CN109372655A - The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts - Google Patents
The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts Download PDFInfo
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- CN109372655A CN109372655A CN201811528924.3A CN201811528924A CN109372655A CN 109372655 A CN109372655 A CN 109372655A CN 201811528924 A CN201811528924 A CN 201811528924A CN 109372655 A CN109372655 A CN 109372655A
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- entrance
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- precompressed
- turbine
- pipeline
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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
Abstract
The present invention relates to the pre- pressure charging systems of gas-liquid parallel drive and method that a kind of high-altitude low entry pressure starts, in order to solve main pump cavitation, the technical issues of avoiding aircraft carrying capacity caused by promoting tank pressure to decline simultaneously, the entrance of pre- press pump is communicated with propellant tank outlet, the entrance that the outlet of pre- press pump passes through the first piping connection to mixing machine, another entrance that the outlet of precompressed turbine passes through the second piping connection to mixing machine, the entrance that the outlet of mixing machine passes through third piping connection to main pump, a part of propellant of main pump outlet is connect by the 4th pipeline with precompressed turbine inlet, flow is controlled by throttle, remaining propellant of main pump outlet enters downstream pipe；High pressure gas supply system is connect by the 5th pipeline with the entrance of precompressed turbine, and high pressure gas check valve is arranged in the 5th pipeline, and switching valve accesses the second pipeline, and check valve is arranged in the 4th pipeline.
Description
Technical field
The present invention relates to a kind of pre- pressure charging systems of gas-liquid parallel drive and method started suitable for high-altitude low entry pressure.
Background technique
Big flow, high revolving speed, high lift turbopump-fed liquid rocket engine in, pre- pressure charging system is usually in stable section
For improving the inlet pressure of main pump, preventing main pump from cavitation occur.Pre- pressure charging system generally comprise coaxial arrangement pre- press pump and
Precompressed turbine, the entrance of pre- press pump are communicated with the outlet of tank, and the outlet of pre- press pump is connected with the entrance of main pump, precompressed turbine
Outlet is connected to the entrance of main pump by mixing machine.Main pump is connect by another pipeline with precompressed turbine inlet.In steady operation
Section, precompressed turbine pump generally use the high pressure propellant actuated or the use turbine combustion gas compatible with main road propellant after main pump
Driving.But section is started, before main pump does not generate positive lift or thrust chamber is not lighted a fire, no drive energy comes so that pre- press pump
Positive lift is generated, pre- press pump shows as flow resistive element, is degrading the operating condition of main pump instead.Raising is generallyd use thus to start
The mode of section tank pressure prevents main pump from cavitation occur.For the engine of high-altitude start, tank pressure height means
The weight of aircraft propellant tank increases, the weight and volume of pressurising medium increases, and greatly affected the effective of aircraft
Load-carrying ability.
Summary of the invention
In order to solve main pump cavitation, while the technology for avoiding aircraft carrying capacity caused by promoting tank pressure from declining is asked
Topic, the present invention provide the pre- pressure charging system of gas-liquid parallel drive and method that low entry pressure in high-altitude starts.
Technical solution of the invention is as follows:
The pre- pressure charging system of gas-liquid parallel drive that high-altitude low entry pressure starts, including main pump 1, pre- press pump 2, precompressed turbine
3 and mixing machine 5；
Pre- press pump 2 and precompressed turbine 3 are coaxially disposed, and the entrance of pre- press pump 2 is communicated with propellant tank outlet, pre- press pump 2
Outlet one entrance of mixing machine 5 is connected to by the first pipeline 7, the outlet of precompressed turbine 3 is connected to by the second pipeline 8
Another entrance of mixing machine 5, the outlet of mixing machine 5 are connected to the entrance of main pump 1 by third pipeline 9, and main pump 1 exports one
Divide propellant to connect by the 4th pipeline 10 with 3 entrance of precompressed turbine, flow is controlled by throttle 6, main pump 1 exports remaining
Propellant enters downstream pipe；
It is characterized by also including high pressure gas supply system, high pressure gas check valve 11, switching valve 12 and check valves
13；
The high pressure gas supply system is connect by the 5th pipeline 4 with the entrance of precompressed turbine 3, the high pressure gas list
It is arranged in the 5th pipeline 4 to valve 11；
The switching valve 12 is two-position three-way valve, including entrance, outlet A and outlet B, the switching valve 12 by entrance and
It exports A and accesses the second pipeline 8, outlet B leads to the external world；
The check valve 13 is arranged in the 4th pipeline 10.
