BYPASS GAS TURBINE ENGINE, METHOD OF RADIAL GAP ADJUSTMENT IN TURBINE OF BYPASS GAS TURBINE ENGINE Russian patent published in 2013 - IPC F01D11/24 F02C7/18 

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine (GTE) comprises a compressor, a combustion chamber, a turbine comprising a cooled stage with a nozzle block with cavities above and under it, and a turbine rotor with a cooled impeller and a swirling device upstream it. A turbine stator comprises at least two turbine vessels with cavities between them. The system of radial gap adjustment comprises a circular insert above the turbine impeller. The cavity above the nozzle block is connected with a pipeline of air bleeding, comprising a controller of flow rate with outlet from a compressor. One of cavities between turbine vessels is connected with a pipeline comprising the second controller of flow rate with an intermediate stage of the compressor. The radial gap adjustment system comprises an on-board computer and sensors for radial gap measurement, a flow rate controller, drives of valves and sensors for measurement of the radial gap are connected by electric links. Flow rate of cooling air for turbine rotor cooling is varied depending on the mode of GTE operation, and when the radial gap achieves zero value, the maximum possible flow rate is switched on for cooling of the turbine regardless of the GTE operation mode.

EFFECT: efficient regulation of radial gaps in a turbine at all modes.

4 cl, 16 dwg