GAS TURBINE COMBUSTOR Russian patent published in 2018 - IPC F23R3/48 F02C7/18 

FIELD: turbines or turbomachines.

SUBSTANCE: invention provides a combustion chamber for a gas turbine, and in particular a combustion chamber including a plurality of combustion chambers for mixing and burning fuel and air and interconnected by a cross-fire tube. According to the present invention, gas turbine is provided with a guide ring for directing the air flow, positioned in a position opposite the air holes. One end portion of the annular space formed between the guide ring and the cross-fire tube is open to the space inside the cross-fire tube, and the other end portion is a closed end that connects to the separating wall of the cross-fire tube. Length of the annular space between the air holes and the closed end is three or more times larger than the diameter of the air holes. In addition, a part of the air holes is drilled with a slope toward the closed end of this annular space, which provides cooling of the cross-fire tube including the guide ring, with a small amount of cooling air. A variant of the combustion chamber of a gas turbine is also provided, characterized in that a projecting part is provided between the air holes and the open end, which ensures the braking of the air flow.

EFFECT: invention provides cooling of the cross-fire tube without reducing the temperature of the combustion exhaust gas passing through the cross-fire tube, and also allows to prevent thermal deformation and burn-out of the cross-fire tube.

10 cl, 9 dwg, 1 tbl