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Combustion hot section technologyThe Turbine Engine Hot Section Technology Combustion Program is briefly described. The overall objective of the project is to develop and verify improved and more accurate analysis methods for increasing the ability to design with confidence the combustion system for advanced aircraft turbine engines. The approach is to first assess and evaluate existing combustor aerothermal analysis models by means of a contracted effort initiated during FY-82. The program also includes both analytical and experimental research efforts in the areas of aerothermal modeling and liner cyclic life. It is expected that the combustor model development effort will generate improved understanding in the areas of high pressure flame radiation characteristics, model numerical methods and solution schemes, complex geometrical boundary conditions, fuel spray - flow field interactions, combustion kinetics, flow and mixing of dilution jets, turbulence and heat transfer, and soot and carbon formation.
Document ID
19850002673
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ercegovic, D. B.
(Army Research and Technology Labs. Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1982
Publication Information
Publication: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST)
Subject Category
Aircraft Propulsion And Power
Accession Number
85N10981
Distribution Limits
Public
Copyright
Public Use Permitted.
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