A finite difference solution to the two-dimensional wall jet on a combustion turbine blade
A simple model for the interaction of a tangentially oriented wall jet with the boundary layer is presented. The boundary-layer equations for steady, two-dimensional, homogeneous, incompressible flow are solved using an implicit finite difference technique. Calculations are performed for laminar and turbulent boundary layer flows with and without tangential jet injection. Results from the finite difference calculation for the laminar, non-injected cases are compared with the Falkner-Skan similarity solutions. Results from the finite difference calculation for the turbulent, noninj ected cases are compared with a two-parameter integral analysis. The boundary-layer calculation is applied to wall-jet injection near the leading edge of a representative combustion turbine blade. The blade geometry is developed by distributing a standard airfoil section over a single-parabolic camber line.