2012 Fiscal Year Final Research Report

Rotating Detonation in High-speed Combustible Flows Using A ShockTunnel

Research Project

Project/Area Number	23656536
Research Category	Grant-in-Aid for Challenging Exploratory Research
Allocation Type	Multi-year Fund
Research Field	Aerospace engineering
Research Institution	Yokohama National University
Principal Investigator	ISHII Kazuhiro 横浜国立大学, 大学院・工学研究院, 教授 (20251754)
Project Period (FY)	2011 – 2012
Keywords	デトネーション / 推進機関 / 衝撃波
Research Abstract	An experimental study has been made on initiation and propagation of rotating detonation waves. A test gas behind a reflected shock wave in a shock tunnel flows into an annular combustion chamber through an orifice plate to clarify conditions of steady propagation of rotating detonation waves. By varying the pressure ratio across the orifice plate, it is found that rotating detonation is achieved for the pressure ratio of 7.5, whereas the pressure ratio of 2.5 results in flash-back. The present study clarifies the pressure ratio needed for stable condition for initiation of rotating detonation waves.

(3 results)