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RESEARCH PAPERS

Design and Development of a High-Pressure Combustor for Aero-Gas-Turbines

[+] Author and Article Information
K. Suzuki

Combustion Section, National Aerospace Laboratory, Tokyo, Japan

A. Ishii, S. Horiuchi

National Aerospace Laboratory, Tokyo, Japan

T. Saito

Group III (Emission), Noise and Emission Research Group, National Aerospace Laboratory, Tokyo, Japan

M. Matsuki

Aeroengine Division, National Aerospace Laboratory, Tokyo, Japan

T. Torisaki

Noise and Emission Research Group, National Aerospace Laboratory, Tokyo, Japan

J. Eng. Power 100(1), 129-135 (Jan 01, 1978) (7 pages) doi:10.1115/1.3446303 History: Received December 30, 1976; Online July 14, 2010

Abstract

Research on a high-pressure combustor for turbofan engines has been carried out at National Aerospace Laboratory (Tokyo). In the first step, a design point of research combustor was fixed from a initial program of FJR Turbofan development. Then the combustor-type was developed, and the major dimensions were decided mainly from the experiences of JR-series lift jet engines, and partly from published data. As the next step, various-segment-type and full-annular-type combustors were tested at the pressure up to 15 bar.

Copyright © 1978 by ASME
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