Assessment of a 3D boundary layer analysis to predict heat transfer and flow field in a turbine passage
Abstract
An assessment was made of the applicability of a three dimensional boundary layer analysis of heat transfer, total pressure losses, and streamline flow patterns on the surfaces of both stationary and rotating turbine passages. In support of this effort, an analysis was developed to calculate a general nonorthogonal surface coordinate system for arbitrary three dimensional surfaces and also to calculate the boundary layer edge conditions for compressible flow using the surface Euler equations and experimental pressure distributions. Calculations are presented for the pressure, endwall, and suction surfaces of a stationary cascade and for the pressure surface of a rotating turbine blade. The results strongly indicate that the three dimensional boundary layer analysis can give good predictions of the flow field, loss, and heat transfer on the pressure, suction, and endwall surface of a gas turbine passage.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 August 1985
 Bibcode:
 1985STIN...8830066A
 Keywords:

 Flow Distribution;
 Fluid Dynamics;
 Gas Turbine Engines;
 Heat Transfer;
 Three Dimensional Boundary Layer;
 Assessments;
 Computation;
 Coordinates;
 Euler Equations Of Motion;
 Pressure;
 Suction;
 Walls;
 Fluid Mechanics and Heat Transfer