摘要
核心机及其派生发动机发展的方法研究表明,可以通过增大空气流量和增大核心机的循环功来实现发动机推力增大,但需要在发动机设计中事先考虑工作转速、流通能力和叶轮机功率等储备。在核心机基础上进行发动机系列化发展,原则上可以采用保持高压压气机设计换算转速不变,或者保持最高燃气温度不变的技术措施,实际应用中上述两种方法都采用。因此,在核心机及基本发动机研制中,既要有燃气温度和转速的储备,又要有高压压气机性能的储备。但是,在核心机基础上研制大涵道比涡扇发动机和小涵道比加力涡扇发动机的技术途径是不同的。
The investigation of core engine and derivative aero-engine development was presented. The increase in engine thrust can be realized by increasing air flow or cycle power of the core engine. But the margin of rotor speed, flow capacity and power needed of the turbomachinery should be considered early in the design stage. Serial development based on the core engine can be done by keeping the corrected speed of the high-pressure compressor constant, or keeping the maximum gas temperature constant. In practice, both of the foregoing approaches were adopted. Therefore,the margin of the maximum gas temperature,rotor speed and capability of HP compressor are required during the development of core engine and baseline aero-engine. However,the approaches in developing high bypass ratio engine and low bypass ratio engine are different.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期241-247,共7页
Journal of Aerospace Power
关键词
航空
航天推进系统
核心机
发动机
派生发展
aerospace propulsion system
core engine
aero-engine
derivative engine
