CAJ | 학술논문

为了研究超燃冲压发动机燃烧室内气流变化规律，通过影响系数法，建立了超燃冲压发动机的准一维模型，该模型考虑了燃料质量添加、壁面传热、截面变化、壁面摩擦等影响因素，同时给出了燃烧室3种模态转换的边界条件。以单模块超燃冲压发动机为研究对象，仿真分析了超燃无激波模态和超燃斜激波模态下燃油当量比、攻角等参数对燃烧室气流参数的影响，结果表明，气流马赫数随当量比的增大、攻角的增大而减小。所建立的模型可为超燃冲压发动机总体设计及性能分析提供一种快速分析的手段。
위료연구초연충압발동궤연소실내기류변화규률，통과영향계수법，건립료초연충압발동궤적준일유모형，해모형고필료연료질량첨가、벽면전열、절면변화、벽면마찰등영향인소，동시급출료연소실3충모태전환적변계조건。이단모괴초연충압발동궤위연구대상，방진분석료초연무격파모태화초연사격파모태하연유당량비、공각등삼수대연소실기류삼수적영향，결과표명，기류마혁수수당량비적증대、공각적증대이감소。소건립적모형가위초연충압발동궤총체설계급성능분석제공일충쾌속분석적수단。
To study the change regularity of airflow in the combustor of scramjet engine,the influence coefficient method was used to mode the quasi one-dimensional model of scramjet combustor,which contained some influence factors such as fuel quality flow,wall heat transfer, cross-sectional variation and wall friction.The conversion boundary conditions of the three modes of the combustor were also presented in this work.A single-module scramjet engine was taken as study object.The effects of fuel equivalent ratio and attack angle on airflow parameters were simulated under scramjet modes without shock-wave and with oblique shock-wave.The presented model provides a method of the overall design of scramjet engine and performance analysis.