An implicit time-marching higher-order accurate finite-difference method for solving the two-dimensional compressible Navier-Stokes equations was applied to the numerical analyses of steady and unsteady, subsonic and transonic viscous flows through gas turbine cascades with trailing edge coolant ejection. Annular cascade tests were carried out to verify the accuracy of the present analysis. The unsteady aerodynamic mechanisms associated with the interaction between the trailing edge vortices and shock waves and the effect of coolant ejection were evaluated with the present analysis.
|Journal||American Society of Mechanical Engineers (Paper)|
|Publication status||Published - 1997|
|Event||Proceedings of the 1997 International Gas Turbine & Aeroengine Congress & Exposition - Orlando, FL, USA|
Duration: 1997 Jun 2 → 1997 Jun 5