Technical Study On LRE Prepressurization Turbopump With Variable Pitch Inducer

The modern turbopump device customarily use various pump in series, and these pump is fitted together according to multi-stage project, For example, in centrifugal pump with inducer, jet exhauster and vane type axialflow pump (inducer) are operated as the booster pump. The abroad greatly thrust liquid rocket engines, between tank and main pump, always install front or inside booster pump device for boosting suction pressure of the main pump and reduceing the structure size and weight of the turbopump.The research of this paper is based on engineering practice. In X type liquid rocket engine under development, the maximal rotate speed of main liqud oxidizer pumps without a prepump is only 10300 rev/min at available maximal suction pressure, this speed is too low to accept, so a prepump must be installed before the main pump. According to the development experience of the former model and liquid rocket engine abroad, the impeller tip booster turbopump device is designed. The water tests and the hot-firing tests of the pump showed that the design project is viable.The general layout and axial force equilibrium system were chosen and optimized. The main performance and structure parameters of inducer was optimized and defined. The performance of single inducer with different hub shape was compared and estimated. By research above, the practical design methods of booster turbopump was obtained.