CN111720240B - Gas oxygen gas generator - Google Patents
Gas oxygen gas generator Download PDFInfo
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- CN111720240B CN111720240B CN201910594729.9A CN201910594729A CN111720240B CN 111720240 B CN111720240 B CN 111720240B CN 201910594729 A CN201910594729 A CN 201910594729A CN 111720240 B CN111720240 B CN 111720240B
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- oxygen
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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
- F02K9/62—Combustion or thrust chambers
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention relates to a liquid rocket engine, in particular to a gas oxygen gas generator; the technical problems that the propellant of the orbit control and attitude control power system of the existing lunar surface landing and ascending aircraft is not uniform, the propellant and a high-pressure storage tank thereof need to be additionally equipped, the volume and the mass of the propellant are increased, the effective load of a liquid rocket engine is reduced, and the launching cost is increased are solved. The technical solution of the invention is as follows: a gas oxygen gas generator, characterized in that: comprises a generator, a water removal device, a first switch valve, a high oxygen-enriched fuel gas storage tank, a switch valve, two groups of multi-stage one-way valve sets and a pressure reducing valve; the generator is provided with a gas oxygen kerosene torch igniter; the liquid oxygen inlet of the generator is connected with the outlet of the upgrading liquid oxygen storage box, and the kerosene inlet of the generator is connected with the outlet of the kerosene storage box; the outlet of the generator is connected with the inlet of the water removal device.
Description
Technical Field
The invention relates to a liquid rocket engine, in particular to a gas oxygen gas generator.
Background
The fuel gas generator is also called as a precombustion chamber, is mainly used as a combustion assembly of a pumping liquid rocket engine, is mainly used for generating high-temperature fuel gas to drive a turbine to do work and pressurize a propellant.
The attitude control power system of the existing lunar landing and ascending aircraft generally adopts different propellants from the main propellant, so that the propellants for the attitude control power system and a high-pressure storage tank thereof need to be additionally equipped, the volume and the mass of the liquid rocket engine are increased, the effective load of the liquid rocket engine is reduced, and the launching cost is increased.
Disclosure of Invention
The invention provides a gas oxygen gas generator, which aims to solve the technical problems that the propellant of an orbit control and attitude control power system of a lunar landing and ascending aircraft taking liquid oxygen kerosene as a main propellant is not uniform, the volume and the mass of the aircraft are increased due to the fact that the propellant and a high-pressure storage tank thereof are additionally arranged, the effective load of a liquid rocket engine is reduced, and the launching cost is increased.
The technical solution of the invention is as follows:
a gas oxygen gas generator, characterized in that:
comprises a generator, a water removal device, a first switch valve, a high oxygen-enriched fuel gas storage tank, a switch valve, two groups of multi-stage one-way valve sets and a pressure reducing valve;
the generator is provided with a gas oxygen kerosene torch igniter;
the liquid oxygen inlet of the generator is connected with the outlet of the upgrading liquid oxygen storage box, and the kerosene inlet of the generator is connected with the outlet of the kerosene storage box; the outlet of the generator is connected with the inlet of the water removal device; the outlet of the water removal device is connected with the inlet of the first switch valve; the outlet of the first switch valve is connected with the inlet of one group of the multi-stage check valve group; the outlet of the multi-stage check valve group is connected with the inlet of the high oxygen-enriched fuel gas storage tank, and the first outlet of the high oxygen-enriched fuel gas storage tank is connected with the gas oxygen storage tank of the descending-stage engine; a second outlet of the high oxygen-enriched fuel gas storage tank is connected with an inlet of the second switch valve; the outlet of the second switch valve is connected with the inlet of the other group of multi-stage check valve groups, and the outlet of the group of multi-stage check valve groups is connected with the inlet of the pressure reducing valve; the outlet of the pressure reducing valve is connected with a gas oxygen inlet G0 of a gas oxygen kerosene torch igniter and a gas oxygen inlet G1 of an attitude control engine; and a kerosene inlet R0 of the gas oxygen kerosene torch igniter and a gas oxygen inlet G1 of the attitude control engine are connected with a kerosene storage box.
Furthermore, the multistage check valve group comprises two groups of check valve groups connected in parallel, and each group of check valve group comprises two check valves connected in series.
Further, the water removal device is a centrifugal water remover.
Further, the first switch valve is an electric air valve.
Further, the second switch valve is an electric explosion valve.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention continuously or discontinuously works according to the working requirement, the kerosene and the liquid oxygen are combusted to generate the high oxygen-enriched fuel gas, the generated high oxygen-enriched fuel gas is dewatered and then stored in the oxygen-enriched fuel gas storage tank, high-pressure gas oxygen is provided for the attitude control power system, a propellant and a high-pressure storage tank thereof do not need to be additionally arranged, the effective load of the liquid rocket engine is increased, and the launching cost is reduced.
