GAS TURBINE ENGINE ANNULAR COMBUSTION CHAMBER DIFFUSER Russian patent published in 2025 - IPC F23R3/00 

FIELD: engines.

SUBSTANCE: invention relates to a diffuser of an annular combustion chamber of a gas turbine engine. Gas turbine engine annular combustion chamber diffuser comprises outer and inner walls, the diffuser outlet part location level is above the diffuser inlet part level, length L of the diffuser lies within range of 3 to 3.5 of the height h of the outlet part of the diffuser, the distance L1 between the outlet part of the diffuser and the burners of the combustion chamber lies within the range L1=1/2h÷3h, height h of the outlet part of the diffuser corresponds to the height h_b of the swirler in the burner and is located so that the swirler is completely inside the streamlines, above the outer wall and the inner wall there are recesses formed by the space between the diffuser walls overhang and the combustion chamber housings, angle α between the outer and inner walls of the diffuser does not exceed 12°, shaping of walls is performed in compliance with condition of isogradience , where dP is pressure change, dx is coordinate change.

EFFECT: invention makes it possible to provide uninterrupted flow in the channel part of the diffuser, low pressure losses, stabilization of the flow at increase of speed at the inlet to the combustion chamber.

1 cl, 1 dwg