CN104777002A - Methane combustion heating experimental system for combustion chamber of scramjet engine - Google Patents
Methane combustion heating experimental system for combustion chamber of scramjet engine Download PDFInfo
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Abstract
The invention discloses a methane combustion heating experimental system for a combustion chamber of a scramjet engine. Natural gas containing 96 percent of methane is adopted to replace methane for heating experimental gas as fuel to simulate an incoming flow condition for a scramjet engine ground experiment within the flight Mach number ranging from 4 to 7. A main air loop is connected to an air-oxygen mixer through a pipeline, an air mixing loop is connected to a mixer through a pipeline, the mixer is used for mixing high-temperature air and normal-temperature air for a low-Mach number experiment, and a combustion heater is connected with an experimental model. An oxygen loop is connected to the air-oxygen mixer through a pipeline, and oxygen and air flow into the combustion heater in two paths after being mixed; a natural gas loop is connected with the combustion heater through a pipeline; a nitrogen blowing-off loop is connected behind a pneumatic valve of the natural gas loop through a pipeline, and is used for blowing off gas remaining in the pipeline after a combustion experiment; a control system is controlled by a preset time sequence, and high-temperature and high-pressure gas is generated by the ignition of an igniter; the gas enters the experimental model after being accelerated in a supersonic nozzle.
Description
Technical field
The present invention relates to scramjet engine ground experiment technical field, specifically, relate to the scramjet engine firing chamber experimental system of a kind of methyl hydride combustion heating.
Background technology
At present, scramjet engine ground experiment adopts burning heater comparatively general.In existing disclosed technical literature, Chinese aerodynamic investigation and centre of development adopt hydrogen and oxygen mix to heat, i.e. oxyhydrogen combustion well heater; Beijing machine power research institute adopts kerosene and oxygen mix to heat, i.e. kerosene heater; The National University of Defense technology adopts alcohol and oxygen mix to heat, i.e. alcohol burn well heater.Eight feet of thermal structure wind-tunnel of the U.S., the methyl hydride combustion well heater of foundation.Eight feet of the highest heating stagnation temperatures of thermal structure wind-tunnel are 2000K (document AIAA paper 96-2197), mainly apply to the experiment of aloof punching engine ground performance.Domestic still do not have methyl hydride combustion well heater to test for supersonic combustion.Adopt methyl hydride combustion well heater, and the rock gas close with methane composition replaces methane to do fuel, easy to use, significantly can reduce experimental expenses.The highest heating stagnation temperature of methyl hydride combustion heating simultaneously can reach 2700K, meets the ground experiment demand of flight Mach number 7 condition.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes the scramjet engine firing chamber experimental system of a kind of methyl hydride combustion heating, adopt the rock gas containing 96% methane to replace methane to do fuel to heat experimental gas, realize the scramjet engine ground experiment inlet flow conditions in simulated flight Mach number 4 ~ 7 scope.
The technical solution adopted for the present invention to solve the technical problems is: comprise air distribution system, oxygen gas distributing system, natural gas distribution system, nitrogen blow-off and control gas distributing system, cooling water system, control system, burning heater, mixer, empty oxygen mixer, supersonic nozzle, empirical model, the air main road pipeline of air distribution system is connected to sky oxygen mixer, and air Can Hun road pipeline is connected to mixer; Burning heater outlet is connected with mixer, and mixer outlet is connected with supersonic nozzle, and supersonic nozzle is connected with empirical model; The oxygen road pipeline of oxygen gas distributing system is connected to sky oxygen mixer, divides two-way to flow into burning heater after oxygen and air mixing; The natural gas circuit pipeline of natural gas distribution system is connected with burning heater; Nitrogen blow-off's road pipeline of nitrogen blow-off and control gas distributing system is connected to after natural gas circuit pneumatic valve, terminate after-blow except remaining rock gas in pipeline for combustion experiment, nitrogen Dominating paths join with air main road solenoid valve, air successively mix way solenoid valve, oxygen way solenoid valve, rock gas source solenoid valve, rock gas end solenoid valve, nitrogen blow-off's solenoid valve be connected; Cooling water system controlled cooling model water tank carries out chilled(cooling) water supply (CWS) to burning heater, supersonic nozzle, empirical model cooling duct; Control system is under default sequential control, and by the rock gas of flow after distribution, oxygen, air Injection burning heater, generation high-temperature high-pressure fuel gas lighted by lighter, and combustion gas enters empirical model after accelerating in supersonic nozzle.
