CN112728087B - Shaft seal device for liquid rocket engine - Google Patents
Shaft seal device for liquid rocket engine Download PDFInfo
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- CN112728087B CN112728087B CN202110017966.6A CN202110017966A CN112728087B CN 112728087 B CN112728087 B CN 112728087B CN 202110017966 A CN202110017966 A CN 202110017966A CN 112728087 B CN112728087 B CN 112728087B
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- 239000007788 liquid Substances 0.000 title claims abstract description 24
- 238000007789 sealing Methods 0.000 claims abstract description 181
- 239000003380 propellant Substances 0.000 claims abstract description 73
- 239000007789 gas Substances 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 10
- 230000006837 decompression Effects 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 239000011261 inert gas Substances 0.000 claims description 5
- 238000007664 blowing Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 230000009467 reduction Effects 0.000 description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N nitrogen Substances N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- WWYNJERNGUHSAO-XUDSTZEESA-N (+)-Norgestrel Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](CC)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 WWYNJERNGUHSAO-XUDSTZEESA-N 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007723 die pressing method Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- BFKJFAAPBSQJPD-UHFFFAOYSA-N tetrafluoroethene Chemical group FC(F)=C(F)F BFKJFAAPBSQJPD-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
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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
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/40—Sealings between relatively-moving surfaces by means of fluid
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Devices (AREA)
Abstract
The application relates to a shaft seal device for a liquid rocket engine, and relates to the technical field of engine shaft seals. This shaft seal device includes the mount pad, first sealing module and second sealing module, be equipped with a through-hole that is used for the cover to establish electric motor rotor in the mount pad, first sealing module inlays and locates in the through-hole, first sealing module is used for forming sealedly between electric motor rotor and through-hole, in order to prevent the propellant to get into the motor cavity, second sealing module locates on the mount pad and is located first sealing module's low reaches, second sealing module is used for forming pneumatic seal between electric motor rotor and through-hole, be used for simultaneously with getting into outside the propellant drainage in the second sealing module to the mount pad, in order to assist first sealing module to prevent the propellant to get into the motor cavity jointly. The shaft seal device provided by the application can meet the requirements of low leakage and even zero leakage of the electric pump of the rocket engine, has good leakage-proof performance, and has the advantages of simple structure, compact space and low manufacturing cost.
Description
Technical Field
The application relates to the technical field of engine shaft seals, in particular to a shaft seal device for a liquid rocket engine.
Background
At present, a propellant conveying mode is an important component of a spacecraft propulsion system, the type of the propellant conveying mode determines the structure and parameters of the spacecraft and the whole propulsion system of the spacecraft to a great extent, and the traditional propellant supply modes of a liquid two-component propulsion system generally comprise a pumping mode and a squeezing mode. Compared with a propulsion system with large thrust and high specific impulse, a propellant storage tank and a pressurized gas cylinder in the extrusion type supply system need to bear high pressure, so that the structural mass of the extrusion type supply system is larger; the pump-type system relies on a pump to pressurize the propellant, thus greatly reducing the structural mass and design cost of the propellant storage tank and pressurized gas cylinder.
In the correlation technique, the pumping pressure formula system can be divided into turbopump supply system and electric pump supply system, and wherein, the turbopump structure is relatively more complicated, and it is great to make the assembly degree of difficulty, and the development cost is high, the cycle length, and under the comparison, the electric pump supply system has with low costs, and system architecture is simple, and the operation is reliable, easily adjusts advantages such as control, the modularization of being convenient for. Particularly, with the high-speed development of motor and battery technologies, the propellant is supplied by the electric pump, so that the motor-driven high-speed propellant supply device has more and more obvious advantages and has wide application prospects in the field of commercial aerospace.
In the electric pump supply system, the electric pump drives the pump through high speed motor and carries out the pressurization to the propellant, and high speed motor carries out work under the coexistent condition of propellant and high-tension electricity, and still involve high-speed and microthermal operating condition, and operational environment is abominable, if the propellant leaks to the cavity of motor, then produces the accident of burning explosion very easily, consequently, the reliability of electric pump axial seal structure is the important factor that restricts the safe and stable operation of electric pump system. At present, an axial dynamic sealing structure commonly used in a liquid rocket engine is a mechanical sealing device, the sealing effect is good, however, the problems of complex structure, large size, high cost and difficult later maintenance exist, and the further popularization and use of the axial dynamic sealing structure are limited to a great extent.
