Method of operating gas turbine group with reheat combustor

Details Method of operating gas turbine group with reheat combustor Method of operating gas turbine group with reheat combustor

1994-03-15

1995-10-03

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

60 3917, F02C 314, F02C 7264

Patent

active

054542200

ABSTRACT:
In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).

REFERENCES:
patent: 2468461 (1949-04-01), Price
patent: 2821066 (1958-01-01), Clarke et al.
patent: 4206593 (1980-06-01), Su et al.
patent: 5184460 (1993-02-01), Franciscus et al.

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