CN114941586A - Double-medium-driven pre-booster pump and starting method of low-temperature liquid rocket engine - Google Patents
Double-medium-driven pre-booster pump and starting method of low-temperature liquid rocket engine Download PDFInfo
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- CN114941586A CN114941586A CN202210613042.7A CN202210613042A CN114941586A CN 114941586 A CN114941586 A CN 114941586A CN 202210613042 A CN202210613042 A CN 202210613042A CN 114941586 A CN114941586 A CN 114941586A
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- 239000007788 liquid Substances 0.000 title claims abstract description 89
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000007789 gas Substances 0.000 claims abstract description 164
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims abstract description 63
- 238000007667 floating Methods 0.000 claims description 22
- 238000001816 cooling Methods 0.000 claims description 17
- 239000002826 coolant Substances 0.000 claims description 14
- 239000012530 fluid Substances 0.000 claims description 12
- 230000009977 dual effect Effects 0.000 claims description 11
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 239000000110 cooling liquid Substances 0.000 claims description 8
- 239000002737 fuel gas Substances 0.000 claims description 8
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 238000005192 partition Methods 0.000 claims description 6
- 239000003380 propellant Substances 0.000 claims description 6
- 238000010146 3D printing Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 description 6
- 238000003756 stirring Methods 0.000 description 5
- 230000004323 axial length Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000009987 spinning Methods 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000011295 pitch Substances 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
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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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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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
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
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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
- F04D29/083—Sealings especially adapted for elastic fluid 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a pre-booster pump for a rocket engine, in particular to a dual-medium driven pre-booster pump and a starting method of a low-temperature liquid rocket engine. The technical problems that the starting energy requirement of the existing engine is large and the quality of a starting gas cylinder is high are solved. The pre-booster pump comprises a rotating shaft, a nozzle ring, a pre-booster pump wheel, a liquid turbine, a liquid oxygen outlet pipe, a gas outlet pipe and a gas turbine, wherein the pre-booster pump wheel, the liquid turbine, the liquid oxygen outlet pipe, the gas outlet pipe and the gas turbine are arranged on the rotating shaft and are sequentially connected; the liquid oxygen outlet pipe comprises a bearing seat, a volute pipeline, a flow guide blade grid and a flow guide hole which are arranged at the left end of the volute pipeline, and a gas collecting annular cavity arranged at the right end of the volute pipeline; the nozzle ring is arranged on the right side of the gas collecting ring cavity; a left bearing and a right bearing are arranged between the bearing seat and the rotating shaft; the pre-booster pump wheel is arranged at the left end of the rotating shaft, the shell of the pre-booster pump wheel is fixedly connected with the liquid oxygen outlet pipe, and the outlet of the pre-booster pump wheel corresponds to the guide vane cascade; the liquid turbine is fixed at the right end of the pre-supercharging pump wheel, and the outlet of the liquid turbine corresponds to the diversion hole.
Description
Technical Field
The invention relates to a pre-booster pump for a rocket engine, in particular to a dual-medium driven pre-booster pump and a starting method of a low-temperature liquid rocket engine.
Background
The low-temperature liquid rocket engine generally adopts a propellant conveying prepressing technology. The pre-booster pump pre-boosts the propellant to ensure that the main pump does not generate cavitation under the lower pressure of the storage tank. The high-pressure gas is adopted to drive the pre-booster pump to start rotation, which is one of effective ways for starting the rocket engine at the upper stage. The high-pressure gas drives the pre-booster pump to start rotating and boost pressure, the boosted propellant enters the fuel gas generator through the oxygen main pump to burn, high-temperature and high-pressure fuel gas is generated to drive the main turbine pump to work, and the engine gradually enters a stable working condition. The pre-booster pump under the stable working condition is switched to be driven by high-pressure liquid oxygen behind the oxygen main pump until the engine is shut down.
At present, a low-thrust liquid rocket engine is mainly started by driving a main turbine pump through external energy, and the required external energy is large due to the large power of the main turbine pump. The engine is started by adopting high-pressure gas to drive the low-power pre-booster pump, the pressure and the flow of the required gas are small, the structural mass of the gas storage cylinder can be reduced, and the effective load of the running rocket engine is improved.
The pre-booster pump generally comprises a turbine, a pre-booster pump wheel, a nozzle, an outlet pipe and other main component structures. The outlet pipe is one of the key parts of the pre-booster pump, and is used for collecting high-speed fluid behind the pre-booster pump wheel, further reducing the speed and boosting the pressure, and improving the efficiency of the pre-booster pump. For the outlet pipe of the volute type pre-booster pump, a flow guide cascade structure is usually arranged between the booster pump impeller and the outlet pipe to rectify high-speed fluid at the outlet of the pre-booster pump impeller and match the flow characteristics of the outlet of the booster pump impeller and the inlet of the volute type outlet pipe, so that the efficiency of the pre-booster pump is further improved. The traditional outlet pipe and the guide vane cascade of the pre-booster pump are both formed by casting, the production and manufacturing period is long, the guide vane cascade is fixed on the outlet pipe structure in a mechanical mode such as screw connection, the structure quality is relatively heavy, the structure is relatively complex, and the working reliability of the pre-booster pump is influenced.
