Combustion chamber intermediate part for a gas turbine

Details Combustion chamber intermediate part for a gas turbine Combustion chamber intermediate part for a gas turbine

2007-11-27

2007-11-27

Casaregola, L. J. (Department: 3746)

Power plants

Combustion products used as motive fluid

Plural combustion products generators in ring coaxial with...

C060S752000

Reexamination Certificate

active

10487519

ABSTRACT:
This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers formed by input areas and transition areas converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes of the individual combustion chambers are placed at an angle relative to an engine axis that is defined by the axial extension of the turbine chamber. In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area of at least one individual combustion chamber into the turbine chamber is deflected in the direction of the engine axis and substantially in the input area of the turbine chamber.

REFERENCES:
patent: 2567079 (1951-09-01), Owner et al.
patent: 2592060 (1952-04-01), Oulianoff
patent: 3169367 (1965-02-01), Hussey
patent: 4195474 (1980-04-01), Bintz et al.
patent: 4264272 (1981-04-01), Weiler
patent: 4719748 (1988-01-01), Davis et al.
patent: 5414999 (1995-05-01), Barnes
patent: 5447413 (1995-09-01), Maier et al.

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