ANNULAR WALL OF COMBUSTION CHAMBER WITH OPTIMIZED COOLING Russian patent published in 2020 - IPC F23R3/04 

FIELD: machine building.

SUBSTANCE: annular wall of the combustion chamber of the gas turbine engine comprises between the cold side and the hot side a plurality of air inlet holes distributed along at least one annular row so that air flowing along the cold side penetrates to the hot side, a plurality of cooling holes to allow air flowing along the cold side to penetrate to the hot side to form a cooling air film along the annular wall. Air inlet holes create zones of sharp temperature gradient around them. Cooling holes are distributed over a plurality of annular rows, which are spaced from each other in axial direction, and axes of each of cooling holes are inclined in direction D of axial flow of gas for combustion at angle of θ1 inclination relative to normal N to annular wall. Annular wall additionally comprises, in zones of abrupt temperature gradient, multi-perforation holes having corresponding bends at angle α exceeding 90°. Angle α is measured between inlet axis Ae and outlet axis As of multi-perforation hole. Outlet axis of the multi-perforation hole is inclined at an angle θ3 relative to the normal N to the annular wall, through which the multi-perforation holes with bends are formed, in the so-called rotation direction, which is at most perpendicular to the direction D of the axial flow of the combustion gas.

EFFECT: invention is aimed at improving cooling efficiency.

12 cl, 6 dwg