Gas turbine combustor design methodology
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.
- OSTI ID:
- 6059921
- Report Number(s):
- CONF-8606184-
- Resource Relation:
- Conference: 22. joint propulsion conference, Huntsville, AL, USA, 16 Jun 1986
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
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