It is special meanwhile the present invention also provides the pre- boosting method of gas-liquid parallel drive that high-altitude low entry pressure starts
Place is: the following steps are included:
1) it when engine starts to start, issues and instructs to switching valve 12, communicate the entrance of switching valve 12 with outlet B, in advance
The medium of pressure turbine outlet leads to the external world；The entrance of switching valve 12 and outlet A cutting；
2) high pressure gas check valve 11 is opened, high pressure gas enters 3 stator chamber of precompressed turbine, and driving precompressed turbine 3 does work,
Pre- press pump 2 is driven to generate lift, pressurized propellant enters main pump inlet；
3) pressure is greater than the opening pressure of check valve 13 after main pump 1 plays rotation and generate lift, pump under the effect of its power source
When, high pressure propellant enters 3 stator chamber of precompressed turbine, and precompressed turbine 3 is driven to do work jointly with high pressure gas；
4) after the stable conditions of main pump 1, high pressure gas removes gas, and high pressure gas check valve 11 is closed, the high pressure after main pump 1
Propellant continues that precompressed turbine 3 is driven to do work；
5) 12 state of switching valve is restored, and the entrance of switching valve 12 is identical as outlet A, and the medium of precompressed turbine outlet is by mixing
Main road propellant after mixed device and pre- press pump 2 blend and enters 1 entrance of main pump；The entrance of switching valve 12 and extraneous cutting；
Pre- pressure charging system enters steady operation section.
Compared with prior art, the present invention beneficial effect is:
1, the pre- pressure charging system of gas-liquid parallel drive of the present invention, by starting section using the production of drive of high-pressure gas precompressed turbine
Raw positive lift is effectively guaranteed inlet pressure necessary to start section main pump, so that engine has low entry pressure and plays kinetic energy
Power.
2, due to reducing to tank pressure requirements, the volume and weight of tank and pressurising medium reduces the present invention, thus
Improve the carrying capacity of rocket body or high-altitude vehicle.
3, the power that the present invention is needed due to precompressed turbine pump is small, it is low to start required energy, drives energy to the external world
The demand in source is small.
Detailed description of the invention
Fig. 1 is the gas generator of the pre- pressure charging system of the embodiment of the present invention and engine system and the connection structure of main turbine
Schematic diagram.
Wherein appended drawing reference are as follows: the pre- press pump of 1- main pump, 2-, 3- precompressed turbine, the 5th pipeline of 4-, 5- mixing machine, 6- throttling
Circle, the first pipeline of 7-, the second pipeline of 8-, 9- third pipeline, the 4th pipeline of 10-, 11- high pressure gas check valve, 12- switching valve,
13- check valve.
Specific embodiment
Below in conjunction with attached drawing, the present invention is described in detail.
1) system configuration
As shown in Figure 1, the pre- pressure charging system of gas-liquid parallel drive needs to be arranged associated component to switch air-liquid driving medium.
System includes main pump 1, pre- press pump 2, precompressed turbine 3, mixing machine 5, high pressure gas supply system, high pressure gas check valve 11, cuts
Change valve 12 and check valve 13；The entrance of pre- press pump 2 is communicated with reservoir outlet, and the outlet of pre- press pump 2 is connected to by the first pipeline 7
One entrance of mixing machine 5, the outlet of precompressed turbine 3 are connected to another entrance of mixing machine 5 by the second pipeline 8, blending
The outlet of device 5 is connected to the entrance of main pump 1 by third pipeline 9, main pump 1 export a part of propellant by the 4th pipeline 10 with
The connection of 3 entrance of precompressed turbine controls flow by throttle 6, and main pump 1 exports remaining propellant and enters downstream pipe；It is described
High pressure gas supply system is connect by the 5th pipeline 4 with the entrance of precompressed turbine 3, and the setting of high pressure gas check valve 11 exists
In 5th pipeline 4；
Switching valve 12 be two-position three-way valve, for switch precompressed turbine 3 outlet medium communicated with 1 entrance pipe of main pump or
Discharge is extraneous.12 entrance of switching valve connects precompressed turbine outlet pipeline, and outlet A is connected with the mixing machine 5 of 1 entrance of main pump, exports B
It is connected with the external world.Initial state, 12 entrance medium of switching valve and outlet A normal open, while cutting off outlet B；After issuing control instruction,
Entrance is connected to outlet B, while cutting off outlet A.