Beneficial effect
The scramjet engine firing chamber experimental system of a kind of methyl hydride combustion heating that the present invention proposes, adopt the rock gas containing 96% methane to replace methane to do fuel to heat experimental gas, realize the scramjet engine ground experiment inlet flow conditions in simulated flight Mach number 4 ~ 7 scope.Air main road pipeline is connected to sky oxygen mixer, and air Can Hun road pipeline is connected to mixer, and mixer carries out the experiment of low mach after mixing for high temperature and normal temperature air ginseng, burning heater connects empirical model.Oxygen road pipeline is connected to sky oxygen mixer, divides two-way to flow into burning heater after oxygen and air mixing; Natural gas circuit pipeline is connected with burning heater; Nitrogen blow-off's road pipeline is connected to after natural gas circuit pneumatic valve, terminates the blowing of the residual gas in rear pipeline for combustion experiment, and control system is under default sequential control, and generation high-temperature high-pressure fuel gas lighted by lighter; Combustion gas enters empirical model after accelerating in supersonic nozzle.
Experimental system of the present invention, according to the sustainable supply of the experimental gas of predetermined pressure, temperature, traffic requirement, provides the experiment condition of the direct-connected ground experiment of aloof punching engine; The flow of temperature as requested, flow determination air, oxygen, rock gas, accurately controls each piping flow by the orifice flowmeter of each pipeline different pore size.Experimental system operating cost is low, operational efficiency is high.Experimental system meets simulated flight Mach number 4 ~ 7 completely, the ground experiment requirement of height 15 ~ 27km, stagnation temperature 1100 ~ 2200K; Heater outlet maximum flow is 2.5kg/s, and the highest stagnation pressure is 4.0MPa, and the key technical indexes is as shown in the table:
Accompanying drawing explanation
Be described in further detail below in conjunction with the scramjet engine firing chamber experimental system of drawings and embodiments to a kind of methyl hydride combustion heating of the present invention.
Fig. 1 is the scramjet engine firing chamber experimental system schematic diagram of methyl hydride combustion of the present invention heating.
Fig. 2 is air main road syndeton schematic diagram.
Fig. 3 is oxygen gas circuit connection structure schematic diagram.
Fig. 4 is natural gas circuit connection structure schematic diagram.
Fig. 5 is nitrogen gas circuit connection structure schematic diagram.
Fig. 6 is pressure before each passage orifice plate, empty oxygen mixer pressure and burning heater chamber pressure time curve figure.
In figure:
1. Nitrogen control road 2. 3. Nitrogen blow road road 4. Natural gas oxygen road 5. 6. Air main roads and mixed air road 7. Empty oxygen mixer 8. Water cooling tank 9. 10. The experiment model of supersonic nozzle 11. Mixer 12. 13. Burning heater air solenoid valve of the main road 14. Air mixed way solenoid valve 15 refs oxygen way solenoid valve 16. 17. Gas source electromagnetic valve gas solenoid valve at the end of 18. The nitrogen blow solenoid valve 19. The air supply, air filter 21. The source of pneumatic valve 22. The cut-off valve 23. The source pressure gauge 24. The source air bleeder 25. Air pressure reducer 26. The low pressure gauge 27. The low pressure air bleeder 28. The low pressure cut-off valve 29 air way pneumatic valve 30. 31. The pressure gauge orifice meter 32. Oxygen cylinders group 33. Oxygen pneumatic valves 34 35 oxygen road orifice flowmeter. 36. The check valve gas cylinders group 37. Pneumatic valve gas source 38. The gas road 39. The pneumatic valve at the end gas road orifice meter 40. Nitrogen cylinders road group 41. Nitrogen blow pneumatic valve
Embodiment
The present embodiment is the scramjet engine firing chamber experimental system of a kind of methyl hydride combustion heating.
