend to respectively push the pressure plate 5-1 and the pressure shell 5-2, the first bulge on the pressure plate 5-1 is not hooked with the first groove any more, and the graphite stationary ring seat 4-2 is convenient to reset.
The second recess has been seted up on the terminal surface of blanking cover 8 orientation end face seal shell 3, and the second recess internal fixation is provided with first graphite pad 12, and end face seal shell 3 is provided with the second arch towards the fixed terminal surface of blanking cover 8, and the second is protruding to be contacted with first graphite pad 12, seals through first graphite pad 12 between end face seal shell 3 and the blanking cover 8.
Wherein, blanking cover 8 accessible prevents changeing pin 15 and end face seal shell 3 fixed connection, guarantees the stability of connecting.
The end face, facing the pressure shell 5-2, of the blocking cover 8 is provided with a third groove, a second graphite pad 13 is fixedly arranged in the third groove, a third protrusion is fixedly arranged on the end face, facing the blocking cover 8, of the pressure shell 5-2, the third protrusion is in contact with the second graphite pad 13, the blocking 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: a propellant delivery pipe 6-1 and a 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 stationary ring seat 4-2.
A valve 6-2 is provided on the propellant delivery tube 6-1.
When the rotor of the turbopump rotates in a working state, the valve 6-2 is opened, propellant with a certain flow rate close to the pressure of a propellant cavity is introduced, and the propellant enters the end face sealing shell 3 through the propellant conveying pipe 6-1 and reaches a position between the pressure plate 5-1 and the graphite stationary ring seat 4-2 to act on the pressure plate 5-1.
Specifically, the floating seal mechanism 7 includes: a floating ring graphite 7-1 and a floating ring seat 7-2.
The floating ring graphite 7-1 is fixedly arranged on the end face, facing the shaft 1, of the floating ring seat 7-2, and the floating ring graphite 7-1 is sleeved on the shaft 1.
The floating ring seat 7-2 is arranged 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 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.
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, the corrugated pipe 4-31 extends, 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 stationary ring seat 4-2, the graphite stationary ring seat 4-2 drives the end face sealing graphite stationary ring 4-1 to be tightly attached to the moving ring 2, and the valve 6-2 keeps a closed state. The end face seal can effectively isolate the propellant in the propelling cavity.
When a rotor of the turbopump rotates, the valve 6-2 is opened, propellant with a certain flow rate close to the pressure of a propellant cavity is introduced, the propellant enters the end face sealing shell 3 through the propellant conveying pipe 6-1 and reaches a position between the pressure plate 5-1 and the graphite static ring seat 4-2 to act on the pressure plate 5-1, the first groove is hooked by the first bulge on the pressure plate 5-1, the graphite static ring seat 4-2 is pulled, the graphite static ring seat 4-2 drives the end face sealing graphite static ring 4-1 to generate an axial gap with the moving ring 2, and at the moment, the corrugated pipe 4-31 contracts. The end face of the pressure plate 5-1, which is far away from the graphite stationary ring seat 4-2, compresses the wave spring 9 to be in contact with the floating ring seat 7-2, and the pressure shell 5-2 compresses the spring 10 to be in contact with the plug cover 8. Meanwhile, as the pressure plate 5-1 hooks the graphite stationary ring seat 4-2 to move, an axial gap is generated between the end face sealed graphite stationary ring 4-1 and the moving ring 2, and as the pressure of the propellant cavity is high and the pressure of the turbine cavity is low, the propellant passes through the axial gap, then flows through the labyrinth seal, and then 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 feed tube 6-1 also passes partly through the gap between the pressure plate 5-1 and the graphite stationary ring seat 4-2, together with the propellant flowing from the propellant chamber, through the floating ring seal into the turbine chamber. Because of the throttling and pressure reducing effects of the labyrinth seal and the floating ring, 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 rotor stops rotating, the valve 6-2 is closed, propellant cannot flow in through the propellant conveying pipe 6-1, the pressure is reduced, the corrugated pipe 4-31 extends, 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 stationary ring seat 4-2, the graphite stationary ring seat 4-2 drives the end face sealing graphite stationary ring 4-1 to be tightly attached to the moving ring 2, and the valve 6-2 keeps a closed state. The face seal now effectively isolates the propellant within the propellant chamber.
