Numerical calculation of local convective heat transfer coefficients over aircooled vane surfaces
Abstract
A numerical model for iterative, simultaneous solution of twodimensional compressible boundary layer equations and steadystate equations of heat conduction is presented, together with a FORTRAN program for calculating the local convective heat transfer coefficients over an aircooled, vaned surface. The approximate integral method is employed for the boundary layer equation, while the finite element method is used to derive the temperature field of the blades. The program input comprises the blade geometry, the pressure or velocity distribution of the gas flow outside the boundary layer, the entrance flow characteristics, the internal cooling conditions, the nodal numbers, and the coordinates of the elements. The program yields the heat transfer coefficients and the temperature distribution on the surface and inside the blades. Good agreement was found with experimental results
 Publication:

Acta Aeronautica et Astronautica Sinica
 Pub Date:
 December 1982
 Bibcode:
 1982AcAAS...3..101L
 Keywords:

 Boundary Layer Equations;
 Compressible Boundary Layer;
 Computational Fluid Dynamics;
 Convective Heat Transfer;
 Finite Element Method;
 Heat Transfer Coefficients;
 Two Dimensional Boundary Layer;
 Computer Programs;
 Flow Characteristics;
 Flow Distribution;
 Fortran;
 Gas Flow;
 Inlet Flow;
 Iterative Solution;
 Steady State;
 Temperature Distribution;
 Fluid Mechanics and Heat Transfer