Gas turbine engines with toroidal combustors

Details Gas turbine engines with toroidal combustors Gas turbine engines with toroidal combustors

1976-11-26

1979-05-01

Garrett, Robert E.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3965, 60 3974R, F02C 308

Patent

active

041517091

ABSTRACT:
A gas turbine engine is described in which a compressor, combustor and turbine are arranged in series flow relationship. The compressor discharge is outwardly angled. This pressurized air is then introduced into a toroidal combustion chamber of the combustor to create an annular vortex within which the combustion process is maintained. The hot gas stream generated is discharged from the combustion chamber to a centripital turbine which drives the compressor rotor. A portion of the pressurized air is introduced into the combustion chamber adjacent the hot gas stream discharge exit and in general flow opposition thereto, to dilute the hot gas stream and confine the combustion process within the combustion chamber, thereby minimizing the possibility of overtemperaturing the turbine. The combustor housing also defines the outer bounds of the hot gas stream flowing through the turbine. A power turbine converts a major portion of the energy of the hot gas stream to a motive shaft power output.

REFERENCES:
patent: 2658338 (1953-11-01), Leduc
patent: 2855754 (1958-10-01), Giannotti
patent: 2924937 (1960-02-01), Leibach
patent: 3010281 (1961-11-01), Cervenka et al.
patent: 3285006 (1966-11-01), Freeman et al.
patent: 3309866 (1967-03-01), Kydd
patent: 3613360 (1971-10-01), Howes
patent: 4018043 (1977-04-01), Clemmens
Judge; A. W., "Small Gas Turbines", MacMillan Co., N.Y, 1960, p. 279.

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