影响液体火箭发动机涡轮效率的某些因素分析  

ANALYSIS OF THE EFFECT OF FACTORS ON THE EFFICIENCY OF LIQUID ROCKET TURBINE

作　　者：祖国君[1] 张远君[1] 

机构地区：[1]北京航空航天大学

出　　处：《推进技术》1992年第6期38-43,58,共7页Journal of Propulsion Technology

摘　　要：分析了液体火箭发动机中所用涡轮的各种损失因素,并建立了相应的数学模型,给出了计算方法。对于喷嘴中的二相流损失,采用龙格-库塔法求解一维定常全耦合的二相流控制方程。用迭代的方法进行冲击式涡轮及有小反力度的涡轮的设计计算,以使设计出的涡轮参数与效率相统一。通过对计算路径的控制,使得本方法和程序能同时用于冲击式涡轮及有小反力度的涡轮的设计计算;在计算结果中,还着重对二相流损失对涡轮效率的影响进行了分析。The loss factors in liquid rocket turbine are analysed in detail and a related mathematical model and calculation method is proposed. For the two-phase fluid losses in nozzle, Ronge-Kuta method is use to solve the static two-phase fluid control equations. Iteration scheme is applied to the design calculation of impulse turbine or turbine with less degree of reaction, in order that the designed turbine factors can coordinate with turbine effi-ciency. By means of the control of the calculation procedure, the present scheme can also be used at the same time in the design calculation of impulse turbine and the turbine with less deree of reaction. The effects oftwo-phase fluid loss on the turbine efficiency is analysed in accordance with calculated results.

关 键 词：液体推进剂 火箭发动机 透平 效率 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]