Development of a Shock Capturing Code for Use as a Tool in Designing High-Work Low Aspect Ratio Turbines

摘要

A numerical algorithm is developed with the capability of capturing shocks in the internal blade passages of a modern gas turbine. The algorithm uses MacCormack's explicit finite difference scheme to solve the two-dimensional form of the Euler equations. Inlet and exit boundary conditions are developed that allow disturbances to propagate out of the computational domain without reflection. Periodic boundary conditions are applied such that an infinite cascade is modeled. The computed steady state solution is compared with experimental data for a high-work low aspect ratio turbine. The ability to obtain a reasonably accurate blade loading diagram within a practical execution time is demonstrated. Two oblique shocks, typical of those formed at the trailing edge of a transonic rotor blade, are captured. These shocks are smeared over several grid points, as expected with a chock capturing scheme, but their influence on the blade loading diagram is evident. Theses. (mjm)