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U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 February 1953



A gas turbine comprising a rotor having peripheral blades, a hollow shaft driven by said rotor, a casing around said shaft, at least one combustion chamber furnishing hot gases, means for applying said gases to said blades in a direction parallel to said shaft for driving said rotor, a main compressor driven by said shaft for compressing air to feed said combustion chamber, said rotor and said main compressor being arranged towards opposite ends of said casing, and an axial‐type compressor with multiple rotors and stators inside said casing, said first‐mentioned rotor being aperturcd to admit cold air to said axial‐type compressor, and said axial‐type compressor forcing the air to said main compressor in a direction opposite to the flow of said gases past said blades, in combination with another compressor driven by said shaft and drawing cold air through said hollow shaft, said other compressor feeding air to at least one combustion chamber furnishing hot gases to drive said first‐mentioned rotor.


(1953), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 25 No. 2, pp. 61-62.




Copyright © 1953, MCB UP Limited

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