蒸发式稳定器低压高温试验  

Experimental investigation of vaporizing flameholder at low pressure and high temperature

作　　者：王健[1] 张力[2] 苏祥荣 

机构地区：[1]南京航空航天大学能源与动力学源,江苏南京210016 [2]航天科工集团公司31所,北京100074 [3]空军驻京丰地区军代表室,北京100074

出　　处：《推进技术》2006年第3期208-210,共3页Journal of Propulsion Technology

摘　　要：在截面180mm×15mm二元试验段上，对蒸发式稳定器高空低压67～68．6kPa及高温755～903K条件下的燃烧效率、总压恢复系数等燃烧性能和稳定器的壁面温度进行了试验研究。试验表明，蒸发式稳定器能够在来流低压68kPa高温873K条件下稳定工作，燃烧效率大于0．9，总压恢复系数在0．9～0．92，燃烧效率随燃油当量比增加而下降，随来流进气温度增加而增加。研究结果为冲压发动机蒸发式稳定器设计提供了参考。In order to obtain the combustion performance of the vaporizing flameholder at low pressure （67 -68.6kPa） under high-altitude condition and high temperature （755 -903K） , the combustion efficiency ,the total pressure recovery ratio and the wall temperature of the vaporizing flameholder in a two-dimensional test unit with the cross-section of 180mm×150mm were measured. The results show that the vaporizing flameholder can operate normally in the coming flow with low pressure of 68kPa and high temperature of 873K and it＇s combustion efficiency is above 0.9 and the total pressure recovery ratio ranges from 0.9 to 0.92. It also shows that the combustion efficiency decreases with the fuel equivalence ratio increasing and increases with the inlet air temperature increasing.

关 键 词：冲压喷气发动机 蒸发式稳定器 低压燃烧 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]