CN115614184A - Small-sized steam generator - Google Patents
Small-sized steam generator Download PDFInfo
- Publication number
- CN115614184A CN115614184A CN202211330916.4A CN202211330916A CN115614184A CN 115614184 A CN115614184 A CN 115614184A CN 202211330916 A CN202211330916 A CN 202211330916A CN 115614184 A CN115614184 A CN 115614184A
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- China
- Prior art keywords
- steam generator
- small
- oxygen
- hydrogen
- sealing ring
- Prior art date
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- 239000001301 oxygen Substances 0.000 claims abstract description 18
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 18
- 238000012360 testing method Methods 0.000 claims abstract description 18
- 239000001257 hydrogen Substances 0.000 claims abstract description 17
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 17
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000002347 injection Methods 0.000 claims abstract description 14
- 239000007924 injection Substances 0.000 claims abstract description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910001868 water Inorganic materials 0.000 claims abstract description 11
- 238000004088 simulation Methods 0.000 claims abstract description 7
- 125000004435 hydrogen atom Chemical class [H]* 0.000 claims abstract 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 9
- 239000000498 cooling water Substances 0.000 claims description 6
- 239000010963 304 stainless steel Substances 0.000 claims description 3
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 3
- 150000002431 hydrogen Chemical group 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 239000000110 cooling liquid Substances 0.000 claims 1
- 229910002804 graphite Inorganic materials 0.000 claims 1
- 239000010439 graphite Substances 0.000 claims 1
- 229920002379 silicone rubber Polymers 0.000 claims 1
- 239000007789 gas Substances 0.000 abstract description 4
- 238000010793 Steam injection (oil industry) Methods 0.000 abstract 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 229910001882 dioxygen Inorganic materials 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a small-sized steam generator, which relates to the field of rocket engine test research, and is a steam generator with gas hydrogen, gas oxygen and water as media and with the flow rate of 650 g/s. The steam generator can adjust the flow and the temperature as required, and a gas hydrogen oxygen torch igniter is adopted for ignition. The invention can generate high-quality high-temperature high-pressure steam and provide an injection medium for a high-altitude simulation test of a small rocket engine. Generally, the steam injection medium provided by the invention provides powerful guarantee for high-altitude simulation test research of a small rocket engine.
Description
Technical Field
The invention relates to the field of rocket engine test research, in particular to a small-sized steam generator.
Background
When a novel upper-level rocket engine is developed, the determination of the high altitude characteristic of the rocket engine is one of important tasks of ground test run of the engine, the thrust of the rocket engine is continuously increased along with the rise of the altitude, the maximum thrust is achieved in a vacuum environment, the environmental pressure of the upper-level rocket engine during working is very low, the high altitude characteristic of the rocket engine can be simulated only by establishing a low-pressure vacuum environment with corresponding altitude during ground test run, and therefore ground vacuum test equipment needs to be established.
Because the construction cost of the full-size high-altitude simulation test bed of the rocket engine is huge, in order to reduce the research cost and accelerate the research progress, the scaling high-altitude simulation test of the engine is an economic and efficient research means in the early stage of the development of the novel upper-level rocket engine. What is needed is a small steam generator that can meet the requirements of testing to meet the requirements of the injection system for the injection medium.
In addition, in the novel engine in the development stage, different working condition parameters are inevitably subjected to experimental research during testing, the requirement on the vacuum degree provided by a high-mode system is changed, and then different parameters such as the flow, pressure and temperature of the steam generator are required, and the parameters of the steam generator are required to have larger adjustable margins.
Disclosure of Invention
The invention aims to provide a small-sized steam generator which is used for high-altitude simulation test research of a small-sized rocket engine. The invention aims to solve the problems that (1) stable high-quality high-temperature steam is provided to provide a medium for starting an injection system; (2) The parameters of the steam such as flow, pressure, temperature and the like are adjustable, and the test use requirements of multiple working conditions are met.