The propellant that high pressure gas check valve 11 is used to prevent precompressed turbine 3 from exporting enters high pressure gas supply road.
The gas that check valve 13 is used to prevent precompressed turbine 3 from exporting enters pipeline after main pump, while guaranteeing to export in main pump 1
Pressure is opened after being higher than certain value.
Mixing machine 5 is that the propellant blending that precompressed turbine 3 will be driven to do work enters 1 entrance pipe of main pump, is prevented to main pump 1
Work causes to disturb.
High-altitude low entry pressure start gas-liquid parallel drive pre- pressure charging system working method the following steps are included:
1) engine start starts, and the logical control gas of switching valve 12, switching valve 12 commutates, and valve export communicates with the outside world,
Pipeline between the outlet of precompressed turbine 3 and 1 entrance of main pump is cut off；
2) supply high pressure gas: high pressure gas enters precompressed stators chamber by high pressure gas check valve 11, and driving is pre-
Turbine acting is pressed, pre- press pump 2 generates lift, and pressurized propellant enters main pump inlet with larger flow；
3) when main pump 1) its power source effect under play rotation and generate lift, pump after pressure be greater than check valve 13) open pressure
When power, high pressure propellant enters 3 stator chamber of precompressed turbine, and precompressed turbine 3 is driven to do work jointly with high pressure gas；
4) after main pump stable conditions, high pressure gas stops supply, and the high pressure propellant after main pump continues to drive precompressed whirlpool
3 acting of wheel；
5) 12 control chamber of switching valve removes gas, and 12 entrance of switching valve is communicated with 1 entrance of main pump, cuts off with the external world.It has driven pre-
The propellant of pressure turbine 3 enters mixing machine 5, blend with the main road propellant after pre- press pump 2 and enters 1 entrance of main pump.In advance
Pressure charging system enters steady operation section.
Claims (2)
1. the pre- pressure charging system of gas-liquid parallel drive that high-altitude low entry pressure starts, including main pump (1), pre- press pump (2), precompressed whirlpool
Take turns (3) and mixing machine (5)；
The entrance of pre- press pump (2) and precompressed turbine (3) coaxial arrangement, pre- press pump (2) is communicated with propellant tank outlet, pre- press pump
(2) outlet is connected to an entrance of mixing machine (5) by the first pipeline (7), and the outlet of precompressed turbine (3) passes through the second pipe
Road (8) is connected to another entrance of mixing machine (5), and the outlet of mixing machine (5) is connected to main pump (1) by third pipeline (9)
Entrance, main pump (1) exports a part of propellant and connect by the 4th pipeline (10) with precompressed turbine (3) entrance, passes through throttling
It encloses (6) and controls flow, main pump (1) exports remaining propellant and enters downstream pipe；
It is characterized by also including high pressure gas supply system, high pressure gas check valve (11), switching valve (12) and check valves
(13)；
The high pressure gas supply system is connect by the 5th pipeline (4) with the entrance of precompressed turbine (3), the high pressure gas list
It is arranged in the 5th pipeline (4) to valve (11)；
The switching valve (12) is two-position three-way valve, including entrance, outlet A and outlet B, the switching valve (12) by entrance and
A access the second pipeline (8) is exported, outlet B leads to the external world；
The check valve (13) is arranged in the 4th pipeline (10).
