Gas turbine combustor with means for removing swirl

Details Gas turbine combustor with means for removing swirl Gas turbine combustor with means for removing swirl

1996-07-23

1998-04-07

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 39826, 60746, F23R 304

Patent

active

057351155

ABSTRACT:
The invention relates to a combustion chamber (6) for a gas turbine (6, 18, 19) through which a flow (2) of compressed air is allowed to pass, flowing along an axis (3) from a compressor part (18) to a turbine part (19), said flow (2) having a swirl relative to the axis (3). In this arrangement, an annular passage (4) is provided at the inlet of the combustion chamber (6) having an inflow part (8) for separating a partial flow (1) from the flow (2), which comprises means (11) for removing the swirl from the partial flow (1), and which communicates with the cooling passages (14) for cooling the combustion chamber (6) as well as with pilot burners (7) for stabilizing combustion in the combustion chamber (6). The combustion chamber (6) is configured in an especially favorable manner with regard to avoiding thermodynamic losses and permits the separation of a partial flow (1) which is outstandingly suitable both for cooling purposes and for stabilizing purposes.

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