Disclosure of Invention
The embodiment of the application provides a shaft seal device for a liquid rocket engine, and aims to solve the problems of complex structure, large size and high cost of the shaft seal device for the liquid rocket engine in the related technology.
The present application provides a shaft seal arrangement for a liquid rocket engine, comprising:
the mounting seat is internally provided with a through hole for sleeving the motor rotor;
the first sealing module is embedded in the through hole and is used for forming sealing between the motor rotor and the through hole so as to prevent propellant from entering a motor cavity;
and the second sealing module is arranged on the mounting seat and positioned at the downstream of the first sealing module, is used for forming pneumatic sealing between the motor rotor and the through hole and is simultaneously used for guiding the propellant entering the second sealing module to the outside of the mounting seat so as to assist the first sealing module in preventing the propellant from entering the motor cavity.
In some embodiments, the first sealing module comprises:
the first sealing assembly is embedded in the inner wall of the through hole and is used for forming sealing between the motor rotor and the through hole and depressurizing the propellant entering the through hole so as to gasify part of the propellant entering the through hole;
and the second sealing assembly comprises at least one second sealing element, the second sealing element is embedded in the inner wall of the through hole and arranged at the downstream of the first sealing assembly, and the second sealing assembly is used for forming sealing between the motor rotor and the through hole and reducing the pressure of the propellant entering the through hole again.
In some embodiments, the first sealing assembly is annular, and at least two pressure reduction grooves are arranged on the inner side surface close to the motor rotor at intervals and used for reducing the pressure of the propellant passing through the pressure reduction grooves.
In some embodiments, at least one elastic sheet is disposed on an inner side surface of the second sealing member close to the motor rotor, and the elastic sheet is configured to be in interference fit with the motor rotor and bend towards the first sealing assembly, so as to form a seal between the motor rotor and the through hole.
In some embodiments, the number of the elastic pieces on each second sealing element is 2, the two elastic pieces are arranged at intervals, and the interference is 0.1-0.2 mm, so that the through holes are used for forming sealing between the motor rotor and the through holes, and the propellant entering the through holes is depressurized again.
In some embodiments, the number of the second sealing elements is 2, a retainer ring connected to both the mounting seat and the first sealing assembly is disposed between the two second sealing elements, and one side of the retainer ring, which is close to the motor rotor, is used for being attached to the motor rotor to separate the two second sealing elements.
In some embodiments, a leak-proof gasket is arranged between the retainer ring and the mounting seat, and the retainer ring, the mounting seat and the first sealing assembly are connected through bolts.
In some embodiments, the second sealing module comprises:
the air inlet channel comprises a first air inlet and a first air outlet, and the first air inlet is used for being connected with air blowing equipment;
an air outlet channel comprising a second air inlet and a second air outlet;
and the sealing channel comprises a first sealing groove and a second sealing groove which are arranged at intervals along the direction of keeping away from the second sealing element, the first sealing groove is communicated with the second sealing groove and the second air inlet, the second sealing groove is communicated with the first air outlet, so that a pneumatic seal is formed between the motor rotor and the through hole, and meanwhile, the propellant is drained to the outside of the second air outlet in the first sealing groove.
In some embodiments, the second seal groove is located downstream of the first seal groove, and the first and second seal grooves are both annular or rectangular.
In some embodiments, the gas introduced into the first gas inlet is an inert gas, and the pressure of the inert gas is 0.2 to 0.5MPa.
