基于气动斜坡的超燃冲压发动机双燃烧室方案研究

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。

Study on Dual-Combustor Scramjet Based on Aero-ramp Injector

In order to improve the stability of scramjet, a scheme of dual-combustor scramjet based on aero-ramp injectors was presented, which belongs to hypersonic vehicle propulsion. The fuel was injected via aero-ramp injector in the main scramjet combustor. The gas-portfire acting as a ramjet combustor was located downstream the aero-ramp. The supersonic freestream was divided by inlets. About 96% of the freestream entered the main scramjet combustor. After pressurized by centrifugal compressor, about 4% of the freestream entered the ramjet combustor. The ramjet combustor worked under the fuel-rich condition, and its exit was located downstream the aero-ramp, about 10 times the diameter of aero-ramp injector from the first row of aero-ramp injectors. The aero-ramp produced intensive streamwise vortexs in the scramjet combustor effectively and with low loss. The jet flow of the ramjet combustor, which had the functions of fuel ignition, mixing enhancement and flame stabilization, was located downstream the streamwise vortexs. The combustion experiments of the novel scheme were performed in supersonic direct-connect facility . The results show that stable combustion over a wider range of fuel equivalence ratios are achieved. The feasibility of the novel dual-combustor ramjet concept is verified by high fuel impulse.