Investigation of Hot Streak Migration and Film Cooling Effects on Heat Transfer in Rotor/Stator Interacting Flows. Report 1
Final rept. 1 Nov 1988-1 Apr 1992
UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT
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Experimental data taken from turbine engines has shown that hot streaks exiting combustors can have a significant impact upon the secondary flow and will temperature of the first stage turbine rotor. Understanding the secondary flow and heat transfer effects due to combustor hot streaks is essential to turbine designers attempting to optimize turbine cooling systems. A numerical investigation has been performed which addresses the issues of multi-blade count ratio and three-dimensionality effects on the prediction of combustor hot streak migration in a turbine stage. The two- and three-dimensional Navier-Stokes analyses developed by Rai et al are used to predict unsteady viscous rotor-stator interacting flow in the presence of a combustor hot streak with heat transfer and film cooling. Predicted results are presented for a two-dimensional 3-stator4-rotor and a three-dimensional 1-stator1-rotor simulations of streak migration through a turbine stage. Comparison of these results with experimental data demonstrates the capability of the three- dimensional procedure to capture most of the flow physics associated with hot streak migration including the effects of combustor hot streaks on turbine rotor surface temperatures.
- Jet and Gas Turbine Engines