The beneficial effect that technical scheme that this application provided brought includes:
the embodiment of the application provides a shaft seal device for a liquid rocket engine, because be provided with a through-hole that is used for the cover to establish electric motor rotor on the mount pad to interval sets up first sealing module and second sealing module in proper order on the through-hole, wherein, first sealing module is used for forming sealedly between electric motor rotor and through-hole, and second sealing module is used for forming pneumatic seal between electric motor rotor and through-hole, is used for simultaneously leading the propellant that gets into in the second sealing module outside the mount pad, prevents propellant entering motor cavity jointly with supplementary first sealing module. This shaft seal device adopts the sealed form of first sealed module and the sealed module combination of second, plays sealed effect and prevents that propellant from getting into the basis of motor cavity, can also form pneumatic seal simultaneously through the air current with propellant drainage to the mount pad outside, sealed leak protection is effectual, and simple structure, space are compact, the cost is with low costs.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of a shaft seal arrangement for a liquid rocket engine provided in accordance with an embodiment of the present application;
fig. 2 is a schematic diagram of the trend of the leakage flow of the propellant for the shaft seal device of the liquid rocket engine according to the embodiment of the present application.
In the figure: 1-a mounting seat, 10-a through hole, 2-a motor rotor, 30-a first sealing assembly, 31-a second sealing element, 32-a decompression groove, 33-an elastic sheet, 34-a retainer ring, 40-an air inlet channel, 41-an air outlet channel, 42-a first sealing groove and 43-a second sealing groove.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The embodiment of the application provides a shaft seal device for a liquid rocket engine, which can solve the problems of complex structure, large size and high cost of the shaft seal device for the liquid rocket engine in the related technology.
Referring to fig. 1, the shaft sealing device comprises a mounting base 1, a first sealing module and a second sealing module, a through hole 10 used for sleeving a motor rotor 2 is formed in the mounting base 1, the first sealing module is embedded in the through hole 10 and used for forming sealing between the motor rotor 2 and the through hole 10 so as to prevent propellant from entering a motor cavity, the second sealing module is arranged on the mounting base 1 and located at the downstream of the first sealing module, the second sealing module is used for forming pneumatic sealing between the motor rotor 2 and the through hole 10 and simultaneously used for guiding the propellant entering the second sealing module to the outside of the mounting base 1 so as to assist the first sealing module to prevent the propellant from entering the motor cavity, the propellant and the motor cavity are isolated, and safe operation of a motor is guaranteed.
Further, the first sealing module specifically comprises a first sealing assembly 30 and a second sealing assembly, wherein the first sealing assembly 30 is embedded in the inner wall of the through hole 10, the first sealing assembly 30 is mainly used for forming sealing between the motor rotor 2 and the through hole 10, and depressurizing propellant entering the through hole 10 to gasify part of propellant entering the through hole 10; the second sealing assembly comprises at least one second sealing element 31, the second sealing element 31 is also embedded in the inner wall of the through hole 10 and is arranged at the downstream of the first sealing assembly 30, namely, if the propellant enters the shaft sealing device, the propellant passes through the first sealing assembly 30 and then passes through the second sealing element 31, the second sealing assembly is mainly used for forming sealing between the motor rotor 2 and the through hole 10, if the propellant leaks, the propellant entering the through hole 10 can be depressurized again by the second sealing assembly, and the rest propellant is further gasified.
Further, from structural design's angle, first seal assembly 30 is the annular, and is close to motor rotor 2's medial surface on the interval be equipped with two at least decompression grooves 32, and decompression groove 32 sets up along the direction interval distribution of the flow direction of propellant, mainly used steps down the propellant that passes through, is clearance fit between first seal assembly 30, mount pad 1 and the motor rotor 2, and the clearance is at 0.1mm ~ 0.3mm. The sealing pressure reduction principle of the first sealing assembly 30 is as follows: the first sealing assembly 30 comprises a plurality of pressure reduction grooves 32, the first sealing assembly 30 is in clearance fit with the motor rotor, the pressure reduction grooves 32 and the motor rotor 2 form a series of throttling clearances and expansion spaces, and propellant fluid generates large resistance through multiple throttling and expansion, so that the sealing purpose is achieved.
