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}
}
Other availability
Please see Document Availability for additional information on obtaining the full-text document. Library patrons may search WorldCat to identify libraries that hold this conference proceeding.
Save to My Library
You must Sign In or Create an Account in order to save documents to your library.