Some modifications to, and operational experiences with, the two-dimensional, finite-difference, boundary-layer code, STAN5
Abstract
The two-dimensional, finite-difference boundary-layer code, STAN5, is the primary tool used at the NASA-Lewis Research Center for predicting turbine blade gas-side heat-transfer coefficients. A number of modifications have been made to the program to enhance its usefulness for these calculations. Experience in using STAN5 has identified some problems in the program that can be treated through program input, without modifying the program. These include the presence of a small separation bubble near the leading edge, and the effect of full-coverage film cooling on transition to turbulence. Some of the techniques used to treat these problems are described.
- Publication:
-
American Society of Mechanical Engineers
- Pub Date:
- March 1981
- Bibcode:
- 1981gatu.confQ....G
- Keywords:
-
- Computer Programs;
- Finite Difference Theory;
- Gas Turbine Engines;
- Heat Transfer Coefficients;
- Rotor Blades (Turbomachinery);
- Two Dimensional Boundary Layer;
- Boundary Layer Transition;
- Energy Dissipation;
- Film Cooling;
- Leading Edges;
- Nusselt Number;
- Separated Flow;
- Stagnation Point;
- Velocity Distribution;
- Fluid Mechanics and Heat Transfer