The technical scheme of the invention is as follows: the primary steam generator generates steam by using oxygen, hydrogen and water as media. The steam pressure of the steam generator is 2MPa, the steam temperature 573K, and the flow and the temperature can be adjusted according to the requirement. The total flow rate of the steam generator was 650g/s, oxygen was 110g/s, hydrogen was 15g/s, the water flow was 525g/s, and the hydrogen-oxygen mixing ratio was 7.3. Igniting by using a hydrogen-oxygen torch igniter. The head of the steam generator adopts three coaxial nozzles, the flame guide tube of the igniter is positioned in the center, the middle is provided with an oxygen nozzle, and the outermost is provided with a hydrogen nozzle. After ignition is completed, the igniter is turned off from the oxygen gas, and the pilot flame tube is used as a hydrogen nozzle. The body part adopts a water-cooling jacket and a spray cooling mixing mode. The cooling water is opened for 7 circles of injection holes. The first circle is an injection panel and is injected along the axial direction, the aperture is 0.5mm,16, and the distribution flow accounts for 11.3 percent; the second circle to the seventh circle are all radial injection, the aperture is 0.7mm, the number is respectively 8, 12 and 16, the distribution flow rates were 11.1%, 16.6%, and 22.2%, respectively. The total length of the first-stage generator is 833mm, the maximum outer diameter is 138mm, and the main material is 304 stainless steel.
The invention has the advantages and positive effects that: (1) The steam generation medium is composed of hydrogen, oxygen and water, and is easy to obtain, a matching system is simple, and the generated steam has high quality; (2) The high-quality injection steam can be provided for a rocket engine high-altitude simulation test, and test conditions are provided for the development of the upper stage rocket engine; (3) The steam generator has adjustable flow, pressure, temperature and other parameters, can meet the requirement of a multi-working-condition test, and improves the test efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, it is obvious that the drawings in the following description are the basic design of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view showing a structure of a small-sized steam generator according to the present invention.
Fig. 2 is a partial structural view illustrating a small-sized steam generator according to the present invention.
1. An igniter flame guide tube; 2. a gas oxygen head; 3. a seal ring; 4. a hydrogen head; 5. a seal ring; 6. a seal ring; 7. cooling the terminal pressure measuring point; 8. a cooling water outer cylinder; 9. cooling the water inner cylinder; 10. a water inlet; 11. a seal ring; 12. a seal ring; 13. a mixing chamber; 14. and (6) installing a flange.
Detailed Description
The invention is further described below with reference to the figures and examples.
The primary steam generator generates steam by using oxygen, hydrogen and water as media. The steam pressure of the steam generator is 2MPa, the steam temperature is 573K, and the flow and the temperature can be adjusted according to the requirement. The total flow rate of the steam generator was 650g/s, oxygen was 110g/s, hydrogen was 15g/s, the water flow was 525g/s, and the hydrogen-oxygen mixing ratio was 7.3. Igniting by using a hydrogen-oxygen torch igniter. The head of the steam generator adopts three coaxial nozzles, the flame guide tube of the igniter is positioned in the center, the middle is provided with an oxygen nozzle, and the outermost is provided with a hydrogen nozzle. After ignition is completed, the igniter is turned off from the oxygen gas, and the pilot flame tube is used as a hydrogen nozzle. The body part adopts a water-cooling jacket and a spray cooling mixing mode. The cooling water is provided with 7 circles of injection holes. The first circle is an injection panel and is injected along the axial direction, the aperture is 0.5mm,16, and the distribution flow accounts for 11.3 percent; the second to seventh rings are all radial injection, the aperture is 0.7mm, the number is 8, 12, 16 respectively, the distribution flow rates are respectively 11.1%, 16.6% and 22.2%. The total length of the first-stage generator is 833mm, the maximum outer diameter is 138mm, and the main material is 304 stainless steel.
Claims (3)
1. A small-sized steam generator is used for high-altitude simulation test research of a small-sized rocket engine and is characterized by consisting of an igniter flame guide pipe (1), an oxygen head (2), a sealing ring (3), a hydrogen head (4), a sealing ring (5), a sealing ring (6), a cooling tail end pressure measuring point (7), a cooling water outer cylinder (8), a cooling water inner cylinder (9), a water inlet (10), a sealing ring (11), a sealing ring (12), a mixing chamber (13) and a mounting flange (14); the medium for generating steam is hydrogen, oxygen and water, and the material is 304 stainless steel; the medium water is used as a medium for generating steam and a cooling liquid of the equipment, and a water-cooling jacket and a spray cooling mixing mode are adopted; the cooling water inner cylinder (9) is provided with 7 rings of injection holes; the first circle is an injection panel and is injected along the axial direction, the aperture is 0.5mm,16 holes are formed, and the distribution flow accounts for 11.3 percent; the second circle to the seventh circle are all radial injection, the aperture is 0.7mm, the number is respectively 8, 12 and 16, the distribution flow rates are respectively 11.1%, 16.6% and 22.2%.
