비행 조건에서의 입자 분사에 따른 엔진 배기플룸 냉각 및 차폐 영향성 연구

Abstract

Cooling and shielding effects of injecting micro-scale particles into the exhaust plume of an aircraft engine flying at high speed at an altitude of 6,096 m (=20,000 ft) were studied using computational methods. A discrete phase model was used to calculate a multiphase flow composed of exhaust plume and particles (liquid water mist and solid carbon). The IR radiation of the plume incident on the particle layer was first calculated, and then the radiation absorption coefficient of the injected particles was calculated using the discrete ordinate model. Furthermore, the change of the thermal flowfield of the exhaust plume according to the particle injection flow rate and the injection material, and the cooling and shielding effects were analyzed. The transmittance of the exhaust plume IR signal passing through the particle layer was determined through the maximum absorption coefficient at each point.