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Composite Matrix Cooling Scheme for Small Gas Turbine CombustorsThe design, manufacture, and testing of a compliant metal/ceramic (CMC) wall cooling concept-implementing combustor for small gas turbine engines has been undertaken by a joint U.S. Army/NASA technology development program. CMC in principle promises greater wall cooling effectiveness than conventional designs and materials, thereby facilitating a substantial reduction in combustor cooling air requirements and furnishing greater airflow for the control of burner outlet temperature patterns as well as improving thermodynamic efficiency and reducing pollutant emissions and smoke levels. Rig test results have confirmed the projected benefits of the CMC concept at combustor outlet temperatures of the order of 2460 F, at which approximately 80 percent less cooling air than conventionally required was being employed by the CMC combustor.
Document ID
19900060155
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Paskin, Marc D.
(General Motors Corp. Indianapolis, IN, United States)
Ross, Phillip T.
(General Motors Corp. Indianapolis, IN, United States)
Mongia, Hukam C.
(General Motors Corp. Allison Gas Turbine Div., Indianapolis, IN, United States)
Acosta, Waldo A.
(NASA Lewis Research Center; U.S. Army, Propulsion Directorate, Cleveland OH, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2158
E-5698
Meeting Information
Meeting: 26th Joint Propulsion Conference
Location: Orlando, FL
Country: United States
Start Date: July 16, 1990
End Date: July 18, 1990
Sponsors: American Inst. of Aeronautics and Astronautics
Accession Number
90A47210
Funding Number(s)
CONTRACT_GRANT: NAS3-24226
Distribution Limits
Public
Copyright
Other

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