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Title: Gas turbine combustion instability

Abstract

Combustion oscillations are a common problem in development of LPM (lean premix) combustors. Unlike earlier, diffusion style combustors, LPM combustors are especially susceptible to oscillations because acoustic losses are smaller and operation near lean blowoff produces a greater combustion response to disturbances in reactant supply, mixing, etc. In ongoing tests at METC, five instability mechanisms have been identified in subscale and commercial scale nozzle tests. Changes to fuel nozzle geometry showed that it is possible to stabilize combustion by altering the timing of the feedback between acoustic waves and the variation in heat release.

Authors:
;
Publication Date:
Research Org.:
USDOE Morgantown Energy Technology Center (METC), WV (United States)
Sponsoring Org.:
USDOE, Washington, DC (United States)
OSTI Identifier:
372671
Report Number(s):
DOE/METC/C-96/7239; CONF-9605160-4
ON: DE96014528; NC: NONE
Resource Type:
Conference
Resource Relation:
Conference: 1996 Central States Section technical meeting of the Combustion Institute, St. Louis, MO (United States), 5-7 May 1996; Other Information: PBD: [1996]
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; GAS TURBINE ENGINES; COMBUSTORS; OSCILLATIONS; INSTABILITY; MIXING

Citation Formats

Richards, G A, and Lee, G T. Gas turbine combustion instability. United States: N. p., 1996. Web.
Richards, G A, & Lee, G T. Gas turbine combustion instability. United States.
Richards, G A, and Lee, G T. 1996. "Gas turbine combustion instability". United States. https://www.osti.gov/servlets/purl/372671.
@article{osti_372671,
title = {Gas turbine combustion instability},
author = {Richards, G A and Lee, G T},
abstractNote = {Combustion oscillations are a common problem in development of LPM (lean premix) combustors. Unlike earlier, diffusion style combustors, LPM combustors are especially susceptible to oscillations because acoustic losses are smaller and operation near lean blowoff produces a greater combustion response to disturbances in reactant supply, mixing, etc. In ongoing tests at METC, five instability mechanisms have been identified in subscale and commercial scale nozzle tests. Changes to fuel nozzle geometry showed that it is possible to stabilize combustion by altering the timing of the feedback between acoustic waves and the variation in heat release.},
doi = {},
url = {https://www.osti.gov/biblio/372671}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Sun Sep 01 00:00:00 EDT 1996},
month = {Sun Sep 01 00:00:00 EDT 1996}
}

Conference:
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