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基于某轴对称排气系统,建立了一种小中段偏径比(S_m/D)、出口偏径比(S_o/D)大于0的双S形二元排气系统模型。该双S形二元排气系统在除了上方探测面0°到20°的角度范围内,所研究的其余方位角均做到了喷管型面对排气系统内部涡轮等高温部件的遮挡。通过数值计算研究了双S形二元排气系统的推力和红外特性,并与基准轴对称排气系统进行了对比。结果表明:小中段偏径比和大长径比使双S形二元排气系统避免了推力损失,相比基准轴对称排气系统,该双S形二元排气系统的推力增加了0.2%;双S形二元排气系统的红外辐射强度在侧向探测面上最小,在上方探测面最大;相比基准轴对称排气系统,双S形二元排气系统在0°方位角降低了97%以上,在侧向、上方和下方探测面90°方向分别降低了62.1%、26.1%和34.9%。
Based on an axisymmetric exhaust system, a double S-shaped binary exhaust system model with a small mid-size ratio (S_m / D) and an outlet diameter ratio (S_o / D) greater than 0 was established. The dual S-shaped binary exhaust system, except for the upper probing surface of 0 ° to 20 ° in the angle range, the rest of the studied azimuth angles were achieved nozzle-type exhaust system turbines and other high temperature components outside the block. The thrust and infrared characteristics of the dual S-shaped exhaust system were studied numerically and compared with the baseline symmetric exhaust system. The results show that the small mid-size ratio and the large aspect ratio can avoid the thrust loss of the dual-S binary exhaust system. Compared with the baseline symmetric exhaust system, the thrust of the dual-S binary exhaust system increases by 0.2 %; Double S-shaped binary exhaust system infrared radiation intensity in the lateral detection of the smallest, the largest detection above the surface; compared to the baseline axisymmetric exhaust system, dual S-shaped binary exhaust system at 0 ° azimuth Decreased by more than 97%, and decreased by 62.1%, 26.1% and 34.9% respectively in the 90 ° directions of the lateral, upper and lower detection planes.