Furthermore, at least one elastic sheet 33 is disposed on an inner side surface of the second sealing member 31 close to the motor rotor 2, and the elastic sheet 33 is configured to be in interference fit with the motor rotor 2 and bend towards the first sealing assembly 30, so as to form a seal between the motor rotor 2 and the through hole 10. There is a certain clearance space between each second seal 31 and the rotor 2 of the motor, and when the propellant flows through, the propellant is further depressurized in the same way.
Further, the number of the elastic pieces 33 on each second sealing member 31 is 2, the two elastic pieces 33 are arranged at intervals, and the interference is 0.1-0.2 mm, so that the sealing is formed between the motor rotor 2 and the through hole 10, and the propellant entering the through hole 10 is depressurized again through the gap. The second sealing member 31 is made of tetrafluoroethylene and a metal sheet by a die pressing process.
Furthermore, from the perspective of structural design, the number of the second sealing members 31 is 2, a retaining ring 34 connected to the mounting base 1 and the first sealing assembly 30 is disposed between the two second sealing members 31, and one side of the retaining ring 34 close to the motor rotor 2 is used for being attached to the motor rotor 2 to separate the two second sealing members 31, thereby further ensuring the sealing effect of the shaft sealing device.
Furthermore, because spare part is more, and all belong to metal parts, consequently, in order to prevent that the propellant from taking place to leak from other positions, still be equipped with leak protection gasket 34 between retaining ring 34 and mount pad 1, then link to each other through the bolt between retaining ring 34, mount pad 1 and the first seal assembly 30, firm in connection, it is all more convenient to dismantle the installation.
Further, as shown in fig. 2, the second sealing module specifically includes an air inlet channel 40, an air outlet channel 41 and a sealing channel, where the air inlet channel 40 includes a first air inlet and a first air outlet, the first air inlet is mainly used to connect with an air blowing device, the air outlet channel 41 includes a second air inlet and a second air outlet, the sealing channel includes a first sealing groove 42 and a second sealing groove 43 that are arranged on the inner wall of the through hole 10 at intervals along a direction away from the second sealing member 31, the first sealing groove 42 is communicated with both the second sealing groove 43 and the second air inlet, and the second sealing groove 43 is communicated with the first air outlet to form a pneumatic seal between the motor rotor 2 and the through hole 10, and simultaneously, the propellant entering the first sealing groove 42 is guided out of the second air outlet.
Further, the diameter of the second sealing groove 43 is larger than that of the first sealing groove 42, the second sealing groove 43 is located at the downstream of the first sealing groove 42, so that the propellant is blown into the first sealing groove 42 while the airflow has a tendency of flowing back to form sealing, and the first sealing groove 42 and the second sealing groove 43 are both annular or rectangular. Specifically, referring to fig. 2, the first sealing groove 42 and the second sealing groove 43 are communicated with the motor rotor 2 through a small gap existing between the inner wall of the through hole 10, when the propellant passes through the first sealing assembly 30 and the two second sealing members 31 in sequence, most of the propellant is changed into a gaseous state due to continuous decompression at this time, and after entering the first sealing groove 42, because a large amount of high-pressure gas enters from the first gas inlet at this time, according to the principle that the gas flows from high pressure to low pressure, the high-pressure gas entering from the first gas inlet first enters the second sealing groove 43 from the first gas outlet, and then enters the first sealing groove 42 from the gap between the first sealing groove 42 and the second sealing groove 43 to form a backflow, and a black arrow in fig. 2 is a leakage propellant flow path. In the process, pneumatic sealing is formed between the through hole 10 and the motor rotor 2, the high-pressure airflow entering the first sealing groove 42 prevents the propellant from flowing further downstream, so that the propellant is prevented from further entering the motor cavity, in addition, the propellant enters the second air inlet along with the flowing direction of the high-pressure airflow and finally flows out of the shaft sealing device from the second air outlet, the leaked propellant is guided out, the sealing effect is achieved, the leaked propellant is discharged, the propellant is fundamentally prevented from entering the motor cavity, and white arrows in fig. 2 are degassing flow paths.
