CN110735718A - Fuel supply gear adjusting device of liquid ramjet engine - Google Patents
Fuel supply gear adjusting device of liquid ramjet engine Download PDFInfo
- Publication number
- CN110735718A CN110735718A CN201910770547.2A CN201910770547A CN110735718A CN 110735718 A CN110735718 A CN 110735718A CN 201910770547 A CN201910770547 A CN 201910770547A CN 110735718 A CN110735718 A CN 110735718A
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- CN
- China
- Prior art keywords
- oil supply
- supply pipeline
- fuel supply
- engine
- pipeline
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
Abstract
The invention discloses a fuel supply gear adjusting device of a liquid ramjet, which is formed by connecting an internal fuel supply pipeline, an external fuel supply pipeline, fuel supply on-off electromagnetic valves, a main fuel supply pipeline, an oil pump, an engine fuel supply pipeline and an experimental engine which are distributed in a fuel supply pipeline integrated module, wherein N internal fuel supply pipelines are distributed in the fuel supply pipeline integrated module, the side of the fuel supply pipeline integrated module is connected with the external fuel supply pipeline, the side of each internal fuel supply pipeline is respectively connected with external fuel supply pipelines, the internal fuel supply pipelines are intersected through the other side of the fuel supply pipeline integrated module and are connected with the engine fuel supply pipeline, the experimental engine is connected with the engine fuel supply pipeline, each external fuel supply pipeline is provided with the fuel supply on-off electromagnetic valves, the number of the fuel supply on-off electromagnetic valves is equal to that of the number of the external fuel supply pipelines is , and the external fuel supply pipelines are connected through the main fuel supply pipeline.
Description
Technical Field
The invention belongs to the field of liquid ramjet connecting pipe experiments, and particularly relates to a fuel supply gear adjusting device for liquid ramjets.
Background
The experimental research of the scramjet engine starts at the beginning of the present century, the inventor, etc. mentioned fuel supply modes in the direct connection type experimental research of the scramjet engine combustion mode conversion, the method can complete the experimental research of the engine combustion characteristic under the working condition of the flight Mach number 4.5 and can measure the working parameters of the engine, but the engine fuel supply device can not realize the function of accurately adjusting the fuel according to the gear position and can not accurately evaluate the influence of the sudden change of the engine fuel flow on the working performance of the engine in the experimental process.
Disclosure of Invention
The invention aims to provide fuel supply gear adjusting devices for a liquid ramjet, which solve the problem that the fuel flow of the prior scramjet cannot be accurately adjusted according to gears.
The fuel supply gear adjusting device of the liquid ramjet engine is formed by connecting an internal fuel supply pipeline, an external fuel supply pipeline, fuel supply on-off solenoid valves, a main fuel supply pipeline, an oil pump, an engine fuel supply pipeline and an experimental engine which are distributed in a fuel supply pipeline integrated module, wherein N internal fuel supply pipelines are distributed in the fuel supply pipeline integrated module, N is not less than 2, the side of the fuel supply pipeline integrated module is connected with the external fuel supply pipeline and ensures that the side of each internal fuel supply pipeline in the fuel supply pipeline integrated module is respectively connected with external fuel supply pipelines, the number of the internal fuel supply pipelines is equal to that of the external fuel supply pipelines, the internal fuel supply pipelines are converged and connected with the engine fuel supply pipeline through the other side of the fuel supply pipeline integrated module, the experimental engine is connected with the engine fuel supply pipeline to achieve the fuel supply effect, the fuel supply on-off solenoid valves are mounted on each external fuel supply pipeline, the number of the fuel.
According to the fuel supply gear adjusting device for the liquid ramjet, the oil supply pressure of an oil pump is not lower than 30Mpa, the shell of the oil supply pipeline integration module is made of 304 stainless steel, the number of oil supply on-off electromagnetic valves is equal to that of internal oil supply pipelines, and the response time is not shorter than 30 ms. The internal oil supply pipeline, the external oil supply pipeline, the main oil supply pipeline and the engine oil supply pipeline are high-pressure copper tubes or high-pressure hoses, and the engine oil supply pipeline is characterized in that the pressure bearing capacity of the oil supply pipelines is not lower than 30 Mpa. The connections between the above-mentioned pipes need to be reliable.
Compared with the prior art, the invention has the remarkable advantages that: (1) the fuel supply gear adjusting function of the engine in the experimental process can be realized by controlling the fuel supply on-off electromagnetic valve 4 to be opened or closed in sequence, and further, the fuel flow in the working process of the engine can be accurately adjusted. Due to the rapid response characteristic of the solenoid valve, the fuel flow can be rapidly adjusted.
(2) The fuel flow of the engine can be changed according to a preset rule by controlling the on-off quantity of the electromagnetic valves, and the fuel supply can be changed according to sine and cosine rules by changing the on-off quantity of the electromagnetic valves for many times.
