TURBO-JET ENGINE Russian patent published in 2009 - IPC F01D25/24 F01D11/00 

FIELD: engineering industry.

SUBSTANCE: turbo-jet engine consists of high pressure compressor, diffuser and combustion chamber. High pressure compressor consists of outer shell that restricts in a radial way the primary flow channel and that is connected to the ring-shaped construction protruding radially outwards. Diffuser consists of external housing connected to a conical support directed to rear part of engine, restricting the base of combustion chamber from above and connected to outer shell of housing. Support, outer shell of housing, and ring-shaped construction determine the cavity around diffuser. In the support there provided are air intake holes for the chamber base to be connected to cavity around diffuser. Outer shell of housing is equipped with air intake holes. Between ring-shaped construction and external housing of diffuser there provided are sealing means ensuring insulation of cavity from the primary flow channel. Sealing means are formed with a brush gasket fixed on periphery of upper part of external diffuser housing. Gasket consists of bristles located radially in the outward direction and supported on internal surface of cylindrical sleeve rigidly connected to ring-shaped construction and enveloping the brush gasket.

EFFECT: tightness between air intake cavity and primary flow channel in compressor irrespective of relative position of outer compressor shell and external diffuser housing.

4 cl, 8 dwg