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U.S. Patent Specifications

U.S. Patent Specifications A gas turbine power plant comprising a compressor assembly consisting of a compressor rotor and an enclosing stationary structure, a turbine assembly consisting of a turbine rotor coaxial with the compressor rotor and an enclosing stationary structure, a shaft carrying said rotors, a combustion system accommodated between the compressor and turbine assemblies, said combustion system including an annular aircasing formed by an inner and outer tubular member mounted coaxially with the shaft and defining between them a flow path from said compressor to said turbine extending generally in an axial direction, and a plurality of flame tubes mounted within and annularly distributed around said aircasing, said outer tubular member being a unitary structure, the internal diameter of which over at least part of its length adjacent one end, is greater than the external diameter of the stationary structure adjoining said end of the tubular member, the external diameter of said stationary structure being less than the internal diameter of said tubular member from a point adjacent said end of said tubular member to a point located a substantial distance in a direction axially away from said tubular member, whereby said tubular member can be withdrawn over said stationary structure to expose the flame tubes. 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 (5): 2 – May 1, 1953
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032296
Publisher site
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Abstract

A gas turbine power plant comprising a compressor assembly consisting of a compressor rotor and an enclosing stationary structure, a turbine assembly consisting of a turbine rotor coaxial with the compressor rotor and an enclosing stationary structure, a shaft carrying said rotors, a combustion system accommodated between the compressor and turbine assemblies, said combustion system including an annular aircasing formed by an inner and outer tubular member mounted coaxially with the shaft and defining between them a flow path from said compressor to said turbine extending generally in an axial direction, and a plurality of flame tubes mounted within and annularly distributed around said aircasing, said outer tubular member being a unitary structure, the internal diameter of which over at least part of its length adjacent one end, is greater than the external diameter of the stationary structure adjoining said end of the tubular member, the external diameter of said stationary structure being less than the internal diameter of said tubular member from a point adjacent said end of said tubular member to a point located a substantial distance in a direction axially away from said tubular member, whereby said tubular member can be withdrawn over said stationary structure to expose the flame tubes.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: May 1, 1953

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