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 liquid disengaging type dynamic seal device provided on a shaft, characterized by comprising: the device comprises a movable ring, an end face sealing shell, an end face sealing mechanism, a pressure mechanism, a propellant supply mechanism, a floating sealing mechanism and a plugging cover;
the end face sealing shell is fixedly connected with the plug cover;
the movable ring is fixedly arranged on the shaft;
the end face sealing mechanism includes: the end face is sealed with a graphite static ring, a graphite static ring seat and an elastic mechanism;
the graphite stationary ring seat is slidably sleeved on the shaft and arranged in the end face sealing shell;
the end face seal graphite stationary ring is fixedly arranged in the graphite stationary ring seat and can be contacted with the moving ring;
the first end of the elastic mechanism is fixedly connected with the graphite stationary 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 sealing 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 stationary ring seat;
the floating sealing mechanism is arranged in the pressure mechanism and sleeved on the shaft.
2. The liquid breakaway dynamic seal of claim 1, wherein:
a labyrinth seal is arranged on the end face, facing the shaft, of the graphite stationary ring seat;
the clearance between the graphite stationary ring seat and the shaft is 0.06-0.16 mm.
3. The liquid breakaway dynamic seal of claim 1 wherein said resilient mechanism comprises: a corrugated pipe and a corrugated pipe seat;
the corrugated pipe seat is fixedly connected with the end face sealing shell;
the first end of the corrugated pipe is fixedly connected with the graphite stationary ring seat, and the second end of the corrugated pipe is fixedly connected with the corrugated pipe seat.
4. The liquid breakaway dynamic seal of claim 1 wherein said pressure mechanism comprises: a pressure plate and a pressure housing;
the first end of the pressure plate can be contacted 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 the pressure shell can be contacted with the plug cover.
5. The liquid breakaway dynamic seal of claim 4, wherein:
a first bulge is fixedly arranged on the end face, facing the graphite stationary ring seat, of the pressure plate;
a first groove is formed in the end face, facing the pressure plate, of the graphite stationary ring seat;
the projection is slidably disposed within the recess.
6. The liquid breakaway dynamic seal of claim 4, wherein:
the end surface of the pressure plate, which is far away from the graphite static ring seat, is connected with the floating sealing mechanism through a wave spring;
and a spring is arranged between the pressure shell and the blocking cover.
7. The liquid breakaway dynamic seal of claim 4, wherein:
a second groove is formed in the end face, facing the end face sealing shell, of the blocking cover, a first graphite pad is fixedly arranged in the second groove, a second protrusion is fixedly arranged on the end face, facing the blocking cover, of the end face sealing shell, and the second protrusion is in contact with the first graphite pad;
the blanking cover orientation the third recess has been seted up on pressure housing's the terminal surface, the third recess internal fixation is provided with the second graphite pad, pressure housing orientation the fixed third arch that is provided with on the terminal surface of blanking cover, the third arch with the contact of second graphite pad.
8. The liquid breakaway dynamic seal of claim 1, wherein said propellant feed mechanism comprises: propellant delivery lines and valves;
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 stationary ring seat;
the valve is disposed on the propellant delivery tube.
9. The liquid breakaway dynamic seal of claim 1, wherein said floating seal mechanism comprises: floating ring graphite and a 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.
10. The liquid breakaway dynamic seal of claim 9, wherein:
the distance between the floating ring graphite and the shaft is 0.2-1 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010908058.1A CN112096652B (en) | 2020-09-02 | 2020-09-02 | Liquid-release dynamic sealing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010908058.1A CN112096652B (en) | 2020-09-02 | 2020-09-02 | Liquid-release dynamic sealing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112096652A true CN112096652A (en) | 2020-12-18 |
| CN112096652B CN112096652B (en) | 2024-05-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010908058.1A Active CN112096652B (en) | 2020-09-02 | 2020-09-02 | Liquid-release dynamic sealing device |
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| CN (1) | CN112096652B (en) |
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| JP2013189914A (en) * | 2012-03-13 | 2013-09-26 | Mitsubishi Heavy Ind Ltd | Turbo pump |
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| CN112096652B (en) | 2024-05-03 |
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