Gas turbine combustion chamber arrangement

Details Gas turbine combustion chamber arrangement Gas turbine combustion chamber arrangement

1976-01-16

1977-08-09

Freeh, William L.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3965, 60 3974S, F02C 308, F02C 718, F02C 722, F02C 730

Patent

active

040402517

ABSTRACT:
A gas turbine has a combustion chamber of toroidal configuration that includes separation structure dividing the combustion chamber into an annular primary zone and an annular dilution zone. Injection of compressor discharge air into the primary zone sets up a toroidal recirculation pattern of generally circular cross-sectional configuration. Fuel slinger structure at the inner periphery of the primary zone has a generally cylindrical surface for receiving and distributing fuel in a thin sheet for discharge in a radially outward direction as minute droplets towards the center of the toroidal recirculation pattern. The radial flow of the fuel droplets interacts with said toroidal recirculation pattern and provides intimate mixing of fuel and air, and resulting efficient combustion within said primary zone. The resulting combustion product flows from the primary zone past the separation structure into the dilution zone. Compressor discharge air injected into the dilution zone dilutes the products of combustion from the primary zone.

REFERENCES:
patent: 2856755 (1958-10-01), Szydlowski
patent: 3018625 (1962-01-01), Bachle
patent: 3124933 (1964-03-01), Stram
patent: 3381471 (1968-05-01), Szydlowski
patent: 3921393 (1975-11-01), Bracken
patent: 3932988 (1976-01-01), Beaufrere

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