摘要
初步设计了满足爆震室进口流量、压力要求的离心式压气机和向心涡轮,并对整个脉冲爆震涡轮喷气发动机性能做出估计。算例结果显示,以航空煤油为燃料、空气为氧化剂,压气机设计出口流量为2.4 kg/s,转速为24270.5 r/min,在总当量比为0.25下,该发动机的单位推力约为853 N/kg/s,单位燃油消耗率为0.076 kg/(N.h)。本文还对带涡轮增压器的脉冲爆震发动机进行了初步原理性试验。试验表明:压气机产生的空气量可满足爆震室的需要,涡轮在经历上千次爆震后仍然完好。
A design method for centrifugal compressor and radial turbine for the hybrid pulse detonation engine （PDE） is presented, and the performance of this engine is evaluated. Using kerosene as fuel and compressed air as oxidizer, when air flow rate is 2.4 kg/s and the total equivalence ratio is 0.25, this engine can produce 853 N/kg/s specific thrust with 0.076 kg/（ N · h） specific fuel comumption （SFC）. The principle experiment of the pulse detonation engine with a turbocharger is also carried out. The experimental results show that the PDE can run continuously and stably. After more than one thousand detonations,there is no visible pitting or discoloration on the turbine blades.
出处
《机械科学与技术》
CSCD
北大核心
2008年第9期1151-1154,共4页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(50336030)资助