2. The invention utilizes the gas oxygen in the oxygen-enriched gas storage tank to supply gas oxygen for the gas generator and the gas oxygen kerosene torch igniter of the engine, the pressure of the oxygen-enriched gas storage tank is always kept at 4-6 MPa, and the reliable ignition of each gas oxygen kerosene torch igniter for many times can be ensured.
3. The liquid oxygen and the kerosene of the invention are respectively from the upgrade liquid oxygen storage tank and the kerosene storage tank, and the invention realizes the integration of the propellant of the rail and attitude control power system.
Drawings
FIG. 1 is a schematic block diagram of one embodiment of the present invention;
the reference signs are:
1-generator, 101-kerosene inlet, 102-liquid oxygen inlet, 103-gas oxygen kerosene torch igniter, 2-water removal device, 3-first switch valve, 4-high oxygen-enriched fuel gas storage tank, 401-first outlet, 402-second outlet, 5-second switch valve, 6-multi-stage check valve group, 601-check valve, 7-pressure reducing valve, 8-ball valve and 9-attitude control engine.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments.
Referring to fig. 1, the gas oxygen gas generator comprises a generator 1, a water removal device 2, a first switch valve 3, a high oxygen-enriched gas storage tank 4, a second switch valve 5, two groups of multi-stage one-way valve sets 6 and a pressure reducing valve 7. The generator 1 is provided with a gas oxygen kerosene torch igniter 103.
The liquid oxygen inlet 102 of the generator 1 is connected with an upgrading liquid oxygen storage box, the kerosene inlet 101 of the generator 1 is connected with the kerosene storage box, and the outlet of the generator 1 is connected with the inlet of the water removal device 2; the outlet of the water removing device 2 is connected with the inlet of the first switch valve 3; the outlet of the first switch valve 3 is connected with the inlet of one group of multi-stage check valve group 6; the outlet of the multi-stage one-way valve group 6 is connected with the inlet of the high oxygen-enriched fuel gas storage tank 4, the first outlet 401 of the high oxygen-enriched fuel gas storage tank 4 is connected with the gas oxygen storage tank of the low-stage engine, and the second outlet 402 of the high oxygen-enriched fuel gas storage tank 4 is connected with the inlet of the second switch valve 5; the outlet of the second switch valve 5 is connected with the inlet of another group of multi-stage check valve group 6, the outlet of the group of multi-stage check valve group 6 is connected with the inlet of the pressure reducing valve 7, the outlet of the pressure reducing valve 7 is connected with the gas oxygen inlet G0 of the gas oxygen kerosene torch igniter 103 and the gas oxygen inlet G1 of the attitude control engine 9, and the kerosene inlet R0 of the gas oxygen kerosene torch igniter 103 and the kerosene inlet R1 of the attitude control engine 9 are connected with the kerosene storage tank.
The dewatering device 2 in this embodiment is a centrifugal type dewatering device, the first switch valve 3 is an electric air valve, the second switch valve 5 is an electric explosion valve, the multi-stage check valve group 6 comprises two groups of check valve groups connected in parallel, and each group of check valve group comprises two check valves 601 connected in series. The kerosene inlet 101, the liquid oxygen inlet 102 and the first outlet 401 of the high oxygen-enriched gas storage tank 4 of the generator 1 are provided with ball valves 8 for opening and closing pipelines.
The working principle of the embodiment is as follows:
kerosene and liquid oxygen enter the generator 1 through a liquid oxygen inlet 102 and a kerosene inlet 101 of the generator 1 respectively for combustion to generate high oxygen-enriched fuel gas (the high oxygen-enriched fuel gas comprises O)2、CO2And H2O is high-temperature, high-oxygen-enriched and high-pressure gas with the pressure of 4-6 MPa), and the high-oxygen-enriched gas enters the high-oxygen-enriched gas storage tank 4 after being dewatered by the dewatering device 2 and sequentially passing through the first switch valve 3 and one of the multistage check valve sets 6. The high oxygen-enriched gas from the high oxygen-enriched gas storage tank 4 is divided into two paths, one path of the high oxygen-enriched gas enters the gas oxygen storage tank of the descending engine to be stored, the other path of the high oxygen-enriched gas sequentially passes through the second switch valve 5 and the other group of multi-stage one-way valve sets 6 and then is decompressed through the decompression valve 7, and the compressed gas is decompressed to 1-2 MPa and then supplies gas oxygen to the attitude control engine 9 and the gas oxygen gas oil torch igniter 103. The embodiment can supply oxygen for the self-contained gas oxygen kerosene torch igniter 103 to realize ignition, and other gas oxygen ports such as R1 of the embodiment can also supply oxygen for other gas oxygen kerosene torch igniters.
The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the present invention.
