Accession Number : ADD009954

Title :   Small Gas Turbofan Engine with Regenerating Diffuser.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Ellis,Stanley H

Report Date : 09 Nov 1982

Pagination or Media Count : 5

Abstract : This invention relates to a mixed flow, high bypass, gas turbofan engine that is small and compact, and that develops a thrust in the range of approximately 200-300 pounds. The engine has an axial length of approximately 18 inches, an air inlet of approximately 10 inches in diameter, and an exhaust nozzle of approximately 6 inches in diameter. To reduce engine length high pressure compressor diameter, a high pressure compressor is positioned in a location that is displaced from and is preferably parallel to the engine axis, a burner is similarly positioned on the other side of the engine axis, only one turbine is used, and a unique flow path also is used. In addition, a heat exchanger of the regenerative type which includes a plurality of pipe diffusers is used, and it is positioned in the hot exhaust flow of the single turbine to pre-heat the compressor air prior to entry into the burner. The small size, the thrust capability, and the good fuel consumption during part-power operation, make this engine ideal for use in air-launched cruise missiles. (Author)

Descriptors :   *Patents, *High bypass turbofans, *Sizes(Dimensions), *Length, Reduction, High pressure compressors, Burners, Heat exchangers, Systems engineering, Performance(Engineering), Efficiency, Thrust, Fuel consumption

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE