CN105822483A - Self-ignition test method for scramjet engine - Google Patents
Self-ignition test method for scramjet engine Download PDFInfo
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- CN105822483A CN105822483A CN201610325579.8A CN201610325579A CN105822483A CN 105822483 A CN105822483 A CN 105822483A CN 201610325579 A CN201610325579 A CN 201610325579A CN 105822483 A CN105822483 A CN 105822483A
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- pipeline
- outlet
- ignition
- quick valve
- oil cylinder
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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
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P17/00—Testing of ignition installations, e.g. in combination with adjusting; Testing of ignition timing in compression-ignition engines
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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 provides a self-ignition test method for a scramjet engine and belongs to the technical field of engine ignition. The method comprises the steps that (1) a first oil cylinder and a second oil cylinder are filled with aviation kerosene and starting fuel correspondingly; (2) an outlet of the first oil cylinder is connected with an inlet of a first fast valve through a pipeline; (3) an outlet of the first fast valve is connected with a first nozzle through a pipeline; (4) an outlet of the second oil cylinder is connected with an inlet of a second fast valve through a pipeline; (5) an outlet of the second fast valve is connected with a second nozzle through a pipeline; (6) the second fast valve is opened to supply the starting fuel to the second nozzle first, and the starting fuel starts self-ignition after entering a combustion chamber; (7) when the starting fuel is supplied for 50 ms, the first fast valve is opened to supply the aviation kerosene; (8) when the aviation kerosene is supplied for 50 ms, the second fast valve is closed, and supply of the starting fuel is stopped; and (9) the first fast valve is in an open state until the end of a test. The self-ignition test method is mainly used for engine self-ignition tests.
Description
Technical field
The invention belongs to engine ignition technical field.
Background technology
Scramjet engine is the airbreathing motor that can use in the hypersonic field of Ma >=4.Its feature is can not to start speed is zero when, could normally work after needing to be accelerated to certain speed by rocket engine or other power set.This electromotor (Ma >=5) when High Mach number can reach, by profile in reasonably design, the purpose that self-ignition starts.But, when starting near low mach (Ma=4 and 4.5), owing in combustor, speed of incoming flow is high, stagnation temperature is low, combustor flow at high speed state causes fuel to evaporate distance along journey, and fuel residence time is the shortest.Meanwhile, the dense spraying being full of in combustor makes minimum ignition energy sharply increase, and it is extremely difficult that these igniting all making scramjet engine and stable burning become.
In order to realize super burn electromotor ignition operation under low mach, the most conventional low mach test method includes: thermojet auxiliary firing, pneumatic congestion auxiliary firing, hydrogen pilot ignition, plasma igniting, pyrotechnic igniter etc..These methods can inject big energy to combustor, improves combustor back pressure, reduces speed of incoming flow, is beneficial to igniting.But under test conditions, on the one hand these methods add a set of auxiliary ignition system, reduce the reliability of electromotor, on the other hand make it possible to back pressure excessive and cause air intake duct not start.Additionally at secure context, required voltage the highest (1100V) during spark plug work, if there is security incident in bad being easy to of insulating；Pyrotechnic igniter belongs to inflammable explosive article, it is desirable to have the professional of qualification operates.
It can be seen that the common feature of current existing low mach test method is:
1, these test methods are all to use in long-time wind-tunnel (test period is second level), are difficult to apply in pulse-combustion wind-tunnel (test period 0.2s)；
2, need to configure extra auxiliary ignition system, reduce reliability, add cost；
3, security risk is big.
Summary of the invention
It is an object of the invention to provide a kind of super burn electromotor self-ignition test method, it can efficiently solve super burn engine ignition problem.
It is an object of the invention to be achieved through the following technical solutions: a kind of super burn electromotor self-ignition test method, its step is as follows:
1, fuel supply conduit is connected
(1) first oil cylinder and the second oil cylinder are respectively provided with aerial kerosene and starting fluid；
The outlet of (2) first oil cylinders is connected by the import of pipeline and the first quick valve；
The outlet of (3) first quick valves is connected with first jet by pipeline, and connecting line is provided with the first pressure transducer；
The outlet of (4) second oil cylinders is connected by the import of pipeline and the second quick valve；
The outlet of (5) second quick valves is connected with second nozzle by pipeline, and connecting line is provided with the second pressure transducer；
2, test sequential is determined
(1), during test, being first turned on the second quick valve is that second nozzle supplies starting fluid, enters combustor rear engine at starting fluid and starts self-ignition work；
(2) opening the first quick valve when starting fluid supply 50ms is that first jet supplies aerial kerosene, and now the first quick valve and the second quick valve are open mode；
(3) closing the second quick valve after aerial kerosene supply 50ms, stop supply starting fluid, starting fluid supplies 100ms altogether；
(4) first quick valves are in open mode, until off-test.
The beneficial effect that technical solution of the present invention is brought:
Utilize the auxiliary ignition system that technical scheme uses when can cast away existing low mach engine test, by using quick valve and corresponding sequencing contro that fuel control method can be applied to pulse-combustion wind tunnel test, and " relay " burning in test of two kinds of fuel can be realized.
