Effect of leading edge sweep on the performance of cavitating inducer of LOX booster turbopump used in semicryogenic engine

26th International Cryogenic Engineering Conference & International Cryogenic Materials Conference 2016

材料科学;物理学

Mishra, Arpit^1 ; Ghosh, Parthasarathi^1

Cryogenic Engineering Centre, Indian Institute of Technology, Kharagpur

721302, India^1

关键词: Cavitating inducers;    CFD analysis;    Inlet backflow;    Liquid rocket engines;    Operating ranges;    Performance characterization;    Staged combustion;    Steady state;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/171/1/012062/pdf
DOI  :  10.1088/1757-899X/171/1/012062

学科分类：材料科学（综合）

来源: IOP

【 摘 要 】

As a part of the developmental effort towards the realization of a staged combustion cycle based liquid rocket engine, a program on simulation of the LOX booster pump for performance characterization has been taken up. Earlier reported work shows that the pump inducer works satisfactorily under cavitating conditions for the throttling range varying from 90% to 113%. However stall occurs below 90% of the designed flow rate which is to be strongly associated with the inlet backflow vortices due to flow separation [1]. It is envisaged that leading edge sweep may help in to controls the incipience and growth of the backflow vortices at the inlet leading edge tip of axial flow inducer leading to a wider operating range. In this paper, steady state 3D CFD analysis of rotating inducer is performed to examine the effect of leading edge sweep on the performance of axial flow LOX pump inducer using ANSYS®CFX and has been compared with the performance of the inducer reported by Mishra and Ghosh [1].