2. the pre- boosting method of gas-liquid parallel drive that high-altitude low entry pressure starts, it is characterised in that: the following steps are included:
1) it when engine starts to start, issues and instructs to switching valve (12), communicate the entrance of switching valve (12) with outlet B, in advance
The medium of pressure turbine outlet leads to the external world；The entrance of switching valve (12) and outlet A cutting；
2) high pressure gas check valve (11) are opened, high pressure gas enters precompressed turbine (3) stator chamber, and driving precompressed turbine (3) is done
Function, drives pre- press pump (2) to generate lift, and pressurized propellant enters main pump inlet；
3) pressure is greater than check valve (13) opening pressure after main pump (1) plays rotation and generate lift, pump under the effect of its power source
When, high pressure propellant enters precompressed turbine (3) stator chamber, and precompressed turbine (3) is driven to do work jointly with high pressure gas；
4) after the stable conditions of main pump (1), high pressure gas removes gas, and high pressure gas check valve (11) is closed, the height after main pump (1)
Pressure propellant continues to drive precompressed turbine (3) acting；
5) switching valve (12) state is restored, and the entrance of switching valve (12) is identical as outlet A, and the medium of precompressed turbine outlet is by mixing
Main road propellant after mixed device and pre- press pump (2) blend and enters main pump (1) entrance；The entrance of switching valve (12) and the external world
Cutting；Pre- pressure charging system enters steady operation section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811528924.3A CN109372655A (en) | 2018-12-13 | 2018-12-13 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811528924.3A CN109372655A (en) | 2018-12-13 | 2018-12-13 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
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| CN109372655A true CN109372655A (en) | 2019-02-22 |
Family
ID=65373880
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|---|---|---|---|
| CN201811528924.3A Pending CN109372655A (en) | 2018-12-13 | 2018-12-13 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973246A (en) * | 2019-03-22 | 2019-07-05 | 西安航天动力研究所 | A kind of gas-liquid composite drive precompressed turbine pump configuration and precompressed turbine pump driving method |
| CN110030114A (en) * | 2019-03-22 | 2019-07-19 | 西安航天动力研究所 | A kind of power oscillation damping high efficiency burnt gas mixing structure |
| CN110748437A (en) * | 2019-09-20 | 2020-02-04 | 上海宇航系统工程研究所 | Propellant conveying system |
| CN112196702A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Liquid rocket engine starter and design method thereof |
| CN112628019A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof |
| CN112628018A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | High-thrust liquid rocket engine and low-power-consumption semi-self-starting method thereof |
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| RU2084677C1 (en) * | 1994-12-20 | 1997-07-20 | Игорь Алексеевич Клепиков | Method of starting liquid rocket engine and liquid rocket engine |
| US5873241A (en) * | 1991-05-23 | 1999-02-23 | United Technologies Corporation | Rocket engine auxiliary power system |
| CN104919166A (en) * | 2013-01-18 | 2015-09-16 | 空中客车防务和空间公司 | Starter device for rocket motor turbopump |
| CN106321284A (en) * | 2016-08-19 | 2017-01-11 | 西北工业大学 | Integrated propellant supply system of rocket based combined circulating engine |
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| US5873241A (en) * | 1991-05-23 | 1999-02-23 | United Technologies Corporation | Rocket engine auxiliary power system |
| RU2084677C1 (en) * | 1994-12-20 | 1997-07-20 | Игорь Алексеевич Клепиков | Method of starting liquid rocket engine and liquid rocket engine |
| CN104919166A (en) * | 2013-01-18 | 2015-09-16 | 空中客车防务和空间公司 | Starter device for rocket motor turbopump |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973246A (en) * | 2019-03-22 | 2019-07-05 | 西安航天动力研究所 | A kind of gas-liquid composite drive precompressed turbine pump configuration and precompressed turbine pump driving method |
| CN110030114A (en) * | 2019-03-22 | 2019-07-19 | 西安航天动力研究所 | A kind of power oscillation damping high efficiency burnt gas mixing structure |
| CN109973246B (en) * | 2019-03-22 | 2020-06-30 | 西安航天动力研究所 | Gas-liquid composite driving prepressing turbine pump structure and prepressing turbine pump driving method |
| CN110748437A (en) * | 2019-09-20 | 2020-02-04 | 上海宇航系统工程研究所 | Propellant conveying system |
| CN112196702A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Liquid rocket engine starter and design method thereof |
| CN112628019A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof |
| CN112628018A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | High-thrust liquid rocket engine and low-power-consumption semi-self-starting method thereof |
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Application publication date: 20190222 |