Single chamber type combustion structure for a gas turbine engin

Details Single chamber type combustion structure for a gas turbine engin Single chamber type combustion structure for a gas turbine engin

1976-05-12

1978-05-23

Garrett, Robert E.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3965, F02C 314, F02C 914

Patent

active

040903605

ABSTRACT:
A single chamber type combustion structure particularly for industrial gas turbine plants in which the axis of the chamber forms a perpendicular to the axis of the compressor-turbine group wherein primary combustion air, delivered by the compressor coupled to the turbine driven by the combustion gases, flows through an annular duct formed between concentric outer and inner walls of the single combustion chamber from one end thereof to the other where its direction is then reversed for flow into the combustion zone within the inner wall through a rotatable vortex blading surrounding a fuel burner. A circular assembly of circumferentially spaced adjustable air deflector vanes is mounted in the annular duct for controlling the distribution of the primary air flowing through the duct prior to entry to the rotatable vortex blading.
The combustion gases discharged from the combustion chamber enter the turbine by way of an annular nozzle concentric with the turbine inlet.

REFERENCES:
patent: 2408743 (1946-10-01), Elliott
patent: 3133416 (1964-05-01), Mock
patent: 3280555 (1966-10-01), Charpentier et al.
patent: 3577878 (1971-05-01), Burnley et al.

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