Disclosure of Invention
The invention aims to solve the technical problems that the required starting energy is larger and the quality of a starting gas cylinder is higher due to the fact that an existing upper-stage engine is generally started by driving a main turbine pump, and provides a double-medium-driven pre-booster pump and a starting method of a low-temperature liquid rocket engine.
The invention provides a double-medium-driven pre-booster pump structure which comprises an air turbine acting on an engine starting stage and a liquid turbine acting on an engine stabilizing stage, wherein the two turbines drive the same pre-booster pump wheel. The working requirements of the engine system are met by coordinating the working matching among various flow systems such as a pre-booster pump air turbine flow path, a liquid turbine flow path, a pump boosting path, a cooling bearing flow path and the like.
The technical solution of the invention is as follows:
the utility model provides a two medium drive's booster pump in advance which characterized in that:
the device comprises a rotating shaft, a nozzle ring, a pre-booster pump wheel, a liquid turbine, a liquid oxygen outlet pipe, a gas outlet pipe and a gas turbine, wherein the pre-booster pump wheel, the liquid turbine, the liquid oxygen outlet pipe, the gas outlet pipe and the gas turbine are arranged on the rotating shaft and are sequentially connected;
the liquid oxygen outlet pipe and the gas outlet pipe are both of volute structures;
the liquid oxygen outlet pipe comprises a bearing seat, a volute pipeline arranged outside the bearing seat, a flow guide vane cascade and a flow guide hole arranged at the left end of the volute pipeline, and a gas collecting annular cavity arranged at the right end of the volute pipeline;
the nozzle ring is arranged on the right side of the gas collecting ring cavity and forms a cavity with the gas collecting ring cavity;
the gas outlet pipe is arranged on the right side of the nozzle ring and is fixedly connected with the liquid oxygen outlet pipe;
a left bearing and a right bearing are arranged between the bearing seat and the rotating shaft;
the pre-booster pump wheel is arranged at the left end of the rotating shaft, the shell of the pre-booster pump wheel is fixedly connected with the liquid oxygen outlet pipe, and the outlet of the pre-booster pump wheel corresponds to the guide vane cascade; a liquid turbine inlet is arranged on the shell of the pre-booster pump wheel;
the liquid turbine is fixed at the right end of the pre-booster pump wheel, and an outlet of the liquid turbine corresponds to the flow guide hole; the guide vane cascade and the guide holes are arranged on the left side wall of the volute pipeline;
the gas collecting ring cavity is provided with a gas inlet; the nozzle ring is provided with a plurality of gas nozzles which are communicated with the gas collecting ring cavity and the gas turbine.
Further, a gas baffle is arranged in the gas collecting ring cavity and is arranged on one side of the gas inlet.
Furthermore, the width b of the guide hole is 3-5 cascade pitches more than the full flow width of the guide cascade;
the thickness of the gas baffle plate is 3-5 mm;
the gas baffle is located between the gas inlet of the gas collecting ring cavity and the last nozzle inlet downstream of the nozzle ring.
Further, the middle diameter surface of the flow guide hole is coaxial with the middle diameter surface of the outlet of the liquid turbine blade cascade; an included angle beta between the diversion hole and the left end face of the liquid oxygen outlet pipe is alpha- (1-3 degrees), wherein alpha is the angle of the fluid at the outlet of the liquid turbine.
Further, the rotating shaft is a hollow rotating shaft; a labyrinth seal is arranged between the pre-booster pump wheel and the left end face of the bearing seat; a cooling bearing channel is arranged between the left bearing and the right bearing; a cooling liquid inlet is formed in the position, located at the right end of the right bearing, of the hollow rotating shaft; the left end of the hollow rotating shaft is provided with a cooling liquid outlet communicated with the inlet of the pre-booster pump wheel;
a left floating ring and a right floating ring are arranged between the air turbine and the right bearing, and the pressure relationship of the left floating ring and the right floating ring is as follows: p2 < P1.
Further, the liquid oxygen outlet pipe is integrally formed by 3D printing;
and the liquid oxygen outlet pipe is connected with the gas outlet pipe through a bolt.
Furthermore, the bearing seat is of a hollow cylindrical structure, 6-10 reinforcing ribs are arranged between the mounting positions of the left bearing and the right bearing, and the thickness of each reinforcing rib is 2-4 mm; the gas outlet pipe is provided with 8-12 reinforcing ribs, and the thickness of each reinforcing rib is 2-5 mm;
the pressure of high-pressure gas in the gas collection annular cavity is 6-10 MPa; the flow speed of the high-speed liquid flowing into the pre-booster pump wheel is 16-20 m/s.
