TURBINE OF GAS TURBINE ENGINE AND METHOD FOR ADJUSTMENT OF RADIAL CLEARANCE IN TURBINE Russian patent published in 2014 - IPC F01D11/24 

FIELD: machine building.

SUBSTANCE: turbine of a bypass gas turbine engine comprises a cooled stage with a nozzle diaphragm with cavities above and below it and a turbine rotor with a cooled runner. The turbine stator comprises at least two turbine casings with cavities in-between and a radial clearance adjustment system including a ring insertion above the turbine runner. The cavity above the nozzle diaphragm is connected to a compressor output by an air bleed pipeline including a flow regulator. The radial clearance adjustment system comprises an on-board computer, sensors for radial clearance measurement and microwave radiation sources set above the insertion. The radial clearance measuring sensors and the microwave radiation sources are connected by electric links with the on-board computer. The microwave radiation sources are made so that to be able of heating the ring insertion. The radial clearance is measured and basing on its value the microwave radiation sources are switched on.

EFFECT: effective control of radial clearances in a turbine in all modes, increasing engine thrust in takeoff and afterburner modes, increasing turbine efficiency factor and reliability.

4 cl, 7 dwg