Consult Fig. 1 ~ Fig. 5, the scramjet engine firing chamber experimental system of the present embodiment methyl hydride combustion heating, is made up of air distribution system, oxygen gas distributing system, natural gas distribution system, nitrogen blow-off and control gas distributing system, cooling water system, control system, burning heater, mixer, empty oxygen mixer, supersonic nozzle, empirical model and coupling.Air main road 5 pipeline of air distribution system is connected to sky oxygen mixer 7, and air Can Hun road 6 pipeline is connected to mixer 11; Burning heater 12 outlet is connected with mixer 11, and mixer 11 outlet is connected with supersonic nozzle 10, and supersonic nozzle 10 is connected with empirical model 9.Air Can Hun road 6 pipeline is connected to and exports with burning heater 12 mixer 11 be connected, and carries out the experiment of Mach number 4, Mach number 5 for high temperature air and normal temperature air ginseng after mixing; When High Mach number 6, Mach number 7, air Can Hun road does not work, and mixer 11 is removed, and burning heater 12 is connected with empirical model 9.Oxygen road 4 pipeline of oxygen gas distributing system is connected to sky oxygen mixer, divides two-way to flow into burning heater 12 after oxygen and air mixing; Natural gas circuit 3 pipeline of natural gas distribution system is connected with burning heater 12; Nitrogen blow-off road 2 pipeline of nitrogen blow-off and control gas distributing system is connected to after natural gas circuit pneumatic valve, after-blow is terminated except the remaining rock gas in pipeline for combustion experiment, nitrogen Dominating paths 1 joins mixed way solenoid valve 14 successively with air main road solenoid valve 13, air, oxygen way solenoid valve 15, rock gas source solenoid valve 16, rock gas end solenoid valve 17, nitrogen blow-off's solenoid valve 18 are connected, for the driving gas for each pneumatic valve after the distribution of nitrogen Dominating paths.Cooling water system controlled cooling model water tank 8 pairs of burning heaters 12, supersonic nozzle 10, empirical model 9 cooling duct carry out chilled(cooling) water supply (CWS).Control system is under default sequential control, and by the rock gas of flow after distribution, oxygen, air Injection burning heater 12, rear generation high-temperature high-pressure fuel gas lighted by lighter; Combustion gas is accelerated in supersonic nozzle 10, forms the air-flow meeting the parameter request of speed, temperature, pressure and oxygen content, then enter empirical model 9 before test section.Treat that experiment terminates, stop supply rock gas, oxygen, air by control system, in nitrogen blow-off's gas pipeline, remain rock gas.The chilled water cooled burning heater 12, supersonic nozzle 10 cooling duct works on after a period of time and closes, off-test.
The scramjet engine firing chamber experimental system of methyl hydride combustion heating achieves reliable ignition and smooth combustion, the firing chamber inlet flow conditions provided is as follows: burning heater rate of discharge is 1 ~ 2.5kg/s, stagnation pressure is 1.0 ~ 4.0MPa, stagnation temperature 900K ~ 2100K, simulated flight Mach number 4 ~ 7, flying height 15 ~ 27km.
Example: require burning heater combustion gas stagnation temperature 2580K, stagnation pressure 1.5MPa, flow 0.78kg/s, oxygen volume content 21%.
Step 1, calculates each piping flow as follows:
Air road: flow 0.515kg/s; Oxygen road: flow 0.209kg/s; Natural gas circuit: flow 0.06kg/s.Total flow: 0.784kg/s.
Step 2, each pipeline distribution pressure arranges as follows:
Air road distribution pressure: 3.55MPa, flow 0.515kg/s;
Oxygen road distribution pressure: 4.3MPa, flow 0.209kg/s;
Natural gas circuit distribution pressure: 6.7MPa, flow 0.06kg/s.