Claims (5)
1. A gas-oxygen gasifier, characterized by:
comprises a generator (1), a water removal device (2), a first switch valve (3), a high oxygen-enriched fuel gas storage tank (4), a second switch valve (5), two groups of multi-stage one-way valve sets (6) and a pressure reducing valve (7);
the generator (1) is provided with a gas oxygen kerosene torch igniter (103);
a liquid oxygen inlet (102) of the generator (1) is connected with an outlet of the upgrading liquid oxygen storage tank, and a kerosene inlet (101) of the generator (1) is connected with an outlet of the kerosene storage tank; the outlet of the generator (1) is connected with the inlet of the water removal device (2); the outlet of the water removal device (2) is connected with the inlet of the first switch valve (3); the outlet of the first switch valve (3) is connected with the inlet of one group of the multi-stage check valve group (6); the outlet of the multi-stage check valve group (6) is connected with the inlet of the high oxygen-enriched fuel gas storage tank (4), and the first outlet (401) of the high oxygen-enriched fuel gas storage tank (4) is connected with the gas oxygen storage tank of the descending-stage engine; a second outlet (402) of the high oxygen-enriched fuel gas storage tank (4) is connected with an inlet of the second switch valve (5); the outlet of the second switch valve (5) is connected with the inlet of the other group of multi-stage check valve set (6), and the outlet of the group of multi-stage check valve set (6) is connected with the inlet of the reducing valve (7); the outlet of the pressure reducing valve (7) is connected with a gas oxygen inlet G0 of a gas oxygen kerosene torch igniter (103) and a gas oxygen inlet G1 of an attitude control engine (9); the kerosene inlet R0 of the gas oxygen kerosene torch igniter (103) and the kerosene inlet R1 of the attitude control engine (9) are both connected with a kerosene storage box.
2. A gas-oxygen gasifier as claimed in claim 1, wherein: the multistage check valve group (6) comprises two groups of check valve groups connected in parallel, and each group of check valve groups comprises two check valves (601) connected in series.
3. A gas-oxygen gasifier as claimed in claim 2, wherein: the dewatering device (2) is a centrifugal type dewatering device.
4. A gas-oxygen gasifier as claimed in any one of claims 1 to 3, wherein: the first switch valve (3) is an electric air valve.
5. A gas-oxygen gasifier as claimed in claim 4, wherein: the second switch valve (5) is an electric explosion valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910594729.9A CN111720240B (en) | 2019-07-03 | 2019-07-03 | Gas oxygen gas generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910594729.9A CN111720240B (en) | 2019-07-03 | 2019-07-03 | Gas oxygen gas generator |
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| Publication Number | Publication Date |
|---|---|
| CN111720240A CN111720240A (en) | 2020-09-29 |
| CN111720240B true CN111720240B (en) | 2021-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910594729.9A Active CN111720240B (en) | 2019-07-03 | 2019-07-03 | Gas oxygen gas generator |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2116491C1 (en) * | 1996-03-26 | 1998-07-27 | Исследовательский центр им.М.В.Келдыша | Method of operation of liquid-propellant rocket engine and liquid-propellant rocket engine used for realization of this method |
| CN106134417B (en) * | 2006-10-19 | 2012-04-04 | 上海空间推进研究所 | Low-thrust rocket |
| CN103711610A (en) * | 2013-12-18 | 2014-04-09 | 中国航天科技集团公司第六研究院第十一研究所 | RBCC fuel gas generator integrated supplying and adjusting system based on liquid oxygen |
| CN108953003A (en) * | 2018-06-28 | 2018-12-07 | 西安航天动力研究所 | A kind of promoted using oxygen rich fuel gas realizes afterburning cycle engine system and thrust depth adjustment method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3042821B1 (en) * | 2015-10-26 | 2017-12-01 | Snecma | METHOD OF CONTROLLING PRESSURE WITHIN A FIRST ERGOL TANK OF FIRED ENGINE |
-
2019
- 2019-07-03 CN CN201910594729.9A patent/CN111720240B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2116491C1 (en) * | 1996-03-26 | 1998-07-27 | Исследовательский центр им.М.В.Келдыша | Method of operation of liquid-propellant rocket engine and liquid-propellant rocket engine used for realization of this method |
| CN106134417B (en) * | 2006-10-19 | 2012-04-04 | 上海空间推进研究所 | Low-thrust rocket |
| CN103711610A (en) * | 2013-12-18 | 2014-04-09 | 中国航天科技集团公司第六研究院第十一研究所 | RBCC fuel gas generator integrated supplying and adjusting system based on liquid oxygen |
| CN108953003A (en) * | 2018-06-28 | 2018-12-07 | 西安航天动力研究所 | A kind of promoted using oxygen rich fuel gas realizes afterburning cycle engine system and thrust depth adjustment method |
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| Publication number | Publication date |
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| CN111720240A (en) | 2020-09-29 |
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