Film-cooling prediction on rotor blade leading edge in 1-1/2 turbine stage

Numerical simulations have been performed to predict the film-cooling effectiveness and the associated heat transfer coefficient on the leading edge of a rotating blade in a 1-1/2 turbine stage. The Reynolds stress turbulence model together with the nonequilibrium wall function is employed in the simulation. A sliding grid is used for the rotor domain, and an interface technique is employed to exchange the information between stator and rotor domains. Simulations are carried out for both the design and the off-design conditions to investigate the effects of the statorrotor interaction on the film-cooling characteristics. The unsteady characteristics of the heat transfer coefficient and film-cooling effectiveness at various rotating speeds are also investigated. With increasing rotating speed, the tilt stagnation line on the leading edge of a rotor moves from the pressure side to the suction side, and the instantaneous coolant streamlines shift from the suction side to the pressure side. This trend is supported by the experimental results. In addition, the detailed instantaneous heat transfer coefficient and film-cooling effectiveness at various time phases, as well as different rotating speeds, are also reported. Copyright 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Film-cooling prediction on rotor blade leading edge in 1-1/2 turbine stage Academic Article