Step 3, before experiment starts, carries out chilled(cooling) water supply (CWS), to guarantee safe environment for use to burning heater 12 and supersonic nozzle 10 cooling duct.Air source of the gas 19 transmits gas and be divided into two-way to source air release 24, and a route air pressure reducer 25 is connected to after source air release 24, is connected to mixer 11 by pipeline and coupling; Another route air source of the gas 19 is connected to sky oxygen mixer 7 by pipeline, connecting line is connected with filtrator 20, source pneumatic valve 21, stop valve 22, source tensimeter 23, source air release 24, air pressure reducer 25, low pressure gauge 26, low pressure air release 27, low-pressure shutoff valve 28, air road pneumatic valve 29, tensimeter 30, orifice flowmeter 31.Oxygen gas cylinder group 32 and oxygen road pneumatic valve 33, oxygen road orifice flowmeter 34, retaining valve 35 are connected to sky oxygen mixer 7 by pipeline.Natural gas cylinder group 36 and rock gas source pneumatic valve 37, natural gas circuit end pneumatic valve 38, natural gas circuit orifice flowmeter 39 are connected to burning heater 12 by pipeline.Gas cylinder group 40 1 tunnel, nitrogen road connects nitrogen blow-off road 2 and tensimeter, retaining valve, is blown down by nitrogen blow-off's pneumatic valve 41 to rock gas; Another road of nitrogen road gas cylinder group 40 is connected with nitrogen Dominating paths 1 and coupling.By air pressure reducer, oxygen road decompressor, natural gas circuit decompressor, each line pressure is controlled, when distribution pressure is determined, orifice flowmeter 31 upstream pressure is determined, each piping flow is also determined, each piping flow is regulated by the orifice plate changing different pore size.The air of above-mentioned predetermined amount of flow, oxygen, rock gas, open air main road solenoid valve 13, air ginseng mixed way solenoid valve 14, oxygen way solenoid valve 15, rock gas source solenoid valve 16, rock gas end solenoid valve 17, nitrogen blow-off's solenoid valve 18 according to scheduled timing, each road gas inject burning heater 12, produces high-temperature high-pressure fuel gas after lighter is lighted.Combustion gas is accelerated in supersonic nozzle 10, the air-flow meeting speed, temperature, pressure and oxygen content parameter request is formed before test section 9, after fire trial terminates, air main road solenoid valve 13, air ginseng mixed way solenoid valve 14, oxygen way solenoid valve 15, rock gas end solenoid valve 17 is closed according to scheduled timing by control system, stop supply rock gas, oxygen, air, opening nitrogen blow-off's solenoid valve 18, blowing down remaining rock gas in gas pipeline end solenoid valve 17 pipeline; Chilled water works on after a period of time and closes, and single test terminates.
Step 4, natural gas fired combustion experiment, before each passage orifice plate collected, pressure, empty oxygen mixer pressure and burning heater chamber pressure change in time, and change curve as shown in Figure 6.
Claims (1)
1. the scramjet engine firing chamber experimental system of a methyl hydride combustion heating, it is characterized in that: comprise air distribution system, oxygen gas distributing system, natural gas distribution system, nitrogen blow-off and control gas distributing system, cooling water system, control system, burning heater, mixer, empty oxygen mixer, supersonic nozzle, empirical model, the air main road pipeline of air distribution system is connected to sky oxygen mixer, and air Can Hun road pipeline is connected to mixer; Burning heater outlet is connected with mixer, and mixer outlet is connected with supersonic nozzle, and supersonic nozzle is connected with empirical model; The oxygen road pipeline of oxygen gas distributing system is connected to sky oxygen mixer, divides two-way to flow into burning heater after oxygen and air mixing; The natural gas circuit pipeline of natural gas distribution system is connected with burning heater; Nitrogen blow-off's road pipeline of nitrogen blow-off and control gas distributing system is connected to after natural gas circuit pneumatic valve, terminate after-blow except remaining rock gas in pipeline for combustion experiment, nitrogen Dominating paths join with air main road solenoid valve, air successively mix way solenoid valve, oxygen way solenoid valve, rock gas source solenoid valve, rock gas end solenoid valve, nitrogen blow-off's solenoid valve be connected; Cooling water system controlled cooling model water tank carries out chilled(cooling) water supply (CWS) to burning heater, supersonic nozzle, empirical model cooling duct; Control system is under default sequential control, and by the rock gas of flow after distribution, oxygen, air Injection burning heater, generation high-temperature high-pressure fuel gas lighted by lighter, and combustion gas enters empirical model after accelerating in supersonic nozzle.
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| CN108800190A (en) * | 2018-06-25 | 2018-11-13 | 西北工业大学 | A kind of test(ing) medium mixing arrangement |
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| CN113984396A (en) * | 2021-09-18 | 2022-01-28 | 国网浙江省电力有限公司电力科学研究院 | Peak-shaving gas turbine unit combustion simulation test device |
| CN113970445B (en) * | 2021-10-14 | 2023-02-10 | 上海交通大学 | Entropy-sound test platform and test method thereof |
| CN113970445A (en) * | 2021-10-14 | 2022-01-25 | 上海交通大学 | Entropy-sound test platform and test method thereof |
| CN114252230A (en) * | 2022-03-02 | 2022-03-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Distribution device for cooling water of high-Mach-number spray pipe of conventional hypersonic wind tunnel |
| CN118150107A (en) * | 2024-05-09 | 2024-06-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel and wide-parameter operation method thereof |
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