The starting method of the low-temperature liquid rocket engine based on the double-medium-driven pre-booster pump is characterized by comprising the following steps of:
1) introducing high-pressure gas into the gas collecting annular cavity, driving the gas turbine to drive the pre-booster pump to start rotation and boost pressure, enabling the boosted propellant to enter the fuel gas generator through the oxygen main pump for combustion, generating high-temperature high-pressure fuel gas to drive the main turbine pump to act, and enabling the engine to gradually enter a stable working condition;
2) under the condition of stable working conditions, high-pressure liquid oxygen is accelerated through the liquid nozzle, after the liquid turbine is driven, the high-pressure liquid oxygen is converged into an outlet of the pre-booster pump and mixed with the liquid oxygen behind the pre-booster pump, and the liquid turbine (1) drives the pre-booster pump to work through the relay of the high-pressure liquid oxygen until the engine enters into stable state operation.
Further, in the step 1), after the driving gas turbine (2) drives the pre-booster pump to start rotation and boost pressure, the method also comprises a bearing cooling step which is continuously executed until the engine enters a steady state to work:
high-pressure liquid oxygen at the outlet of the pre-booster pump is guided to a labyrinth seal between the bearing seat and the pre-booster pump, flows into a coolant channel between the two bearings after being throttled by the labyrinth seal, cools the left bearing and the right bearing in sequence, then enters the hollow rotating shaft from a coolant inlet at the right end of the right bearing on the hollow rotating shaft, and returns to the inlet of the pre-booster pump wheel from a coolant outlet at the left end of the hollow rotating shaft.
Further, in the step 1), when the gas turbine works, the pressure relationship between the left floating ring and the right floating ring is ensured as follows: p2 < P1.
The invention has the beneficial effects that:
(1) the double-medium-driven pre-booster pump provided by the invention has the advantages of good working matching and high balance degree of various flow paths such as a high-pressure gas driven gas turbine path, a high-pressure liquid driven liquid turbine path, a pre-booster pump boosting path, a bearing cooling flow path and the like.
(2) According to the double-medium-driven pre-booster pump provided by the invention, the nozzle ring is connected to the outlet pipe through the screw, so that the problem that the nozzle structure is deformed in size due to the traditional welding connection mode is solved, the replaceability of the nozzle ring is improved, the maintainability of the pre-booster pump structure is improved, and the technical problems that the internal quality of a welding seam is difficult to detect due to the limited structural space of the traditional welding connection mode are solved.
(3) The starting method of the low-temperature liquid rocket engine has the advantages that the gas drives the pre-booster pump to start and boost pressure, so that the engine can be reliably started, the energy of starting gas is effectively reduced, the quality of a starting gas cylinder is reduced, and the effective load of the carrier rocket engine is improved.
(4) According to the double-medium driven pre-booster pump provided by the invention, the gas partition plate is arranged in the gas collecting ring cavity, and the gas partition plate can enable high-speed gas entering the gas collecting ring cavity to enter a part of the gas inlet nozzle ring to drive the gas turbine to do work earlier, so that the circulation effect of the gas in the gas collecting ring cavity is eliminated, the gas work efficiency is improved, the pressure and the flow of a required driving gas source can be reduced, and the structural quality of a gas cylinder is reduced.
(5) The invention provides a double-medium driven pre-booster pump, wherein a flow guide blade grid of the pre-booster pump is embedded at the inlet side of a flow channel of an outlet pipe and is integrally formed with the outlet pipe. The guide vane cascade of conventional design is generally fixed on the volute structure through mechanical connection such as screw tightening, and the guide vane cascade and the volute structure are designed in an integrated manner, so that on one hand, the overall axial length can be reduced, the structure is more compact, the required structural space is smaller, on the other hand, the mechanical connection method of the guide vane cascade of conventional design is eliminated, and the structural reliability is higher. In addition, the guide vane cascade and the volute structure are integrated, so that the structural rigidity of the bearing seat on the inner side of the volute structure can be improved, the rotating system can run more stably, and the structural vibration of the pre-booster pump is reduced.
(6) According to the double-medium driven pre-booster pump provided by the invention, the structure of the liquid oxygen outlet pipe is provided with the diversion hole of the liquid turbine outlet, and the installation angle beta of the inlet side of the diversion hole is adapted to the angle of the fluid at the outlet of the liquid turbine; the width b of the flow guide hole is 3-5 blade grid distances more than the full flow width of a single-nozzle driving liquid turbine blade grid. Aiming at a low-power pre-booster pump, a flow guide structure is not generally arranged behind a liquid turbine. The flow guide holes are formed in the volute structure, so that high-speed liquid behind the liquid turbine can be stably guided into the volute flow channel, the flow loss is reduced, and the efficiency of the pre-booster pump is improved.
