CN109162955B - End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump - Google Patents
End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump Download PDFInfo
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- CN109162955B CN109162955B CN201810986754.7A CN201810986754A CN109162955B CN 109162955 B CN109162955 B CN 109162955B CN 201810986754 A CN201810986754 A CN 201810986754A CN 109162955 B CN109162955 B CN 109162955B
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- Prior art keywords
- ring
- seal
- engine
- turbo pump
- end surface
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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
- F04D29/086—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
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F04D29/02—Selection of particular materials
- F04D29/026—Selection of particular materials especially adapted for liquid 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
- F04D7/00—Pumps adapted for handling specific fluids, e.g. by selection of specific materials for pumps or pump parts
Abstract
The utility model provides an automatic disjunctor formula dynamic seal device of terminal surface labyrinth combination for engine turbo pump, including quiet ring (1), vice seal assembly (2), seal housing (3), support ring (4), gland (5), spring (6), retaining ring (7), rotating ring (8), adopt end face seal to realize when the turbo pump precooling between pump end and turbine end, during operation the seal face is automatic to be thrown off under the sealing pressure effect, utilize axial plane ladder skewed tooth to form labyrinth seal and play the throttle and maintain the off-state, thereby guarantee that the rocket engine can realize keeping apart zero consumption of helium, zero leakage when sealed can realize the precooling, the high reliability performance of zero wearing and tearing during operation.
Description
Technical Field
The invention relates to an end surface labyrinth combined automatic disengaging type dynamic sealing device for an engine turbo pump, and belongs to the technical field of engine sealing.
Background
Since the 21 st century, manned mars and deep space exploration plans are proposed by various aerospace major countries in the world, and a high-thrust rocket is an essential transportation tool, so that the future development direction of the carrier rocket is to further reduce the cost and pollution and improve the reliability and carrying capacity. The oxyhydrogen engine has the advantages of high theoretical specific impulse, no pollution, good cooling performance and the like, and is widely applied to new generation carrier rockets at home and abroad.
Because the density of the liquid hydrogen medium is low, only 1/14 of water exists, the hydrogen turbine pump must work at a high rotating speed to provide enough pressure for the engine, and because the viscosity of the liquid hydrogen is very low, almost no lubricating performance exists, the working environment of the dynamic seal is severe. Especially for the high-thrust oxyhydrogen engine, the size of the hydrogen turbine pump is large, the pressure is higher, and the sealing pressure and the sliding speed of the dynamic seal of the hydrogen turbine pump are high, so to sum up, the dynamic seal of the high-thrust oxyhydrogen engine turbine pump is a technical difficulty.
The main function of the dynamic seal of the hydrogen turbine pump is to prevent liquid hydrogen at the pump end from leaking to the turbine cavity when the engine is precooled, and to allow the liquid hydrogen at the pump end to leak to the turbine cavity in a small amount because the turbine end is hydrogen-rich gas when the engine works. In the prior art, a hydrogen turbopump is usually sealed by floating rings with higher reliability, but isolation helium gas needs to be filled between two stages of floating rings for sealing during precooling, the helium gas consumption is increased rapidly along with the increase of the structural size of the turbopump, the core-class engine can adopt ground helium gas supply, and a rocket needs to carry a large amount of helium gas for a second-class engine, so that the system complexity is increased, and the effective load is reduced.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the problems that in the prior art, a high-thrust engine needs to meet the requirements on low helium consumption and high sealing, the end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump is provided.
The technical scheme for solving the technical problems is as follows:
an end face labyrinth combined automatic disengaging type dynamic sealing device for an engine turbo pump comprises a static ring, a sealing shell, a gland, a spring, a check ring, a dynamic ring and stepped helical teeth, wherein the dynamic ring is arranged at the central position of the top of the sealing shell, the side wall of the inner side of the sealing shell is provided with a gland mounting groove and a sealing groove, the static ring is mounted on one side of the gland mounting groove and the sealing groove, which faces the dynamic ring, the gland is mounted in the gland mounting groove, the spring penetrates through the hollow position of the gland and axially supports against the static ring to ensure that the convex connecting end of the static ring and the dynamic ring does not fall off, the check ring is arranged on the other side of the static ring to ensure that the static ring is stable in position when the engine does not work and ensure that the static ring is tightly attached to the convex connecting end of the dynamic ring, when the engine works, the cavity, the connection end face of the shaft sleeve and the static ring is provided with step helical teeth which ensure the sealing of the engine during working, and after the engine stops working, the static ring returns to the original position and is tightly attached to the convex connection end of the movable ring.
The sealing device is characterized by further comprising a support ring and an auxiliary sealing assembly, wherein the support ring is installed at the bottom of the sealing groove, the auxiliary sealing assembly is arranged at the top of the support ring in a pressing mode and used for enhancing the sealing performance of the sealing device, the auxiliary sealing assembly comprises a sealing shell and an O-shaped spring, the O-shaped spring is wrapped on the sealing shell, and the O-shaped spring is a double-layer alloy spring.
