GAS TURBINE COMBUSTION CHAMBER Russian patent published in 2023 - IPC F23R3/34 

FIELD: gas turbine plants.

SUBSTANCE: invention can be used in the combustion chambers of aircraft gas turbine engines. The combustion chamber of the gas turbine plant contains a flame tube with a front device, an additional front device installed on the wall of the flame tube. The additional front device consists of a body with outer and inner walls, with a mixing chamber installed between them and interconnected pylons. The pylons are wedge-shaped in cross section and with a flat wall, installed evenly around the circumference with gaps between them. The outer wall of the housing contains a fuel cavity communicated with the fuel supply channels. The mixing chamber is connected at the inlet with channels for supplying air through the gaps between the pylons, and at the outlet it is in communication with the channel for supplying the air-fuel mixture to the flame tube. The mixing chamber is equipped with a fairing installed on the outer wall of the body of the additional front device. The wedge-shaped pylons face the mixing chamber with their flat wall; a calibrated hole for fuel supply is made in the flat wall of each pylon. The pylons are provided with a channel communicated on one side with the fuel cavity, and on the other side with the mixing chamber through a calibrated hole.

EFFECT: increased efficiency and reliability of the combustion chamber of a gas turbine plant in the conditions of its operation at high temperatures and air pressure at the inlet to the combustion chamber, expansion of the range of low-emission operation of the gas turbine combustion chamber.

3 cl, 3 dwg