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为提高超燃冲压发动机工作稳定性,提出了基于气动斜坡的超声速燃烧冲压发动机双燃烧室方案,该方案属于高超声速飞行器动力装置新方案。超燃主燃烧室采用基于气动斜坡的燃料喷注方式,并以小型燃气发生器作为亚燃燃烧室布置于气动斜坡喷嘴下游。超声速来流空气经进气道分流,96%左右进入超燃主燃烧室,4%左右经燃料电池驱动的离心式压气机增压后进入亚燃燃烧室。亚燃燃烧室在富油工况下工作,其出口布置在超燃主燃烧室气动斜坡喷注模块的下游(距气动斜坡第1排喷孔10倍喷孔直径处),此模块在主燃烧室中高效、低损失地形成流向涡。亚燃燃烧室喷流位于流向涡之后,起到点火、增强掺混和稳定火焰的作用。在直连式试验台上进行了该方案燃烧室部分的燃烧试验,结果表明:该方案成功实现了碳氢燃料大当量比范围内的稳定燃烧,以燃料比冲为评判标准,初步证明了该方案的可行性。
In order to improve the working stability of the scramjet, a twin-combustor scheme of the supersonic combustion ramjet engine based on the pneumatic ramp is proposed, which belongs to the new scheme of the hypersonic vehicle power plant. The main combustion chamber of the super-combustion engine adopts the fuel injection method based on the pneumatic ramp, and the small gas generator is arranged as the sub-combustion chamber downstream of the pneumatic ramp nozzle. Ultrasonic flow to the air through the inlet diversion, about 96% into the main combustion chamber, about 4% by the fuel cell-powered centrifugal compressor into the sub-combustion chamber after turbocharging. The sub-combustion chamber is operated under rich conditions and its outlet is arranged downstream of the pneumatic ramp injection module of the main combustion chamber (10 times the diameter of the injection hole in the first row of the pneumatic ramp) Room efficient and low loss to the formation of flow vortex. The sub-combustor jet is located in the flow vortex, the ignition, and enhance the role of mixing and stabilizing the flame. The combustion experiment of the combustion chamber of this scheme was carried out on a direct-coupled test bench. The results showed that the scheme successfully achieved stable combustion in the range of large equivalence ratio of hydrocarbon fuel. The fuel specific impulse was used as the evaluation criterion. Feasibility of the program.