Результаты опытов по теплообмену в проточной части турбин и компрессоров газотурбинных двигателей

Abstract

Experimental investigations of heat transfer processes inside turbine and compressors flow parts for Gas Turbine engines and power plants had been fulfilling in KSTU-KAI during many years. This work presents the collections of data for heat transfer border condition inside turbine and compressor current of Gas Turbine engines that allow calculating temperature condition of them parts. Generalized equation, which has been received in this work, allow calculate heat transfer coefficients on various parts of stator and rotor of turbine and compressor: for rotor parts - on profile blade surface; on face blade-to-blade surface; on turbine blades. For stator parts: inside axial clearance downstream of nozzles; inside radial clearance above turbine rotor; inside axial clearance downstream of turbine rotor; on face surfaces blade-to-blade channels of nozzles and direct blades.