GAS-TURBINE ENGINE Russian patent published in 2007 - IPC F02C7/12 

FIELD: aviation industry.

SUBSTANCE: invention relates to gas turbine engines of aircraft and ground application. According to invention, gas-turbine engine contains compressor, combustion chamber, turbine and shaft jacket with insulation, arranged from inner side of combustion chamber, which includes front and rear parts in direction of flow and flexible member placed in between and is connected with supports of compressor and turbine bearings and is coupled with ring closed air spaces of front and rear parts and with air space from outer side of flexible member. Ring closed air spaces of front and rear parts of shaft jacket at inlet are made for communication with intermediate stage of compressor, and at outlet, with spaces of labyrinth seals of oil spaces of compressor and turbine bearings, respectively, and with air space from outer side of flexible member which is connected at outlet by channel with space between inner housing of combustion chamber and shaft jacket. Heat insulation in zone of channel outlet is provided with ring axial lips forming additional air space and ring slotted outlet channel.

EFFECT: increased reliability of gas-turbine engine and its service life owing to reduction of heat transfer to oil in inner space of engine shaft jacket, improved efficiency of cooling of compressor and turbine bearings.

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