And a disengagement gap exists between the static ring and the end surface of the gland mounting groove, and the disengagement gap is 1-2 mm.
The wall thickness of the sealing groove is 2.5 mm-3 mm, and the diameter gap between the diameter of the static ring and the diameter of the end face of the sealing shell is 0.05 mm-0.08 mm.
The static ring material is stainless steel brazed pure silver or silver-magnesium-nickel alloy.
The O-shaped spring is made of polytetrafluoroethylene.
The supporting ring material is polyether-ether-ketone.
The moving ring is a chromium oxide coating coated on a metal material.
And the surface of the shaft sleeve is coated with a silver or silver-magnesium-nickel alloy wear-resistant layer.
Compared with the prior art, the invention has the advantages that:
(1) the end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump can meet the requirements that a high-thrust oxyhydrogen engine turbo pump can prevent liquid hydrogen from leaking to a turbine cavity in a precooling stage, automatically disengages under the pressure action of a medium of the turbo pump when the engine is started, can disengage at a low speed, realizes zero abrasion of sealing, improves the working reliability of dynamic sealing, can realize zero consumption of helium of the engine during precooling, and meets the sealing performance requirement during precooling, and the adopted stepped helical teeth meet the requirements of the engine on working throttling and maintaining the end surface sealing disengaging state;
(2) the disengaging seal provided by the invention adopts a static ring embedded with copper graphite and a plasma spraying chromium oxide coating moving ring to form a main seal pair, meets the requirements of medium compatibility and wear resistance, and adopts a spring energy storage seal ring formed by combining a metal spring and polytetrafluoroethylene as an auxiliary seal. The spring energy storage sealing ring still has good elasticity and sealing performance at extremely low temperature. The polytetrafluoroethylene material is matched with metal, so that the friction coefficient can be reduced, good friction duality is formed, the medium compatibility is realized, the sealing shaft sleeve is made of high-strength high-temperature alloy material, the matching surface of the sealing shaft sleeve is a silver-welded or silver-magnesium-nickel alloy wear-resistant layer, and the sealing shaft sleeve has good friction and wear performance and liquid hydrogen environment compatibility.
Drawings
FIG. 1 is a schematic view of a sealing device provided by the present invention;
FIG. 2 is a schematic structural view of a secondary seal assembly provided in the present invention;
FIG. 3 is a schematic view of a lug anti-rotation structure provided by the present invention;
FIG. 4 is a schematic view of a stationary ring and seal housing positioning structure provided by the present invention;
FIG. 5 is a schematic view of the structure of the disengagement gap of the stationary ring provided by the present invention;
FIG. 6 is a static ring structure provided by the invention;
FIG. 7 is a view of the seal housing configuration provided by the present invention;
Detailed Description
The utility model provides an automatic formula dynamic seal device that takes off of terminal surface labyrinth combination for engine turbo pump, includes quiet ring 1, vice seal assembly 2, seal housing 3, support ring 4, gland 5, spring 6, retaining ring 7, rotating ring 8, the mounting means of this device is installed on seal housing 3 with vice seal assembly 2 and support ring 4 earlier, fixes gland 5 to seal housing 3 again on, aims at a series of through-holes and seal housing 3 spring hole positions on gland 5 during fixed, later installs spring 6 on seal housing 3 again. After the spring 6 is placed, the static ring 1 is installed, the lug of the static ring 1 is placed in the corresponding stop groove of the sealing shell, the static ring 1 is fixed on the sealing shell 3 by the retainer ring 7, a static ring 1 assembly is formed, and the static ring 1 assembly is convenient to install on a turbine pump.
The following is further illustrated with reference to specific examples:
as shown in fig. 1, a gland mounting groove and a seal groove are axially arranged at two ends of the seal housing 3, the stationary ring 1 is mounted at one side of the gland mounting groove and the seal groove, the support ring 4 is mounted at the bottom of the seal groove, the auxiliary seal assembly 2 is press-mounted at the top of the support ring 4, the stationary ring 1 is provided with two lugs for fixing the position of the stationary ring 1, the axial lugs of the stationary ring 1 are tightly attached to the seal groove and further sealed with the support ring 4 and the auxiliary seal assembly 2, the movable ring 8 is arranged at the central position of the top of the seal housing 3, both ends of the movable ring 8 are provided with boss connecting ends, a locking groove for further fixing the position of the stationary ring is arranged at the outer side of the boss connecting end of the movable ring 8, the radial lugs of the stationary ring 1 are mounted in the locking groove to make the stationary ring 1 tightly attached to the boss connecting end of the movable ring, the gland 5 is mounted in the gland mounting, the retainer ring 7 is arranged on the other side of the stationary ring to ensure that the stationary ring 1 is stable when the engine does not work. The bottom of the dynamic ring 8 is provided with a shaft sleeve, and the connecting end surface of the shaft sleeve and the axial convex lug of the static ring 1 is provided with step helical teeth for ensuring the sealing of the engine during working.