2. The small-sized steam generator according to claim 1, wherein the steam generator head is a tri-coaxial nozzle, the inner side is a hydrogen nozzle, the middle is an oxygen nozzle, and the outermost is a hydrogen nozzle, the igniter head is ignited at the center, after the ignition is finished, the igniter is turned off by oxygen, and the igniter flame guide tube is used as a hydrogen nozzle.
3. The small steam generator as claimed in claim 2, wherein the sealing ring (6) is made of silicon rubber, and the other sealing rings (3), (5), (11) and (12) are made of expanded graphite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211330916.4A CN115614184A (en) | 2022-10-27 | 2022-10-27 | Small-sized steam generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211330916.4A CN115614184A (en) | 2022-10-27 | 2022-10-27 | Small-sized steam generator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115614184A true CN115614184A (en) | 2023-01-17 |
Family
ID=84876847
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211330916.4A Pending CN115614184A (en) | 2022-10-27 | 2022-10-27 | Small-sized steam generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115614184A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117552894A (en) * | 2023-02-21 | 2024-02-13 | 北京航天试验技术研究所 | Rocket engine high-altitude simulation test method and equipment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2059160C1 (en) * | 1992-04-20 | 1996-04-27 | Конструкторское бюро химического машиностроения | Method for organizing working process in reactive burner combustion chamber |
| CN101782028A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Hydrogen-oxygen fuel-rich precombustion chamber for full flow staged combustion cycle engine |
| CN104329655A (en) * | 2014-11-13 | 2015-02-04 | 北京航天试验技术研究所 | Fuel gas generator used for providing injection working medium |
| RU156407U1 (en) * | 2015-03-18 | 2015-11-10 | Федеральное государственное бюджетное учреждение науки Объединенный институт высоких температур РАН (ОИВТ РАН) | HYDROGEN MINIPAROGENERATOR |
| WO2019130619A1 (en) * | 2017-12-28 | 2019-07-04 | 泉寛治 | Engine burning hydrogen and oxygen |
| CN111237087A (en) * | 2020-01-19 | 2020-06-05 | 西北工业大学 | Novel active and passive micropore plate composite cooling structure for aerospace power and cooling method |
| WO2022172914A1 (en) * | 2021-02-15 | 2022-08-18 | 寛治 泉 | Engine for combusting hydrogen-oxygen |
-
2022
- 2022-10-27 CN CN202211330916.4A patent/CN115614184A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2059160C1 (en) * | 1992-04-20 | 1996-04-27 | Конструкторское бюро химического машиностроения | Method for organizing working process in reactive burner combustion chamber |
| CN101782028A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Hydrogen-oxygen fuel-rich precombustion chamber for full flow staged combustion cycle engine |
| CN104329655A (en) * | 2014-11-13 | 2015-02-04 | 北京航天试验技术研究所 | Fuel gas generator used for providing injection working medium |
| RU156407U1 (en) * | 2015-03-18 | 2015-11-10 | Федеральное государственное бюджетное учреждение науки Объединенный институт высоких температур РАН (ОИВТ РАН) | HYDROGEN MINIPAROGENERATOR |
| WO2019130619A1 (en) * | 2017-12-28 | 2019-07-04 | 泉寛治 | Engine burning hydrogen and oxygen |
| CN111237087A (en) * | 2020-01-19 | 2020-06-05 | 西北工业大学 | Novel active and passive micropore plate composite cooling structure for aerospace power and cooling method |
| WO2022172914A1 (en) * | 2021-02-15 | 2022-08-18 | 寛治 泉 | Engine for combusting hydrogen-oxygen |
Non-Patent Citations (2)
| Title |
|---|
| 俞南嘉, 张国舟, 宋雅娜, 马彬, 童晓艳: "同轴氢氧谐振点火器试验研究", 推进技术, no. 03, 25 June 2004 (2004-06-25), pages 267 - 270 * |
| 赵宏;张海栋;孙小丽;郑鑫;: "大流量火箭蒸汽发生器试验研究", 推进技术, no. 08, 15 August 2013 (2013-08-15), pages 1077 - 1081 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117552894A (en) * | 2023-02-21 | 2024-02-13 | 北京航天试验技术研究所 | Rocket engine high-altitude simulation test method and equipment |
| CN117552894B (en) * | 2023-02-21 | 2024-05-17 | 北京航天试验技术研究所 | Rocket engine high-altitude simulation test method and equipment |
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