(7) According to the double-medium-driven pre-booster pump provided by the invention, the gas collecting annular cavity of the liquid oxygen outlet pipe is an annular cavity with a shape changing on the wall surface, the annular cavity is naturally formed by the wall surface of the volute and the structure of the nozzle ring, and the gas collecting annular cavity and the volute structure are integrally designed, so that the axial length of the pre-booster pump is reduced, the structure is more compact, and the required structural space is smaller.
(8) According to the double-medium-driven pre-booster pump provided by the invention, the liquid oxygen outlet pipe adopts an integrated design, the flow characteristics of the outlet of the liquid turbine and the inlet of the gas turbine are considered, the structure is compact, the axial size of the pre-booster pump is shortened, the weight of the pre-booster pump is reduced, the working system of the pre-booster pump is simplified, and the working reliability is improved.
(9) The liquid oxygen outlet pipe in the double-medium-driven pre-pressurizing pump provided by the invention adopts a 3D printing integrated design, and compared with a casting molding technology, the development period is shortened.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of a dual medium-driven pre-booster pump according to the present invention;
FIG. 2 is a schematic structural diagram of a liquid oxygen outlet pipe in an embodiment of the dual medium-driven pre-booster pump of the present invention;
FIG. 3 is a cross-sectional view A-A of FIG. 2;
FIG. 4 is an exploded schematic view of a liquid oxygen outlet pipe and a nozzle ring (the dotted arrow represents the gas circulation direction) in an embodiment of the dual medium-driven pre-booster pump of the present invention;
FIG. 5 is a schematic diagram of the flow paths of an embodiment of the dual medium driven pre-booster pump of the present invention (the realized arrows represent the liquid oxygen flow direction and the dashed arrows represent the gas flow direction).
Reference numerals are as follows: 1-liquid turbine, 2-gas turbine, 3-pre-booster pump wheel, 32-shell, 321-liquid turbine inlet, 33-labyrinth seal, 34-coolant channel, 35-reinforcing fin, 4-liquid oxygen outlet pipe, 41-bearing seat, 42-volute pipeline, 43-guide cascade, 44-guide hole, 45-gas collecting ring cavity, 451-gas inlet, 452-gas baffle; 5-rotating shaft, 51-cooling liquid inlet, 52-cooling liquid outlet, 6-nozzle ring, 61-gas nozzle; 7-gas outlet pipe, 71-reinforcing rib, 72-revolution speed transducer; 8-left bearing, 9-right bearing, 10-left floating ring and 11-right floating ring.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1 to 4, the double-medium-driven pre-booster pump of the present invention comprises a rotating shaft 5, a nozzle ring 6, and a pre-booster pump impeller 3, a liquid turbine 1, a liquid oxygen outlet pipe 4, a gas outlet pipe 7 and a gas turbine 2 which are arranged on the rotating shaft 5 and connected in sequence. The pre-booster pump is of a cantilever type structure, and the rotating shaft 5 is supported by two bearings. The liquid turbine 1 and the pre-booster pump wheel 3 are welded into a whole, and the air turbine 2 is separately arranged on the right side.
The liquid oxygen outlet pipe 4 includes a bearing seat 41, a volute conduit 42 disposed outside the bearing seat 41, a guide vane cascade 43 and a guide hole 44 disposed at the left end of the volute conduit 42, and a gas collecting annular chamber 45 disposed at the right end of the volute conduit 42. A left bearing 8 and a right bearing 9 are arranged between the bearing seat 41 and the rotating shaft 5.
As shown in fig. 2 and 3, a diversion hole 44 is formed in the wall surface of the liquid oxygen outlet pipe, and the outlet fluid of the diversion liquid turbine 1 is mixed with the fluid entering from the diversion cascade 43 in the volute. The middle diameter surface of the flow guide hole 44 is coaxial with the middle diameter surface of the cascade outlet of the liquid turbine 1, the included angle between the flow guide hole 44 and the left end surface of the liquid oxygen outlet pipe 4 is beta-alpha- (1-3 degrees), wherein alpha is the angle of the liquid turbine outlet fluid, and the included angle beta between the flow guide hole 44 and the left end surface of the liquid oxygen outlet pipe 4 is 1-3 degrees smaller than the angle alpha of the liquid turbine 1 outlet fluid. The width b of the diversion hole 44 is 3-5 cascade pitches more than the full flow width of the diversion cascade 43, and the outlet installation angle of the diversion hole 44 is set as an axial outlet.