In the disengaging type dynamic sealing device, the spring 6 applies axial force to the static ring 1, so that the end faces of the static ring 1 and the dynamic ring 8 can be jointed and maintain a certain sealing specific pressure, and a pump end medium is prevented from leaking to a turbine end during precooling. When the engine is started, the pressure difference between the upstream and the downstream of the static ring 1 is increased, so that the static ring 1 overcomes the force of the spring 6 and the friction force of the secondary sealing assembly 2 to automatically disengage under the action of the pressure difference. When the engine works, the labyrinth seal formed by the contact end surfaces of the shaft sleeve and the lugs plays a throttling role, the upstream and downstream pressure difference of the static ring 1 is maintained, and the end surface seal is ensured to be in a disengagement state. When the engine is shut down, the medium pressure is reduced, the pressure difference between the two ends of the static ring 1 is reduced to a certain degree, and the static ring 1 is reclosed and effectively sealed under the action force of the spring 6, so that the repeated starting of the engine is realized.
The static ring 1 of the disengaging dynamic seal adopts an over-balance design, and the balance diameter is larger than the outer diameter of the connecting end of the dynamic ring 8. When the pressure difference of the stationary ring 1 increases, the fluid push-away force acting on the stationary ring 1 also increases.
The main seal of the disengaging type dynamic seal is an end face seal formed between a dynamic ring 8 and a static ring 1, a hard-to-soft sealing material is adopted, the dynamic ring 8 is sprayed with chromium oxide, the static ring is embedded with a graphite ring structure as shown in figure 6, and the graphite material of the static ring has high impact resistance.
The labyrinth seal of the disengaging seal is formed by a static ring 1 and a shaft sleeve, the labyrinth seal adopts step helical teeth, the shaft sleeve is provided with labyrinth teeth, and a step-shaped sealing surface is arranged at the opposite position of the static ring 1. In order to prevent hard-to-hard collision and abrasion and meet the medium compatibility in a hydrogen environment, the shaft sleeve is made of a high-temperature alloy material, and the static ring 1 is made of stainless steel brazed pure silver or silver-magnesium-nickel alloy material.
As shown in fig. 2, the secondary seal assembly 2 needs to work in a high-low temperature environment of low-temperature liquid hydrogen and high-temperature gas, so a spring 6 energy storage seal ring is adopted, the seal ring is made of reinforced polytetrafluoroethylene material, the spring 6 is made of double-layer springs, and the materials are high-temperature alloys.
The roughness of the contact plane of the auxiliary sealing assembly 2 and the sealing shell 3 and the roughness of the contact plane of the auxiliary sealing assembly 2 and the static ring 1 are not more than 0.4.
The interference of the auxiliary sealing assembly 2 and the static ring 1 is not too large, and the starting and moving friction force of the auxiliary sealing assembly is controlled to be in the range of 300-600N at low temperature.
In order to prevent the spring energy storage sealing ring from entering the assembly gap between the sealing shell 3 and the static ring 1 under the action of high pressure, a support ring 4 is arranged between the sealing ring and the sealing shell 3.
In order to prevent the spring energy storage sealing ring from being separated from the sealing surface due to the influence of vibration during working, the gland 5 is arranged to limit the spring energy storage sealing ring. The gland 5 is fixed on the sealing shell 3 by screws, a series of through holes are also arranged on the gland 5, the number and the positions of the through holes correspond to those of the spring holes on the sealing shell 3 and are used for placing the springs 6, and the sealing shell 3 is shown in figure 7.
As shown in FIG. 4, in order to prevent the stationary ring 1 from being stuck when moving, the diameter clearance between the balance diameter of the stationary ring 1 and the positioning surface of the seal housing 3 is 0.05mm to 0.08mm, and the axial length of the positioning surface is 2.5mm to 3 mm.
The design of the spring force must ensure that the main seal has enough specific seal pressure to ensure the sealing of a medium under the condition of precooling, and when the engine is shut down, the friction force of the auxiliary seal assembly 2 can be overcome to reclose the static ring and the dynamic ring, so that the repeated use of the engine is met.
As shown in figure 5, after the sealing environment is automatically separated under the action of pressure difference, the static ring 1 moves to be in contact with the end face of the sealing shell 3 to realize braking, and the separation gap of the sealing is controlled to be 1-2 mm, as shown in figure 3, a lug on the static ring 1 is used for preventing rotation, a retainer ring 7 is arranged on the sealing shell 3, the purpose is to prevent the dynamic ring 8 and metal on the static ring 1 from being rubbed due to rapid abrasion of graphite under abnormal conditions, and in addition, the static ring 1 can be assembled into a static ring 1 component under the action of the retainer ring 7, so that the test and the assembly are convenient.
