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RESEARCH PAPERS: Advanced Energy Systems

A Test Device for Premixed Gas Turbine Combustion Oscillations

[+] Author and Article Information
G. A. Richards, R. S. Gemmen, M. J. Yip

U.S. Department of Energy, Federal Energy Technology Center, Morgantown, WV 26505

J. Eng. Gas Turbines Power 119(4), 776-782 (Oct 01, 1997) (7 pages) doi:10.1115/1.2817054 History: Received September 03, 1996; Revised February 14, 1997; Online November 19, 2007

Abstract

We report the design and operation of a test device suitable for studying combustion oscillations produced by commercial-scale gas turbine fuel nozzles. Unlike conventional test stands, this test combustor uses a Helmholtz acoustic geometry to replicate the acoustic response that would otherwise be observed only during complete engine testing. We suggest that successful simulation of engine oscillations requires that the flame geometry and resonant frequency of the test device should match the complete engine environment. Instrumentation for measuring both pressure and heat release variation is described. Preliminary tests suggest the importance of characterizing the oscillating behavior in terms of a nozzle reference velocity and inlet air temperature. Initial tests also demonstrate that the stabilizing effect of a pilot flame depends on the operating conditions.

Copyright © 1997 by The American Society of Mechanical Engineers
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