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


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
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In