(3) The on-off of the electromagnetic valve can be realized for many times in the experimental process, and the working characteristics of the engine under the working conditions of rich combustion and oxygen enrichment are examined.
Drawings
Fig. 1 is a schematic diagram of a fuel supply gear adjusting device for a liquid ramjet engine according to the present invention.
Fig. 2 is a schematic left side view of an oil supply pipeline integrated module structure of the fuel supply gear adjusting device for the liquid ramjet engine.
Detailed Description
The invention is further described with reference to the following figures.
Referring to fig. 1 to 2, the fuel supply gear adjusting device for the liquid ramjet engine is formed by connecting an internal fuel supply pipeline 1, an external fuel supply pipeline 3, a fuel supply on-off solenoid valve 4, a main fuel supply pipeline 5, an oil pump 6, an engine fuel supply pipeline 7 and an experimental engine 8 which are distributed in a fuel supply pipeline integrated module 2, wherein N internal fuel supply pipelines 1 are distributed in the fuel supply pipeline integrated module 2, N is larger than or equal to 2, the fuel supply pipeline integrated module 2 side is connected with the external fuel supply pipeline 3, side of each internal fuel supply pipeline 1 in the fuel supply pipeline integrated module 2 is guaranteed to be connected with external fuel supply pipelines 3 respectively, the internal fuel supply pipelines 1 are intersected and connected with the engine fuel supply pipeline 7 through the other side of the fuel supply pipeline integrated module 2, the experimental engine 8 is connected with the engine fuel supply pipeline 7 to achieve a fuel supply effect, the fuel supply on-off solenoid valves 4 are mounted on each external fuel supply pipeline 3, the number of the fuel supply pipelines 4 is , and the external fuel supply pipelines 3 are connected with the oil pump 6.
Wherein, the internal oil supply pipelines 1 are uniformly and symmetrically distributed in the oil supply pipeline integrated module 2; the internal oil supply pipeline 1, the external oil supply pipeline 3, the main oil supply pipeline 5 and the engine oil supply pipeline 7 are made of high-pressure copper tubes, and the pressure bearing capacity of the oil supply pipelines is not lower than 30 Mpa. The oil supply pressure of the oil pump 6 is not lower than 30Mpa, the shell of the oil supply pipeline integrated module 2 is made of 304 stainless steel, the number of the oil supply on-off electromagnetic valves 4 is equal to that of the internal oil supply pipelines 1, and the response time is not lower than 30 ms. The internal oil supply pipeline 1, the external oil supply pipeline 3, the main oil supply pipeline 5 and the engine oil supply pipeline 7 are connected in a welding mode, and reliable sealing is kept.
The working principle is as follows:
the internal oil supply pipeline 1, the oil supply pipeline integrated module 2, the external oil supply pipeline 3, the oil supply on-off solenoid valve 4, the oil pump 6, the main oil supply pipeline 5, the engine oil supply pipeline 7 and the experimental engine 8 are connected according to the mode shown in figure 1, the joints of the internal oil supply pipeline 1, the external oil supply pipeline 3, the main oil supply pipeline 5 and the engine oil supply pipeline 7 need to be ensured to be reliably sealed, welding is needed if necessary, and the pressure bearing of the oil supply pipeline is not lower than 30 Mpa. The number of the internal oil supply pipelines 1 is equal to that of the oil supply on-off electromagnetic valves 4, and the response time is not less than 30 ms. The oil supply pressure of the oil pump 6 is not lower than 30 Mpa.
Before the test is prepared, the oil supply on-off electromagnetic valve 4 needs to be kept closed, and the oil pump 6 is started to pressurize the oil. When the oil pump is added to the preset pressure, the experiment is started, the fuel supply flow of the engine is controlled by sequentially opening the fuel supply on-off electromagnetic valve 4, and when the fuel flow change demand occurs in the experiment, the electromagnetic valves can be opened or closed to achieve the purpose of adjusting the fuel flow.
Claims (5)
- The fuel supply gear adjusting device for the liquid ramjet engine is characterized by being formed by connecting an internal oil supply pipeline (1), an external oil supply pipeline (3), an oil supply on-off electromagnetic valve (4), a main oil supply pipeline (5), an oil pump (6), an engine oil supply pipeline (7) and an experimental engine (8) which are distributed in an oil supply pipeline integrated module (2);the oil supply system comprises an oil supply pipeline integration module (2), wherein N internal oil supply pipelines (1) are distributed in the oil supply pipeline integration module (2), N is larger than or equal to 2, the side of the oil supply pipeline integration module (2) is connected with external oil supply pipelines (3), the side of each internal oil supply pipeline (1) is respectively connected with external oil supply pipelines (3), the number of the internal oil supply pipelines is equal to that of the external oil supply pipelines, the internal oil supply pipelines (1) are intersected with the other side of the oil supply pipeline integration module (2) and connected with an engine oil supply pipeline (7), an experimental engine (8) is connected with the engine oil supply pipeline (7), oil supply on-off electromagnetic valves (4) are mounted on each external oil supply pipeline (3), the number of the oil supply on-off electromagnetic valves (4) is equal to that of the external oil supply pipelines (3), and.
