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U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 August 1955



In a gas turbine power plant, a plurality of substantially parallel flame tubes, an annular duct for said tubes, and a turbine inlet nozzle ring concentric to the duct, in combination with a transition piece extending from the flame tubes located in the annular duct to the turbine inlet nozzle ring concentric to the duct, said duct having inner and outer walls, said transition piece including a ring‐shaped frusto‐conical member adapted to extend from one of said walls to the nozzle ring, a plurality of duct extensions which are substantially cylindrical at one end and which converge to a segment shaped opening at the other end, said duct extensions being secured together to form a ring shape, and said extensions being secured at their segment shaped ends to one end of said ring‐shaped member, the latter being substantially co‐extensive axially with said extensions.


(1955), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 8, pp. 272-272.




Copyright © 1955, MCB UP Limited

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