GAS-TURBINE ENGINE Russian patent published in 2007 - IPC F02C7/06 

FIELD: engine building; small-size gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine characterized in that it has unified lubricating system for supports using fuel as single kind of lubricating fluid has compressor, turbine, first bearing support disposed between compressor and turbine, combustion chamber mounted about this support, second bearing support disposed upstream of compressor or downstream of turbine, rotor shaft mounted on two support, fuel feed line running to first support, and channel for conveying fuel from the latter to combustion chamber. Gas-turbine engine is provided with fuel feed line running to second support and channel for discharging fuel from support. Cavity of this support accommodates fuel collector in the form of cup secured on shaft about support. This cup accommodates main fuel intake whose inlet is disposed near cup wall. Fuel intake communicates through fuel discharge channel with combustion chamber. Provided on inner wall of cup is annular groove incorporating inlet of fuel intake. Engine also has second-support space breathing line in the form of at least one radial channel provided in engine rotor shaft within fuel collector, as well as axial channel. The latter communicates with radial one and serves to provide communication between support space and environment. At least one channel affording communication between support space and radial channels is provided within fuel collector. Sealing member is fitted between fuel collector and support. Additional fuel intake is provided within fuel collector, its inlet being disposed at smaller diameter than inlet of main one but at larger diameter than sealing member. In addition, fuel intake communicates through fuel discharge channel with combustion chamber.

EFFECT: reduced maintenance charges and simplified design of engine.

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