RESEARCH PAPERS: Gas Turbines: Aircraft

Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor

[+] Author and Article Information
Y. Kinoshita, J. Kitajima, Y. Seki

Akashi Technical Institute, Kawasaki Heavy Industries, Limited, Akashi, Japan

A. Tatara

Jet Engine Division, Kawasaki Heavy Industries, Limited, Akashi, Japan

J. Eng. Gas Turbines Power 117(3), 394-400 (Jul 01, 1995) (7 pages) doi:10.1115/1.2814108 History: Received March 04, 1994; Online November 19, 2007


The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach 5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NOx emissions are a critical problem for the ram combustor at Mach 5 condition.

Copyright © 1995 by The American Society of Mechanical Engineers
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