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U.S. Patent Specifications

U.S. Patent Specifications 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 axialtype compressor with multiple rotors and stators inside said casing, said firstmentioned rotor being aperturcd to admit cold air to said axialtype compressor, and said axialtype 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 firstmentioned rotor. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology , Volume 25 (2): 2 – Feb 1, 1953

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032266
Publisher site
See Article on Publisher Site

Abstract

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 axialtype compressor with multiple rotors and stators inside said casing, said firstmentioned rotor being aperturcd to admit cold air to said axialtype compressor, and said axialtype 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 firstmentioned rotor.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Feb 1, 1953

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