The gas collecting ring cavity 45 is provided with a gas inlet 451; the nozzle ring 6 is provided with a plurality of gas nozzles 61 communicating the gas collecting ring chamber 45 and the gas turbine 2. The gas collecting ring cavity 45 and the nozzle ring 6 form a closed cavity structure for collecting high-pressure gas entering from the gas inlet 451, so that the axial length of the pre-booster pump is shortened, and the structural weight is reduced. The gas turbine 2 is a local gas inlet structure, a gas partition plate 452 is arranged in the gas collecting ring cavity 45, the gas partition plate 452 is positioned between a gas inlet 451 of the gas collecting ring cavity 45 and the last nozzle inlet at the downstream of the nozzle ring 6, and the gas partition plate 452 enables high-speed gas entering the gas collecting ring cavity 45 tangentially to enter the nozzle ring 6 earlier to drive the gas turbine to do work, so that the circulation effect of the gas in the gas collecting ring cavity 45 is eliminated, and the overall efficiency of the gas turbine 2 is improved. The thickness of the gas barrier 452 is 3 to 5 mm. Bearing frame 41 is hollow tubular structure, sets up 6 ~ 10 enhancement fins 35 in the middle of left bearing 8 and the 9 mounted position of right bearing, strengthens fin 35 thickness 2 ~ 4 mm. The pressure of high-pressure gas in the gas collection annular cavity 45 is 6-10 MPa; the flow velocity of the high-speed liquid flowing from the pre-booster pump wheel 3 is 16-20 m/s.
As shown in figure 4, the nozzle ring 6 is arranged on the right side of the gas collecting ring cavity 45 and is connected to the right side of the gas collecting ring cavity 45 of the liquid oxygen outlet pipe 4 through screws, so that the size deformation of the nozzle structure caused by the traditional welding connection mode is avoided, and the replaceability of the nozzle ring 6 and the maintainability of the pre-booster pump structure are also improved.
2 packing portions of the air turbine set up the location ring structure, avoided the less air turbine 2 of axial yardstick and the not high problem of 5 splined connection radial positioning precision of pivot.
Liquid oxygen outlet pipe 4 prints integrated into one piece for 3D. The compactness of the whole structure of the pre-booster pump is improved by integrally designing the guide vane cascade 43 and the volute structure, the liquid turbine outlet and the volute structure and the gas turbine inlet and the volute structure. The liquid oxygen outlet pipe 4 is of a volute structure with a variable cross section and capable of rotating around the middle, and two bearings (a left bearing 8 and a right bearing 9) are placed in the liquid oxygen outlet pipe 4 and used for supporting the whole rotating system.
The guide vane cascade 43 is embedded in the volute and is integrally formed with the liquid oxygen outlet pipe 4, and the number of the guide vane cascade 43 is required to be prevented from being coupled with the number of the blades of the pre-booster pump wheel 3, so that excitation is generated by unsteady flow of dynamic and static interference. And 3D printing and manufacturing processes are adopted for integral forming, so that the bearing supporting rigidity is improved. The guide vane cascade 43, the volute and the pre-booster pump wheel 3 are designed in a combined mode, so that the separation loss inside the guide vane cascade 43 is reduced, and the overall efficiency of an outlet pipe of the pre-booster pump is improved.
The impeller of the pre-booster pump wheel 3 is arranged at the left end of the rotating shaft 5, the shell 32 of the pre-booster pump wheel is fixedly connected with the liquid oxygen outlet pipe 4, and the outlet of the pre-booster pump wheel 3 corresponds to the guide vane cascade 43; the casing 32 of the pre-booster pump wheel 3 is provided with an inlet of a liquid turbine 321; the liquid turbine 1 is fixed at the right end of the impeller of the pre-booster pump wheel 3, and the outlet of the liquid turbine corresponds to the diversion hole 44; both the guide vane cascade 43 and the guide holes 44 are disposed on the left side wall of the volute conduit 42. The liquid turbine 1 is a single-nozzle local air inlet structure, in order to adapt to the outlet flow of the liquid turbine 1, a flow guide hole 44 is formed in the wall surface of the liquid oxygen outlet pipe 4, and the outlet fluid of the flow guide liquid turbine is mixed with the fluid in the volute. The inlet installation angle beta of the diversion hole 44 is matched with the outlet fluid angle of the liquid turbine 1. Since the axial length of the pilot hole 44 is small, the outlet installation angle of the pilot hole 44 is set to be an axial outlet.
The rotating shaft 5 is a hollow rotating shaft; a labyrinth seal 33 is arranged between the impeller of the pre-booster pump wheel 3 and the left end surface of the bearing block 41; a coolant channel 34 is arranged between the left bearing 8 and the right bearing 9; a cooling liquid inlet 51 is formed in the position, located at the right end of the right bearing 8, of the hollow rotating shaft; the left end of the hollow rotating shaft is provided with a cooling liquid outlet 52 communicated with the inlet of the pre-booster pump wheel 3; a left floating ring 10 and a right floating ring 11 are arranged between the air turbine 2 and the right bearing 9, and the pressure relationship between the left floating ring 10 and the right floating ring 11 is as follows: p2 < P1.