Accompanying drawing explanation
Fig. 1 is the fuel conduit connection figure of the present invention
Fig. 2 is starting fluid and the aerial kerosene pressure-time diagram of the present invention
Detailed description of the invention
Embodiment
Below against accompanying drawing, the invention will be further described:
A kind of super burn electromotor self-ignition test method, its step is as follows:
1, fuel supply conduit is connected
(1) first oil cylinder 1 and the second oil cylinder 5 are respectively provided with aerial kerosene and starting fluid；
The outlet of (2) first oil cylinders 1 is connected by the import of pipeline and the first quick valve 2；
The outlet of (3) first quick valves 2 is connected with first jet 4 by pipeline, and connecting line is provided with the first pressure transducer 3；
The outlet of (4) second oil cylinders 5 is connected by the import of pipeline and the second quick valve 6；
The outlet of (5) second quick valves 6 is connected with second nozzle 8 by pipeline, and connecting line is provided with the second pressure transducer 7；
2, test sequential is determined
(1) during test, it is first turned on the second quick valve 6 and supplies starting fluid for second nozzle 8, enter combustor 9 rear engine at starting fluid and start self-ignition work；
(2) opening the first quick valve 2 when starting fluid supply 50ms and supply aerial kerosene for first jet 4, now the first quick valve 2 and the second quick valve 6 are open mode；
(3) aerial kerosene 11 closes the second quick valve 6 after supplying 50ms, stops supply starting fluid, and starting fluid supplies 100ms altogether；
(4) first quick valves 2 are in open mode, until off-test.
As shown in Fig. 2 coordinate, curve 10 is starting fluid service time, and curve 11 is aerial kerosene service time.
Claims (1)
1. a super burn electromotor self-ignition test method, its step is as follows:
One, fuel supply conduit is connected
(1), the first oil cylinder (1) and the second oil cylinder (5) are respectively provided with aerial kerosene and starting fluid；
(2), the outlet of the first oil cylinder (1) is connected by the import of pipeline and the first quick valve (2)；
(3), the outlet of the first quick valve (2) be connected with first jet (4) by pipeline, connecting line is provided with the first pressure transducer (3)；
(4), the outlet of the second oil cylinder (5) is connected by the import of pipeline and the second quick valve (6)；
(5), the outlet of the second quick valve (6) be connected with second nozzle (8) by pipeline, connecting line is provided with the second pressure transducer (7)；
Two, test sequential is determined
(1), during test, being first turned on the second quick valve (6) is that second nozzle (8) supplies starting fluid, enters combustor (9) rear engine at starting fluid and starts self-ignition work；
(2) opening the first quick valve (2) when starting fluid supply 50ms is that first jet (4) supplies aerial kerosene, and now the first quick valve (2) and the second quick valve (4) are open mode；
(3) closing the second quick valve (4) after aerial kerosene supply 50ms, stop supply starting fluid, starting fluid supplies 100ms altogether；
(4) first quick valves (2) are in open mode, until off-test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610325579.8A CN105822483A (en) | 2016-05-17 | 2016-05-17 | Self-ignition test method for scramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610325579.8A CN105822483A (en) | 2016-05-17 | 2016-05-17 | Self-ignition test method for scramjet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105822483A true CN105822483A (en) | 2016-08-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610325579.8A Pending CN105822483A (en) | 2016-05-17 | 2016-05-17 | Self-ignition test method for scramjet engine |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101082312A (en) * | 2007-07-03 | 2007-12-05 | 浙江大学 | Double group component sydraulic free-piston engine |
| CN101539480A (en) * | 2009-04-30 | 2009-09-23 | 哈尔滨工业大学 | One-dimensional evaluation method of combustion efficiency for scramjet engine |
| CN102863994A (en) * | 2012-10-12 | 2013-01-09 | 葛明龙 | Four-component fuel hypergolic with 70%-98% of hydrogen peroxide |
| CN103484173A (en) * | 2013-09-16 | 2014-01-01 | 上海交通大学 | Self-ignition fuel |
-
2016
- 2016-05-17 CN CN201610325579.8A patent/CN105822483A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101082312A (en) * | 2007-07-03 | 2007-12-05 | 浙江大学 | Double group component sydraulic free-piston engine |
| CN101539480A (en) * | 2009-04-30 | 2009-09-23 | 哈尔滨工业大学 | One-dimensional evaluation method of combustion efficiency for scramjet engine |
| CN102863994A (en) * | 2012-10-12 | 2013-01-09 | 葛明龙 | Four-component fuel hypergolic with 70%-98% of hydrogen peroxide |
| CN103484173A (en) * | 2013-09-16 | 2014-01-01 | 上海交通大学 | Self-ignition fuel |
Non-Patent Citations (3)
| Title |
|---|
| 丁猛，余勇，梁剑寒，刘卫东，王振国: "碳氢燃料超燃冲压发动机点火技术试验", 《推进技术》 * |
| 张弯洲，乐嘉陵，杨顺华，程文明，邓维鑫，周化波: "马赫数为4的超燃发动机碳氢燃料点火试验", 《航空动力学报》 * |
| 李大鹏，丁猛，梁剑寒，刘卫东，王振国: "Ma=4液体碳氢燃料超燃冲压发动机点火试验", 《推进技术》 * |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160803 |
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| RJ01 | Rejection of invention patent application after publication |