GAS TURBINE ENGINE AND METHOD FOR RADIAL CLEARANCE ADJUSTMENT IN GAS TURBINE Russian patent published in 2014 - IPC F01D11/24 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises compressor, combustion chamber, turbine rotor and stator. Turbine comprises cooled cascade with guide vanes with chambers above and under said guide vanes. Turbine rotor incorporates cooled working wheel and swirler arranged there ahead. Turbine stator includes at least two turbine cases with chambers there between and radial clearance adjusting system incorporating circular insert above working wheel. Chamber above guide vanes is communicated via air bleed pipe including flaw rate regulator with compressor outlet. One of chambers between turbine cases is communicated via pipeline with second flow rate regulator with compressor mid-cascade. Radial clearance adjustment system comprises onboard computer, radial clearance transducers and flow rate controller. Valve drives and radial clearance transducers are connected by electric couplings. Method of radial clearance adjustment includes the cooling of rotor and stator. Radial clearance is measured to vary airflow rate for turbine cooling subject to measured value. Said airflow rate is discretely varied depending upon gas turbine engine operating conditions.

EFFECT: efficient adjustment, higher thrust, efficiency and reliability.

2 cl, 14 dwg