超音速燃烧冲压发动机最佳设计参数

Optimum Design of Scramjet Engine

关键词:  超音速燃烧冲压式喷气发动机  最佳设计  航天飞机主发动机  计算

Key words:  Supersonic combustion ramjet engine  Optimum design  Computation  Space shuttle main engine

摘要:

本文对超音速燃烧冲压发动机设计参数进行优化。从产生推力与发动机热力循环两方面综合分析得到了以下结果:作为空天飞机动力装置的超音速燃烧冲压发动机,在M_H=6-6.6飞行范围内,按照等面积和等M数分段加热的热力循环设计时,比冲最大;在M_H=6.6-10飞行范围内,按照等面积和等温分段加热的热力循环设计时,比冲最大。从而得到最佳设计参数,并在此基础上,用一元流方法计算了有面积变化,有化学反应、摩擦和散热损失时,超音速燃烧冲压发动机的性能。

Abstract:

The purpose of this paper is to study the optimization of scramjet engine design. The propulsive force of the engine and the engine cycle analysis have been studied. The results of study show that the optimum value of the specific impulse will be attained in the case of heat addition according to constant area-constant Mach number process when the flight Mach number is within 6-6.6; while the o-ptimum specific impulse will be attained in the case of heat addition according to constant area-constant temperature process when the flight Mach number is within 6.6-10.The performance of scramjet engine is also obtained in this paper using a set of conservation equations with one dimensional flow, involving area change, heat release, skin friction and combustor wall heat transfer.