kThis study investigated the Navier-Stokes L computations of the surface heat transfer coefficients of a transition duct flow. A transition duct from an axisymmetric n cross section to a nonaxisymmetric cross section, is usually used to connect the turbine exit to the nozzle. As the gas Pr turbine inlet temperature increases, the transition duct is subjected to the high temperature at the gas turbine exit. pThe transition duct flow has combined development of hydraulic and thermal entry length. The design of the Qw transition duct required accurate surface heat transfer coefficients.The Navier-Stokes computational method R could be used to predict the surface heat transfer coefficients

Assuming the local adiabatic wall temperature equals the local total temperature in a low speed coolant mixing layer, integral conservation equations with and without the boundary layer effects are formulated for the mixing layer downstream of a single coolant injection hole oriented at a 30 degree angle to the crossflow. These equations are solved numerically to determine the center-line local adiabatic wall temperature and the effective coolant coverage area. Comparison of the numerical results with an existing film cooling experiment indicates that the present analysis permits a simplified but reasonably accurate prediction of the centerline effectiveness and coolant coverage area downstream of a single hole crossflow stream wise injection at 30-deg inclination angle.