The gas outlet pipe 7 is also of a volute type structure. The gas flow in the volute type gas outlet pipe 7 is smooth enough, the pressure P2 is ensured to be less than P1 when the gas turbine 2 works, the phenomenon that the driving gas reversely flows into the cavity of the pre-booster pump to cause cavitation of the pre-booster pump is prevented, and meanwhile, the pressure P2 is also reduced as much as possible, so that the working pressure ratio of the gas turbine 2 is improved, and the working capacity of the gas turbine 2 is ensured. The pressure P1 is not too high after cooling the bearing, so as to prevent the loss caused by too high flow rate of the liquid for cooling the bearing path leaking to the gas turbine flow path.
The pump speed is measured at the right end of the pre-booster pump and a speed sensor 72 is fitted to the gas outlet pipe 7. The gas outlet pipe 7 is provided with a reinforcing rib 71, so that the structural rigidity of the turbine exhaust pipe is improved, the structural vibration is reduced, and the rotating speed measurement precision is improved.
As shown in fig. 5, the flow structure of the pre-booster pump includes a high-pressure gas-driven gas turbine path, a high-pressure liquid-driven liquid turbine path, a pre-booster pump booster path, and a bearing cooling flow path.
Gas turbine flow path: after entering the gas collecting ring cavity 45, the high-pressure gas is accelerated by the nozzle ring 6 to drive the gas turbine 2 to do work, and then is exhausted to the outside through the turbine exhaust pipe. When the air turbine 2 drives the rotor to do work, the liquid turbine 1 is in a spinning stirring power consumption state.
Liquid turbine flow path: the high-pressure liquid oxygen is accelerated through the liquid nozzle, and after the liquid nozzle drives the liquid turbine 1, the high-pressure liquid oxygen is converged into the outlet of the pre-booster pump wheel 3 and is mixed with the liquid oxygen behind the pre-booster pump wheel 3. When the liquid turbine 1 drives the rotor to do work, the gas turbine 2 is in a spinning state, and the gas turbine 2 is in the spinning state at the moment, so that the stirring power consumption is small and can be ignored.
Pre-pressurizing pump to increase road pressure: the gas turbine 2/the liquid turbine 1 drives the pre-booster pump wheel 3 to rotate and boost pressure, low-pressure liquid oxygen at the inlet of the pre-booster pump wheel 3 is boosted to the outlet of the pre-booster pump wheel 3, and is mixed with the liquid oxygen behind the liquid turbine 1 and flows to an oxygen main pump.
Cooling the bearing flow path: the high-pressure liquid oxygen after the pre-booster pump wheel 3 is guided to flow through the labyrinth seal 33, throttled, and then passes through the coolant channel 34 to sequentially cool the left bearing 8 and the right bearing 9, and then flows into the rotating shaft 5 from the coolant inlet of the rotating shaft 5, passes through the hollow structure of the rotating shaft 5, and then flows back to the inlet of the pre-booster pump from the coolant outlet 52. Two floating ring sealing structures (a left floating ring 10 and a right floating ring 11) are arranged between the bearing cooling flow path and the air turbine flow path, so that the phenomenon that the flow of liquid oxygen of the cooling bearing path leaking to the outside is too large to cause loss is avoided.
The labyrinth seal and the two floating ring seals are arranged in a coordinated manner to achieve throttling capacity, so that the flow of a bearing cooling flow path is ensured to meet the bearing cooling requirement. At the same time, the gas driving the gas turbine is prevented from flowing back to the pre-booster pump cavity to cause cavitation of the pre-booster pump.
Meanwhile, the invention also provides a starting method of the low-temperature liquid rocket engine based on the dual-medium driven pre-booster pump, which comprises the following steps of:
1) high-pressure gas is introduced into the gas collecting annular cavity 45, the gas turbine 2 is driven to drive the pre-pressurizing pump to start rotation and pressurize, the pressurized propellant enters the fuel gas generator through the oxygen main pump to be combusted, high-temperature and high-pressure fuel gas is generated to drive the main turbine pump to do work, and the engine gradually enters a stable working condition; the gas turbine 2 is operated with a pressure P2 < P1.
After entering the gas collecting ring cavity 45, the high-pressure gas is accelerated through the nozzle ring 6 to drive the gas turbine 2 to do work, and then is discharged to the outside through the gas outlet pipe 7. When the gas turbine 2 drives the pre-booster pump to work, the liquid turbine 1 is in a spinning stirring power consumption state, and when the output power of the gas turbine 2 is designed, the stirring power consumption of the liquid turbine 1 needs to be considered.
2) Under the condition of stable working conditions, high-pressure liquid oxygen is accelerated through the liquid nozzle, after the liquid turbine 1 is driven, the high-pressure liquid oxygen is converged into an outlet of the pre-booster pump and mixed with the liquid oxygen behind the pre-booster pump, and the liquid turbine 1 drives the pre-booster pump to work through the relay of the high-pressure liquid oxygen until the engine enters into stable work.
