摘要
建立了固体推进剂吸气式涡轮火箭发动机的设计状态数值模型,提出了基于压气机增压比、涡轮前温度和涡轮落压比关系的燃烧室燃气与空气配比表达式,以及涡轮落压比和发动机涵道比的匹配关系。定量分析了压气机增压比、涡轮进口燃气总温、涵道比/涡轮落压比和飞行马赫数对固体推进剂吸气式涡轮火箭发动机的单位推力和比冲的影响。
A numerical model for calculating performance of solid propellant air-turbo-rocket at design point was set up,and a relationship expression of fuel-air ratio of combustion based on compressor pressure ratio, tubine intet total temperature and turbine expansion ratio was put forward. And a relationship between the turbine expansion ratio and the bypass ratio was given. The effects of compressor pressure ratio, turbine inlet temperature, bypass ratio/turbine expansion ratio and flight Mach number on the specific thrust and specific impulse were analyzed quantitatively.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第1期53-57,共5页
Journal of Solid Rocket Technology
作者简介
TU Qiu-ye （ 1971 --）, male, PhD, speciality： propulsion and engineering of aerodynamics and astrodynamics. E-mail： tuqiuye @ nwpu. edu. cn
