GAS TURBINE COMBUSTION CHAMBER Russian patent published in 2018 - IPC F23R3/10 F23R3/42 F23R3/28 

FIELD: fuel combustion devices.

SUBSTANCE: gas turbine combustion chamber includes the swirler edge located on the outer edge of the plate with air holes with protrusion towards the combustion cavity, and a spring-loaded sealing installed at the combustion chamber insert with a plate with air holes and a swirler edge interface portion. Spring-loaded sealing has an air hole designed to ensure the passage of the combustion air portion, introduced into the gap between the plate with the air holes outer edge and the combustion chamber insert. Swirler edge has an air hole designed to enter the combustion air part that has passed through the air hole in the spring-loaded sealing into the combustion cavity. Combustion chamber inert has an air hole located opposite the air hole in the spring-loaded sealing, designed to enter of the combustion air part outside the combustion chamber insert into the gap between the plate with air holes outer edge and the combustion chamber insert. On the combustion chamber insert end portion, on the combustion chamber insert with a plate with air holes interface side, a rotary guide is installed designed to straighten the combustion air flow.

EFFECT: due to the plate with air holes outer edge effective cooling, the invention enables possibility of the swirler edge deformation / damage prevention at this plate with air holes outer edge.

9 cl, 8 dwg