To investigate the influence of thermodynamic parameters of combustion gas on convective heat transfer

a method of calculating thermodynamic parameters of multicomponent combustion gas was proposed for hydrocarbon-air combustion system in aero-engine system. The certain thermodynamic parameters derived by the method were then applied to simulate the convective heat transfer over flat plates and turbine cascades under different inlet temperatures and compare with the numerical results with air as working substance. Results showed that local convective heat transfer coefficients of the gas as the working substance were greater than the coefficients of the air for the flat plate and turbine cascade respectively

and with the rise of inlet temperature

the differences of the local Nusselt number of air and gas increased gradually under the same input conditions except different working substances for the flat plate and turbine cascade respectively. Within given inlet temperature range

the local Nusselt number of the flat plate rose from 28% to 30%

and the turbine cascade increased from 725% to 969%.