Идентификация граничных условий теплообмена турбины по результатам испытаний

Abstract

Convective boundary conditions for a turbine casing are determined on the basis of an aircraft engine testing. Improved accuracy in determination of the convective boundary conditions from the heat flux under complex nature of environment flow is achieved. The improvement occurred due to introduction of corrective coefficients for the heat transfer coefficients. The correction takes into account the conductive heat transfer inside the part. The identified temperature field of the turbine casing was compared with an experimentally measured one.