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U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 May 1948



In a power plant the combination of a combustion and turbine section including a housing, axially spaced bearings carried by the housing, a shaft supported in said bearings and carrying a turbine wheel at one end and a shaft coupling member at the other end, the bearing remote from the turbine rotor being axially adjustable relative to the housing and constructed and arranged to carry the thrust loads imposed on the turbine shaft, a plurality of elongated combustion chambers supported on the housing in radially spaced relation thereto and in circumferentially spaced relation to each other, said elongated chambers extending in a generally axial direction with their discharge ends located adjacent the turbine wheel and adapted to deliver hot gases thereto; a compressor section including a casing, axially spaced bearings carried by the casing, a compressor impeller arranged between said last‐mentioned bearings and having a shaft supported therein, one of said last‐mentioned bearings being axially adjustable relative to the casing and constructed and arranged to carry thrust loads imposed on the compressor shaft, said compressor shaft having a coupling member at one end thereof and the compressor casing having walls defining a vane type diffuser with a separate axially facing discharge opening for each diffusing passage; means connecting said housing and casing together with said coupling members in adjacent axially spaced relation, means connecting the coupling members constructed and arranged to allow independent axial adjustment of the turbine shaft and the compressor shaft relative to said casing and housing whereby the respective turbine and compressor clearances may be separately adjusted, and a separate air adapter member for conveying air from each diffuser discharge opening to the adjacent inlet end of a combustion chamber.


(1948), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 20 No. 5, pp. 158-158.




Copyright © 1948, MCB UP Limited

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