摘要
针对高性能分级燃烧(闭式)循环液体火箭发动机用反力式涡轮的特点,对所设计的动叶叶栅S1流面的准三元流气动分析和已有动叶平面叶栅的亚声速风洞试验,研究了反力式涡轮动叶正负攻角对叶栅内的绕流和能量损失的影响。结果表明:对于给定的来流方向,为得到连续收敛的叶栅几何通道和小的能量损失,动叶应采用正攻角设计。对已有的连续收敛的动叶叶栅,应采用负攻角流入工况,能量损失小。
According to the characteristics of the astronautical reaction turbine used in a high performance liquid rocket engine with staged closed circulation combustion, the designed rotor cascade and the blade to blade flow in the cascade were investigated. For the existed rotor cascade, the effects of positive or negative attacking angle for the reaction turbine on the energy loss and the blade to blade flow also were studied by means of two-dimensional cascade experiments in the subsonic tunnel. The results indicate that: in order to obtain the continuous contraction of the geometrical cascade and less energy loss the positive attacking angle showld be adopted for the rotor design. For the existed contracting rotor cascade, the negative attacking angle condition will result in the lessen the energy loss.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2002年第5期383-386,共4页
Journal of Propulsion Technology