- 2. The liquid ramjet fuel supply gear adjustment device of claim 1, wherein: the internal oil supply pipelines (1) are uniformly and symmetrically distributed in the oil supply pipeline integrated module (2).
- 3. The liquid ramjet fuel supply gear adjustment device of claim 1, wherein: the internal oil supply pipeline (1), the external oil supply pipeline (3), the main oil supply pipeline (5) and the engine oil supply pipeline (7) are high-pressure copper tubes or high-pressure hoses, and the pressure bearing of the oil supply pipelines is not lower than 30 Mpa.
- 4. The liquid ramjet fuel supply gear adjustment device of claim 1, wherein: the oil supply pressure of the oil pump (6) is not lower than 30Mpa, the shell of the oil supply pipeline integrated module (2) is made of 304 stainless steel, the number of the oil supply on-off electromagnetic valves (4) is equal to that of the internal oil supply pipelines (1), and the response time is not lower than 30 ms.
- 5. The liquid ramjet fuel supply gear adjustment device of claim 1, wherein: the connection among the internal oil supply pipeline (1), the external oil supply pipeline (3), the main oil supply pipeline (5) and the engine oil supply pipeline (7) keeps reliable sealing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910770547.2A CN110735718A (en) | 2019-08-20 | 2019-08-20 | Fuel supply gear adjusting device of liquid ramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910770547.2A CN110735718A (en) | 2019-08-20 | 2019-08-20 | Fuel supply gear adjusting device of liquid ramjet engine |
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| CN110735718A true CN110735718A (en) | 2020-01-31 |
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| CN201910770547.2A Pending CN110735718A (en) | 2019-08-20 | 2019-08-20 | Fuel supply gear adjusting device of liquid ramjet engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412201A (en) * | 2020-03-13 | 2020-07-14 | 南京理工大学 | Direct-connected laboratory bench flow control device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1114624A (en) * | 1993-12-23 | 1996-01-10 | 休斯航空公司 | Integrated storage and transfer system and method for spacecraft propulsion systems |
| CN101526217A (en) * | 2008-03-05 | 2009-09-09 | 株式会社日立制作所 | Gas turbine combustor and gaseous fuel supply method for gas turbine combustor |
| CN103411775A (en) * | 2013-07-22 | 2013-11-27 | 北京航空航天大学 | Fuel supplying system for liquid-propellant rocket engine test |
| US20150027102A1 (en) * | 2013-03-16 | 2015-01-29 | Patrick R.E. Bahn | Tri-propellant rocket engine for space launch applications |
| CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
| CN106151880A (en) * | 2016-08-29 | 2016-11-23 | 安徽伏斯特智能科技股份有限公司 | A kind of low discharge regulation system and control method thereof |
| CN107255050A (en) * | 2017-08-05 | 2017-10-17 | 中国科学院工程热物理研究所 | A kind of microminiature aero-engine fuel control system and method for starting-controlling |
-
2019
- 2019-08-20 CN CN201910770547.2A patent/CN110735718A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1114624A (en) * | 1993-12-23 | 1996-01-10 | 休斯航空公司 | Integrated storage and transfer system and method for spacecraft propulsion systems |
| CN101526217A (en) * | 2008-03-05 | 2009-09-09 | 株式会社日立制作所 | Gas turbine combustor and gaseous fuel supply method for gas turbine combustor |
| US20150027102A1 (en) * | 2013-03-16 | 2015-01-29 | Patrick R.E. Bahn | Tri-propellant rocket engine for space launch applications |
| CN103411775A (en) * | 2013-07-22 | 2013-11-27 | 北京航空航天大学 | Fuel supplying system for liquid-propellant rocket engine test |
| CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
| CN106151880A (en) * | 2016-08-29 | 2016-11-23 | 安徽伏斯特智能科技股份有限公司 | A kind of low discharge regulation system and control method thereof |
| CN107255050A (en) * | 2017-08-05 | 2017-10-17 | 中国科学院工程热物理研究所 | A kind of microminiature aero-engine fuel control system and method for starting-controlling |
Non-Patent Citations (1)
| Title |
|---|
| 李志敏: ""冲压增程火箭弹内外弹道一体化计算方法研究"", 《《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412201A (en) * | 2020-03-13 | 2020-07-14 | 南京理工大学 | Direct-connected laboratory bench flow control device |
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Application publication date: 20200131 |