COMBUSTION CHAMBER OF GAS TURBINE ENGINE WITH IMPACT-JET COOLING OF FLAME TUBE Russian patent published in 2025 - IPC F23R3/06 F23R3/02 

FIELD: engines.

SUBSTANCE: proposed design relates to combustion chambers of gas turbine engines (GTE) and can be used in turbomachine building. In the design of the gas turbine engine combustion chamber with the flame tube impact-jet cooling, made with double walls: "cold" – on the side of air flow from behind the compressor and "hot" – on the side of the flame, with formation of a discharge channel between them, "Cold" wall is equipped with branch pipes ("nozzles"), supplying to the "hot" wall of cooling air jets, which is directed through the discharge channel to the front device of the flame tube and, if necessary, for film or effusion cooling of the "hot" wall, in contrast to the known one, the discharge channel can further direct air into the "combustion zone" and "dilution zone", downstream in these directions is made with an increase in the cross-sectional area after each row of branch pipes by a value not less than the total outlet area of the branch pipes of this row, increase in area can be from stepped to smoothly variable, and at least the first row of holes in the "cold" wall upstream is made without branch pipes.

EFFECT: reduction of specific fuel consumption in gas turbine engine by reduction of total air pressure losses in combustion chamber during impact-jet cooling of flame tube with double walls due to increase in cooling efficiency of its internal ("hot") walls, which also enables to reduce the amount of air for their cooling, this is achieved by optimizing the design of the “cold” wall of the flame tube and the shape of the branch pipes.

8 cl, 8 dwg