A Radiative Heating System for Active Cooling Experiments
A radiation heating and active cooling technology, applied in the field of radiation heating system, can solve the problem that the real thermal environment of scramjet cannot be simulated
Active Publication Date: 2016-03-09
合肥中科重明科技有限公司
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In this way, the heat flow around the circular tube is evenly distributed, which is completely different from the situation where the cooling panel of the actual scramjet is loaded with heat flow on one side, so it cannot simulate the real thermal environment of the scramjet engine
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[0025] Hereinafter, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other arbitrarily if there is no conflict.
[0026] The radiant heating system used in the active cooling experiment of the embodiment of the present invention includes: a radiant heating device, a power supply module, a fuel preheating transport device and a hot fuel collection device, wherein the radiant heating device adopts infrared radiation The cooling panel is heated, which includes: a radiant heating element, an electrode assembly, a heat preservation and heat insulation assembly and a box, wherein the radiant heating element is a graphite plate structure located at the lower part of the cooling panel, and the radiant heating element The length and width are both greater than the length and width of the cooling panel, the...
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The invention discloses a radiation heating system used for an active cooling test. The radiation heating system used for the active cooling test comprises a radiation heating device, a power supply module, a fuel preheat transportation device and a hot fuel collection device. The radiation heating device is used for heating a cooling panel in an infrared radiation mode, and comprises a radiation heating element, an electrode assembly, a heat preservation and insulation assembly and a tank body. The power supply module supplies power for the radiation heating device. The fuel preheat transportation device is connected with a hydrocarbon fuel inlet pipeline and transports hydrocarbon fuel for the cooling panel. The hot fuel collection device is connected with a hydrocarbon fuel outlet pipeline, and is used for cooling high-temperature hydrocarbon fuel flowing out of the cooling panel. An even radiation heating area can be provided for the lower surface of the cooling panel of which the maximum size is 1000mm*40mm, wherein the length of the even radiation heating area is larger than 1000mm, the width is larger than 40mm, the heat flux density is larger than 1Mw / m<2>, and continuous operation can be carried out for a long time under the condition of radiation heat flux.
Description
Technical field [0001] The invention relates to the experimental field of scramjet engines, in particular to a radiation heating system used for active cooling experiments. Background technique [0002] During supersonic flight, the temperature of the outer surface of the aircraft will exceed the allowable temperature of many commonly used lightweight materials at high Mach numbers. In addition to the oxygen and strong air flow in the combustion chamber, the conventional structural materials are not cooled. It is difficult to work long hours. [0003] In view of the thermal environment faced by hypersonic flight, active cooling technology is proposed to solve the thermal protection problem of scramjet, that is, the airborne fuel flows through the cooling channel opened in the combustion chamber wall to cool the combustion chamber wall, and then Inject it into the combustion chamber to burn. Super combustion engines use liquid hydrocarbons as fuel, such as kerosene. Kerosene flow...
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IPC IPC(8): G01M15/14
Inventor 袁越明李龙程迪陆阳卢锡年范学军
Owner 合肥中科重明科技有限公司