When the liquid turbine 1 drives the pre-supercharging pump wheel to do work, the air turbine 2 is in a self-rotating state, and when the liquid turbine 1 is designed to output power, the self-rotating stirring power consumption of the air turbine 2 is small and can be ignored.
In addition, in order to meet the requirement of bearing cooling, the step 1) of driving the gas turbine 2 to drive the pre-booster pump to start rotating and boosting pressure further comprises a bearing cooling step of continuously executing until the engine enters into steady-state operation:
high-pressure liquid oxygen at the outlet of the pre-booster pump is guided to a labyrinth seal between the bearing seat and the pre-booster pump, flows into a coolant channel 34 between the two bearings after being throttled by the labyrinth seal 33, sequentially cools the two bearings (the left bearing 8 and the right bearing 9), enters the hollow rotating shaft from a coolant inlet 51 at the right end of the right bearing on the hollow rotating shaft, and returns to the inlet of the pre-booster pump impeller 3 from a coolant outlet 52 at the left end of the hollow rotating shaft.
The pre-booster pump is an axial flow pump and comprises two turbines, namely a gas turbine and a liquid turbine. The gas turbine is adopted to drive the pre-booster pump in the starting stage of the engine, and the liquid turbine is adopted to drive the pre-booster pump in the stabilizing stage of the engine. The invention relates to a double-medium driven pre-booster pump, which is suitable for a liquid rocket engine adopting a pre-booster pump starting mode, and improves the working reliability and the structural maintenance of the pre-booster pump while meeting the system requirements of the engine by coordinating the working matching among various flow paths such as an air turbine driving path, a liquid turbine driving path, a pump boosting path, a cooling bearing path and the like. The invention discloses a double-medium driven pre-booster pump which can be popularized and applied to similar liquid rocket engines adopting a pre-booster pump starting mode.
While the foregoing description of the present example and the accompanying drawings represent a preferred embodiment of the present invention, it will be appreciated by those skilled in the art that various changes in design requirements and design parameters may be made without departing from the scope of the invention as defined in the appended claims.
Claims (10)
1. The utility model provides a two medium drive's booster pump in advance which characterized in that:
comprises a rotating shaft (5), a nozzle ring (6), and a pre-booster pump wheel (3), a liquid turbine (1), a liquid oxygen outlet pipe (4), a gas outlet pipe (7) and a gas turbine (2) which are arranged on the rotating shaft (5) and are connected in sequence;
the liquid oxygen outlet pipe (4) and the gas outlet pipe (7) are both in a volute structure;
the liquid oxygen outlet pipe (4) comprises a bearing seat (41), a volute pipeline (42) arranged on the outer side of the bearing seat (41), a flow guide vane cascade (43) and a flow guide hole (44) arranged at the left end of the volute pipeline (42), and a gas collecting ring cavity (45) arranged at the right end of the volute pipeline (42);
the nozzle ring (6) is arranged on the right side of the gas collecting ring cavity (45) and forms a cavity with the gas collecting ring cavity;
the gas outlet pipe (7) is arranged on the right side of the nozzle ring (6) and is fixedly connected with the liquid oxygen outlet pipe (4);
a left bearing (8) and a right bearing (9) are arranged between the bearing seat (41) and the rotating shaft (5);
the pre-booster pump wheel (3) is arranged at the left end of the rotating shaft (5), the shell (32) of the pre-booster pump wheel (3) is fixedly connected with the liquid oxygen outlet pipe (4), and the outlet of the pre-booster pump wheel corresponds to the guide vane cascade (43); a liquid turbine inlet (321) is arranged on the shell (32) of the pre-booster pump wheel (3);
the liquid turbine (1) is fixed at the right end of the pre-booster pump wheel (3), and an outlet of the liquid turbine (1) corresponds to the flow guide hole (44); the guide vane cascade (43) and the guide holes (44) are arranged on the left side wall of the volute pipeline (42);
the gas collecting ring cavity (45) is provided with a gas inlet (451); the nozzle ring (6) is provided with a plurality of gas nozzles (61) which are communicated with the gas collecting ring cavity (45) and the gas turbine (2).
2. The dual medium driven pre-booster pump of claim 1, wherein: a gas baffle plate (452) is arranged in the gas collection annular cavity (45), and the gas baffle plate (452) is arranged on one side of the gas inlet (451).
3. The dual medium driven pre-booster pump of claim 2, wherein: the width b of the guide holes (44) is 3-5 blade grid distances more than the full flow width of the guide blade grids (43);
the thickness of the gas partition plate (452) is 3-5 mm;
the gas baffle (452) is located between the gas inlet (451) of the gas collecting ring cavity (45) and the inlet of the last nozzle (61) downstream of the nozzle ring (6).