The invention is not described in detail and is within the knowledge of a person skilled in the art.
Claims (9)
1. The utility model provides an automatic formula dynamic seal device that breaks away from of engine turbo pump terminal surface labyrinth combination which characterized in that: including quiet ring (1), seal housing (3), gland (5), spring (6), retaining ring (7), rotating ring (8), ladder skewed tooth (9), rotating ring (8) set up in seal housing (3) top central point and put, and seal housing (3) inboard lateral wall is provided with gland mounting groove and seal groove, and quiet ring (1) is installed in gland mounting groove and seal groove towards rotating ring (8) one side, gland (5) are installed in the gland mounting groove, spring (6) pass gland (5) cavity position and live quiet ring (1) in axial withstand and guarantee quiet ring (1) and rotating ring (8) protruding link and do not drop, retaining ring (7) set up and guarantee quiet ring (1) stable in position when the engine is out of work in quiet ring opposite side to make quiet ring (1) hug closely rotating ring (8) protruding link, during engine operation, quiet ring (1), The cavity pressure that sealed casing (3), rotating ring (8) formed increases, promotes quiet ring (1) and throw off to rotating ring (8) opposite direction along the axial, and rotating ring (8) bottom sets up the axle sleeve, and the terminal surface is connected with quiet ring (1) to the axle sleeve sets up sealed ladder skewed tooth (9) of assurance engine during operation, and engine stop work back, quiet ring (1) playback is hugged closely with rotating ring (8) protruding link.
2. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 1, characterized in that: still include support ring (4), vice seal assembly (2), install in the seal groove bottom in support ring (4), vice seal assembly (2) pressure equipment is in support ring (4) top reinforcing means leakproofness, vice seal assembly (2) are including sealed shell (202), O type spring (201), and O type spring (201) cladding is in sealed shell (202), and O type spring (201) are double-deck alloy spring.
3. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 1, characterized in that: and a disengagement gap exists between the static ring (1) and the end surface of the mounting groove of the gland (5), and the disengagement gap is 1-2 mm.
4. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 1, characterized in that: the wall thickness of the sealing groove is 2.5 mm-3 mm, and the diameter gap between the diameter of the static ring (1) and the diameter of the end face of the sealing shell is 0.05 mm-0.08 mm.
5. The end face labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 4, characterized in that: the static ring (1) is made of stainless steel brazed pure silver or silver-magnesium-nickel alloy.
6. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump as claimed in claim 2, wherein: the O-shaped spring (201) is made of polytetrafluoroethylene.
7. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump as claimed in claim 2, wherein: the material of the support ring (4) is polyether ether ketone.
8. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 1, characterized in that: the moving ring (8) is a chromium oxide coating coated on a metal material.
9. The end surface labyrinth combined automatic disengaging type dynamic sealing device for the engine turbo pump according to claim 1, characterized in that: and the surface of the shaft sleeve is coated with a silver or silver-magnesium-nickel alloy wear-resistant layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810986754.7A CN109162955B (en) | 2018-08-28 | 2018-08-28 | End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810986754.7A CN109162955B (en) | 2018-08-28 | 2018-08-28 | End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump |
Publications (2)
| Publication Number | Publication Date |
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| CN109162955A CN109162955A (en) | 2019-01-08 |
| CN109162955B true CN109162955B (en) | 2021-03-26 |
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| CN201810986754.7A Active CN109162955B (en) | 2018-08-28 | 2018-08-28 | End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump |
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| CN110725955A (en) * | 2019-11-08 | 2020-01-24 | 成都一通密封股份有限公司 | Supercritical CO for protecting bearing box2Special safety sealing structure |
| CN111120393A (en) * | 2019-12-27 | 2020-05-08 | 北京星际荣耀空间科技有限公司 | Energy storage sealing structure and dynamic sealing device for high-pressure easily-vaporized medium |
| CN112096865A (en) * | 2020-09-08 | 2020-12-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-linkage back-to-back assembled elastic sealing structure for aero-engine |
| CN112145471B (en) * | 2020-10-22 | 2022-05-17 | 航天科工火箭技术有限公司 | Gas disengaging type combined dynamic sealing device |
| CN113294376A (en) * | 2021-06-29 | 2021-08-24 | 哈尔滨工业大学 | Balance seal for nuclear main pump and manufacturing method thereof |
| CN113958535B (en) * | 2021-09-02 | 2023-06-27 | 西安航天动力研究所 | Impeller pressure drop type disengaging sealing device for liquid rocket engine |
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