NUMERICAL AND EXPERIMENTAL STUDY OF COAXIAL INJECTOR JETS AT SUPERCRITICAL PRESSURES

摘要：

1. Introduction Injector design is very crucial in the development of liquid rocket combustors due to significant impact on the combustion efficiency and stability. The development of an optimum injector requires the information of flow characteristics near injectors, such as atomization, mixing and turbulent reactions. Unfortunately, it is too expensive and costly to conduct hot fire tests for all preliminary design concepts. Moreover, up to now there is no effective method/instrument to measure detailed flow properties near injectors under engine operating conditions. Therefore, it is desirable to apply for instructive and less expensive capability of CFD simulations during the development phase of new rocket engines.

作者: Hiroumi TANI

作者单位: Nagashima-Teramoto Lab.Department of Aeronautics and Astronautics, School of Engineering, University of Tokyo 7-3-1 Hongo, Bunkyo, Tokyo, JAPAN

会议类型: 国际会议

会议名称: 2008 National Academic Symposium for Ph. D. Candidates and Tri-University Workshop on Aero-Structural Mechanics & Aerospace Engineering(NASPCTUWMAE2008)(2008年国际航天航空工程会议暨2008年博士生学术会议(力学))

会议地点: 北京

会议语种:英文

页码: 1-4

在线出版日期: 2008-10-23（万方平台首次上网日期，不代表论文的发表时间）