INTERMEDIATE HOUSING ASSEMBLY OF GAS TURBINE ENGINE Russian patent published in 2019 - IPC F23R3/02 F01D9/06 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to turbine construction, particularly, to gas turbine engines (GTE) for ground and aviation applications. In the gas turbine engine intermediate housing assembly, located between the compressor and the turbine, comprising two annular channels for supply of air from the compressor to the remote combustion chamber and from the external combustion chamber to the turbine through the corresponding branch pipes, unlike known annular channel of air supply from compressor to remote combustion chamber is located inside annular channel of gas supply from external combustion chamber to turbine and is equipped with inclined end wall, and in channel diffuser there is flow divider and guide plates.

EFFECT: reduced pressure losses in combustion chamber and increased efficiency of gas turbine engine.

1 cl, 3 dwg