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Title: Gas turbine combustor design methodology

Abstract

The detailed representation of flow and combustion processes offered by multidimensional models and the predictive tool of the proven empirical correlations are combined to form a basis for a gas turbine combustor design method. Provisions are made to fully utilize the output of the analytical computations by evaluating the values of relevant parameters within subdivisions of liner sector. By this means, the impact of a systematic modification to the detail of dome swirlers and liner configuration is easily determined. A heat transfer calculation method that utilizes the variation in combustor parameters in the three dimensions and evaluates radiation flux components through a view factor is considered. In comparison with experimental data obtained for a typical production liner, the predictions of the developed method in regard to emission formation, combustion performance, and wall temperature are quite satisfactory.

Authors:
;
Publication Date:
OSTI Identifier:
6059921
Report Number(s):
CONF-8606184-
Resource Type:
Conference
Resource Relation:
Conference: 22. joint propulsion conference, Huntsville, AL, USA, 16 Jun 1986
Country of Publication:
United States
Language:
English
Subject:
20 FOSSIL-FUELED POWER PLANTS; 42 ENGINEERING; COMBUSTORS; DESIGN; MATHEMATICAL MODELS; PLANNING; GAS TURBINES; COMBUSTION CONTROL; CONFIGURATION; EMISSION; HEAT FLUX; HEAT TRANSFER; PERFORMANCE; THERMODYNAMICS; THREE-DIMENSIONAL CALCULATIONS; VORTEX FLOW; CONTROL; ENERGY TRANSFER; FLUID FLOW; MACHINERY; TURBINES; TURBOMACHINERY; 200104* - Fossil-Fueled Power Plants- Components; 421000 - Engineering- Combustion Systems

Citation Formats

Rizk, N K, and Mongia, H C. Gas turbine combustor design methodology. United States: N. p., 1986. Web.
Rizk, N K, & Mongia, H C. Gas turbine combustor design methodology. United States.
Rizk, N K, and Mongia, H C. 1986. "Gas turbine combustor design methodology". United States.
@article{osti_6059921,
title = {Gas turbine combustor design methodology},
author = {Rizk, N K and Mongia, H C},
abstractNote = {The detailed representation of flow and combustion processes offered by multidimensional models and the predictive tool of the proven empirical correlations are combined to form a basis for a gas turbine combustor design method. Provisions are made to fully utilize the output of the analytical computations by evaluating the values of relevant parameters within subdivisions of liner sector. By this means, the impact of a systematic modification to the detail of dome swirlers and liner configuration is easily determined. A heat transfer calculation method that utilizes the variation in combustor parameters in the three dimensions and evaluates radiation flux components through a view factor is considered. In comparison with experimental data obtained for a typical production liner, the predictions of the developed method in regard to emission formation, combustion performance, and wall temperature are quite satisfactory.},
doi = {},
url = {https://www.osti.gov/biblio/6059921}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Wed Jan 01 00:00:00 EST 1986},
month = {Wed Jan 01 00:00:00 EST 1986}
}

Conference:
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.

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