GAS TURBINE ENGINE Russian patent published in 2014 - IPC F01D11/18 F01D11/24 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises compressor with several axial stages including casing, guide vanes and working vanes and turbine comprising housing and at least one stage with guide vanes and working wheel as well as means for adjustment of radial clearances of at least one stage of compressor and/or turbine. Said means is composed of circular insert made of material with shape memory fitted in housing of compressor and/or turbine above appropriate working vanes of at least one stage. Valve is arranged in cooling air feed line. Said circular insert represents a porous component. Circular insert inner surface has sot coating, for example, graphite, or panels of "cellular seal" can be attached thereto.

EFFECT: efficient control over radial clearance, higher takeoff and augmenter thrust, efficiency and reliability.

3 cl, 9 dwg