液体火箭发动机推进剂泵诱导轮与离心轮的匹配

doi:10.7527/S1000-6893.2018.22609

流体力学与飞行力学

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液体火箭发动机推进剂泵诱导轮与离心轮的匹配

杨宝锋¹, 李斌^1,2, 陈晖¹, 刘占一¹

1. 西安航天动力研究所液体火箭发动机技术重点实验室, 西安 710100;
2. 航天推进技术研究院, 西安 710100

收稿日期:2018-08-15 修回日期:2018-10-08 出版日期:2019-05-15 发布日期:2018-10-29
通讯作者: 杨宝锋 E-mail:ybf1000@qq.com
基金资助:
国家"973"计划（613321）

Matching effect between inducer and impeller in a liquid rocket engine propellant pump

YANG Baofeng¹, LI Bin^1,2, CHEN Hui¹, LIU Zhanyi¹

1. Science and Technology on Liquid Rocket Engine Laboratory, Xi'an Aerospace Propulsion Institute, Xi'an 710100, China;
2. Academy of Aerospace Propulsion Technology, Xi'an 710100, China

Received:2018-08-15 Revised:2018-10-08 Online:2019-05-15 Published:2018-10-29
Supported by:
National Basic Research Program of China (613321)

摘要/Abstract

摘要： 为获得诱导轮离心轮周向匹配的时序效应对离心泵外特性以及压力脉动的影响规律，阐释相关作用机制，采用基于分离涡仿真（DES）的离心泵三维全流道数值仿真方法，引入熵产理论以及压力脉动强度系数等先进分析方法对不同匹配角度下离心泵内能量损失机制及压力脉动特性进行了研究。结果表明：离心轮诱导轮的时序效应对泵外特性有一定的影响，随着匹配角度的增加，扬程和效率均呈现先减小后缓慢增大的趋势，扬程变化为0.8%，效率变化为1.2%，其影响机制由不同匹配角度下叶轮通道分离涡、叶轮叶片尾迹以及靠近隔舌处扩压器通道回流涡变化决定；时序效应对离心轮扩压器动静干涉效应影响显著，当诱导轮叶片尾缘位于离心轮相邻主叶片中间位置时，能够有效消除3倍频成分，显著降低泵内压力脉动水平，其中动静干涉区域以及隔舌处扩压器叶片表面压力脉动平均降幅分别达到14.5%和16.7%。

关键词: 涡轮泵, 诱导轮, 离心轮, 液体火箭发动机, 时序效应, 熵产, 压力脉动

Abstract: The relative circumferential position between the inducer and the impeller (clocking effect) has a considerable impact on the performance and pressure pulsations of the pump, which is, however, often ignored by designers. To evaluate the influence of this effect,a 3D numerical simulation is performed based on the Detached Eddy Simulation (DES) method. The entropy production method and pressure pulsation intensity coefficient are employed to evaluate the energy loss and pressure pulsation characteristics of the pump and clarify the formation mechanism of this clock effect. The numerical results show that the clocking effect has certain influence on the external characteristics of the pump. The head and efficiency first decrease and then slowly increase with the increase of the matching angle, and the maximum variation of the head and efficiency are 0.8% and 1.2%, respectively. The formation of this is owing to the different extents of the separation vortices in the impeller passage and the impeller blade wake in the diffuser inlet as well as the backflow vortices in the diffuser blade passage near volute tongue. The clocking effect has great impact on the rotor-stator interaction effect between the impeller and the diffuser. When the inducer blade trailing edge is located in the middle of two adjacent impeller blades, 3 times of the rotating frequency component of pressure pulsation can be eliminated, and the pressure pulsation level in the pump is dramatically reduced with the Root Mean Square (RMS) value of the pressure pulsation in the rotor-stator interaction region and the diffuser blade surface near the volute tongue decreasing by 14.5% and 16.7%, respectively.

Key words: turbopump, inducer, impeller, liquid rocket engine, clocking effect, entropy production, pressure pulsation

中图分类号:

V434.21

杨宝锋, 李斌, 陈晖, 刘占一. 液体火箭发动机推进剂泵诱导轮与离心轮的匹配[J]. 航空学报, 2019, 40(5): 122609-122609.

YANG Baofeng, LI Bin, CHEN Hui, LIU Zhanyi. Matching effect between inducer and impeller in a liquid rocket engine propellant pump[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(5): 122609-122609.

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E-mail：hkxb@buaa.edu.cn

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液体火箭发动机推进剂泵诱导轮与离心轮的匹配

Matching effect between inducer and impeller in a liquid rocket engine propellant pump

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