Further, the high-pressure gas introduced into the first air inlet is nitrogen, the pressure of the nitrogen is 0.2-0.5 MPa, other inert gases compatible with a propellant such as helium and the like can be selected, the propellant is liquid hydrogen, liquid oxygen, LNG and the like, the pressure before entering the shaft sealing device is 3-4 MPa, the pressure of the motor cavity is 0.1MPa, the propellant undergoes first pressure reduction after passing through the first sealing assembly 30, the pressure is reduced to 1.3MPa, the pressure is reduced to 0.3MPa when passing through the first second sealing assembly 31, the pressure is reduced to about 0.11MPa when passing through the second sealing assembly 31, the leaked propellant is blown off and discharged by the nitrogen with 0.2-0.5 MPa at the moment, the mass of the hydrogen leaked to the motor cavity is substantially 0g, and the mass flow of the propellant at the second air outlet is about 5mg/s.
This shaft seal device adopts the mode of combination seal, combine contact seal and non-contact seal promptly, first seal assembly 30 is non-contact seal, two second sealing members 31 are contact seal, the airflow channel of the sealed module of second is non-contact seal promptly, form four sealing faces in proper order in through-hole 10, realize not only sealed while but also realizing reducing pressure step by step, turn into the gas easy to seal with difficult sealed liquid, and through the propellant of the isolated most leakage of twice second sealing member 31, blow off the discharge through blowing off the gas at last, sealed reliability has been guaranteed greatly, and overall structure is simple compact, the size is very little relatively, and is low in cost, it is sealed effectual.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience of describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be configured and operated in a specific orientation, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. A shaft seal arrangement for a liquid rocket engine, comprising:
the mounting seat (1) is internally provided with a through hole (10) for sleeving the motor rotor (2);
a first sealing module embedded in the through hole (10), the first sealing module being used for forming a seal between the motor rotor (2) and the through hole (10) to prevent propellant from entering the motor cavity;
a second sealing module provided on the mounting seat (1) and located downstream of the first sealing module for forming a pneumatic seal between the motor rotor (2) and a through hole (10) and for diverting the propellant entering the second sealing module out of the mounting seat (1) to assist the first sealing module in preventing the propellant from entering the motor chamber;
the first sealing module includes:
-a first sealing assembly (30) embedded in the inner wall of the through hole (10), the first sealing assembly (30) being adapted to form a seal between the motor rotor (2) and the through hole (10) and to depressurize the propellant entering the through hole (10) to gasify a portion of the propellant entering the through hole (10);
-a second sealing assembly comprising at least a second sealing element (31), said second sealing element (31) being embedded in the inner wall of said through hole (10) and being arranged downstream of said first sealing assembly (30), said second sealing assembly being intended to form a seal between said motor rotor (2) and said through hole (10) and to depressurize again the propellant entering said through hole (10);
the second sealing module includes:
-an air inlet channel (40) comprising a first air inlet and a first air outlet, the first air inlet being adapted to be connected to an air blowing device;
-an outlet channel (41) comprising a second inlet and a second outlet;
-a sealing channel comprising a first sealing groove (42) and a second sealing groove (43) spaced apart on the inner wall of the through hole (10) in a direction away from the second sealing element (31), the second sealing groove (43) being located downstream of the first sealing groove (42), and the diameter of the second sealing groove (43) being larger than the diameter of the first sealing groove (42), the first sealing groove (42) communicating with a second inlet, the second sealing groove (43) communicating with a first outlet for forming a pneumatic seal between the motor rotor (2) and the through hole (10) while conducting the propellant entering the first sealing groove (42) out of the second outlet; wherein,
high-pressure gas entering through the first gas inlet enters the second sealing groove (43) from the first gas outlet, and then enters the first sealing groove (42) through a gap between the first sealing groove (42) and the second sealing groove (43) to form a backflow so as to push the propellant into the first sealing groove (42).
2. A shaft seal arrangement for a liquid rocket engine according to claim 1, wherein: first seal assembly (30) are the annular, and are close to the interval is equipped with two at least decompression groove (32) on the medial surface of motor rotor (2), decompression groove (32) are used for the process the propellant steps down.