4. A dual medium driven pre-booster pump according to claim 1, 2 or 3, wherein: the middle diameter surface of the flow guide hole (44) is coaxial with the middle diameter surface of the cascade outlet of the liquid turbine (1); an included angle beta between the diversion hole (44) and the left end face of the liquid oxygen outlet pipe (4) is alpha- (1-3 degrees), wherein alpha is the fluid outlet angle of the liquid turbine (1).
5. The dual medium driven pre-booster pump of claim 4, wherein: the rotating shaft (5) is a hollow rotating shaft; a labyrinth seal (33) is arranged between the pre-booster pump wheel (3) and the left end face of the bearing seat (41); a cooling bearing channel (34) is arranged between the left bearing (8) and the right bearing (9); a cooling liquid inlet (51) is formed in the position, located at the right end of the right bearing (8), of the hollow rotating shaft; the left end of the hollow rotating shaft is provided with a cooling liquid outlet (52) communicated with the inlet of the pre-booster pump wheel (3);
a left floating ring (10) and a right floating ring (11) are arranged between the air turbine (2) and the right bearing (9), and the pressure relationship between the left floating ring (10) and the right floating ring (11) is as follows: p2 < P1.
6. The dual medium driven pre-booster pump of claim 5, wherein: the liquid oxygen outlet pipe (4) is integrally formed by 3D printing;
the liquid oxygen outlet pipe (4) is connected with the gas outlet pipe (7) through a bolt.
7. The dual medium driven pre-booster pump according to claim 6, wherein the bearing seat (41) is a hollow cylindrical structure, 6-10 reinforcing ribs (35) are arranged between the mounting positions of the left bearing (8) and the right bearing (9), and the thickness of the reinforcing ribs (35) is 2-4 mm; the gas outlet pipe (7) is provided with 8-12 reinforcing ribs (71), and the thickness of each reinforcing rib (71) is 2-5 mm;
the pressure of high-pressure gas in the gas collection annular cavity (45) is 6-10 MPa; the flow speed of the high-speed liquid flowing into the pre-booster pump wheel (3) is 16-20 m/s.
8. A method of starting a cryogenic liquid rocket engine based on a dual medium driven booster pump according to any one of claims 1 to 7, comprising the steps of:
1) high-pressure gas is introduced into the gas collecting annular cavity (45), the gas turbine (2) is driven to drive the pre-booster pump to start rotating and boost pressure, the boosted propellant enters the fuel gas generator through the oxygen main pump to be combusted, high-temperature and high-pressure fuel gas is generated to drive the main turbine pump to do work, and the engine gradually enters a stable working condition;
2) under the condition of stable working conditions, high-pressure liquid oxygen is accelerated through the liquid nozzle, after the liquid turbine (1) is driven, the high-pressure liquid oxygen is converged into an outlet of the pre-booster pump and mixed with the liquid oxygen after the pre-booster pump, and the liquid turbine (1) drives the pre-booster pump to work through the relay of the high-pressure liquid oxygen until the engine enters into stable work.
9. A method of starting a cryogenic liquid rocket engine according to claim 8, wherein:
in the step 1), after the driving gas turbine (2) drives the pre-booster pump to start rotating and boost, the method also comprises a bearing cooling step which is continuously executed until the engine enters into steady-state operation:
high-pressure liquid oxygen at the outlet of the pre-booster pump is guided to a labyrinth seal (33) between a bearing seat (41) and the pre-booster pump, flows into a coolant channel (34) between two bearings after being throttled by the labyrinth seal (33), cools a left bearing (8) and a right bearing (9) in sequence, enters a hollow rotating shaft from a coolant inlet (51) at the right end of the right bearing (9) on the hollow rotating shaft, and returns to the inlet of the pre-booster pump impeller (3) from a coolant outlet (52) at the left end of the hollow rotating shaft.
10. The method of starting a cryogenic liquid rocket engine according to claim 9,
in the step 1), when the air turbine (2) works, the pressure relation between the left floating ring (10) and the right floating ring (11) is ensured as follows: p2 < P1.
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| CN202210613042.7A CN114941586B (en) | 2022-05-31 | 2022-05-31 | Dual-medium-driven pre-booster pump and starting method of low-temperature liquid rocket engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116291960A (en) * | 2023-04-23 | 2023-06-23 | 北京星河动力装备科技有限公司 | Gas collecting structure, turbo pump and rocket engine |
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| US5074762A (en) * | 1988-12-12 | 1991-12-24 | Societe Europeenne De Propulsion | Compact structural assembly for feeding propellants at high pressure to a rocket engine |
| FR2964425A1 (en) * | 2010-09-03 | 2012-03-09 | Snecma | TURBOPOMPE, ESPECIALLY FOR FEEDING ROTOR MOTORS |
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| CN114941586B (en) | 2024-09-10 |
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