Investigation on Schemes for Accelerating Oxidizer Boost Pump During Start-Up of LOX/Kerosene Staged Combustion Rocket Engine

被引：0
|
作者：
Wang C.-M. [1 ,2 ]
Zhang X.-G. [2 ]
Gao Y.-S. [2 ]
Chen H. [2 ]
机构：
[1] School of Astronautics, Northwestern Polytechnical University, Xi'an
[2] Xi'an Aerospace Propulsion Institute, Xi'an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2020年 / 41卷 / 07期
关键词：
Boost pump; Cavitation; Liquid rocket engine; Main pump; Staged combustion engine; Start;
D O I：
10.13675/j.cnki.tjjs.190818
中图分类号：
学科分类号：
摘要：
In order to reduce inlet pressure for start of LOX/kerosene staged combustion rocket engine, the spin-up delay problem of oxidizer boost pump needs to be solved to eliminate its flow resistance influence on main pump cavitation. Two schemes for accelerating boost pump were studied, which are the liquid oxygen turbine scheme that has been applied in engineering and the helium starting turbine scheme proposed. Effects of the two schemes on engine gas-liquid system and boost pump structure were compared. Mathematical model was established to examine mechanism, effect and influencing factors of boost pump accelerating. Results show that for the liquid oxygen turbine scheme, the structure of boost turbopump has little change. To improve acceleration performance, the turbine supply pipeline should increase the diameter and shorten the length to reduce dynamic and static flow resistance. Meanwhile, the turbine nozzle flow area should be selected according to its comprehensive impact on the turbine flow and pressure drop. In the scheme of helium starting turbine, boost turbopump varies greatly in both structure and flow path, and reduction of helium consumption is limited by relatively low velocity ratio and efficiency of the starting turbine. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：1441 / 1448
页数：7
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