3. A shaft seal arrangement for a liquid rocket engine according to claim 1, wherein: the second sealing element (31) is close to the inner side face of the motor rotor (2) and is provided with at least one elastic sheet (33), and the elastic sheet (33) is used for being in interference fit with the motor rotor (2) and bending towards the direction of the first sealing assembly (30) so as to form sealing between the motor rotor (2) and the through hole (10).
4. A shaft seal arrangement for a liquid rocket engine according to claim 3, wherein: the number of the elastic pieces (33) on each second sealing piece (31) is 2, the two elastic pieces (33) are arranged at intervals, and the interference is 0.1-0.2 mm, so that sealing is formed between the motor rotor (2) and the through hole (10), and the propellant entering the through hole (10) is depressurized again.
5. A shaft seal arrangement for a liquid rocket engine according to claim 1, wherein: the quantity of second sealing member (31) is 2, two be equipped with between second sealing member (31) one with mount pad (1) and first seal assembly (30) all link to each other retaining ring (34), retaining ring (34) are close to one side of motor rotor (2) is used for the subsides to be located on motor rotor (2) to cut off two second sealing member (31).
6. A shaft seal arrangement for a liquid rocket engine according to claim 5, wherein: and a leakage-proof gasket is arranged between the check ring (34) and the mounting seat (1), and the check ring (34), the mounting seat (1) and the first sealing assembly (30) are connected through bolts.
7. A shaft seal arrangement for a liquid rocket engine according to claim 1, wherein: the first sealing groove (42) and the second sealing groove (43) are both annular or rectangular.
8. A shaft seal arrangement for a liquid rocket engine according to claim 1, wherein: the gas introduced into the first gas inlet is inert gas, and the pressure of the inert gas is 0.2-0.5 MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110017966.6A CN112728087B (en) | 2021-01-07 | 2021-01-07 | Shaft seal device for liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110017966.6A CN112728087B (en) | 2021-01-07 | 2021-01-07 | Shaft seal device for liquid rocket engine |
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| Publication Number | Publication Date |
|---|---|
| CN112728087A CN112728087A (en) | 2021-04-30 |
| CN112728087B true CN112728087B (en) | 2023-03-24 |
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| CN202110017966.6A Active CN112728087B (en) | 2021-01-07 | 2021-01-07 | Shaft seal device for liquid rocket engine |
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Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2589955B1 (en) * | 1985-11-08 | 1989-12-08 | Sealol | TURBOPUMP SEALING DEVICE |
| FR3008749B1 (en) * | 2013-07-22 | 2015-08-28 | Snecma | CENTRIFUGAL PUMP, ESPECIALLY FOR FEEDER ENGINES |
| CN204961831U (en) * | 2015-09-25 | 2016-01-13 | 金川集团股份有限公司 | Non -contact labyrinth seals |
| CN107387261B (en) * | 2017-08-25 | 2023-05-30 | 西安航天动力研究所 | Combined mechanical sealing device |
| CN107975600A (en) * | 2017-11-23 | 2018-05-01 | 西安航天动力研究所 | A kind of self forcing cooling refractory machinery seals device |
| RU2691414C1 (en) * | 2018-08-06 | 2019-06-13 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Method of providing tightness of turbo-pump unit under conditions of high vibration loads |
| CN109519304A (en) * | 2018-12-26 | 2019-03-26 | 北京星际荣耀空间科技有限公司 | Thrust regulating valve and rocket engine |
| CN109779947B (en) * | 2019-03-01 | 2024-05-24 | 北京星际荣耀空间科技有限公司 | Dynamic sealing device suitable for low-temperature high-speed reuse |
| CN110030381B (en) * | 2019-03-12 | 2024-06-21 | 北京星际荣耀空间科技股份有限公司 | Be suitable for high-speed high pressure to use dynamic seal device and aircraft |
| 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 |
| CN111502864B (en) * | 2020-04-16 | 2021-07-20 | 西安航天动力研究所 | Open-cycle liquid oxygen kerosene engine system and use method thereof |
-
2021
- 2021-01-07 CN CN202110017966.6A patent/CN112728087B/en active Active
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