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Supercritical fuel injection systema fuel injection system for gas turbines is described including a pair of high pressure pumps. The pumps provide fuel and a carrier fluid such as air at pressures above the critical pressure of the fuel. A supercritical mixing chamber mixes the fuel and carrier fluid and the mixture is sprayed into a combustion chamber. The use of fuel and a carrier fluid at supercritical pressures promotes rapid mixing of the fuel in the combustion chamber so as to reduce the formation of pollutants and promote cleaner burning.
Document ID
19810020591
Document Type
Other - Patent
Authors
Marek, C. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Cooper, L. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
February 26, 1980
Subject Category
Aircraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,189,914|NASA-CASE-LEW-12990-1
Patent Application
US-PATENT-APPL-SN-916654

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