A computer program for the transient thermal analysis of an impingement cooled turbine blade
Abstract
A computer program to calculate transient and steady state temperatures, pressures, and coolant flows in a cooled turbine blade or vane with an impingement insert is described. Input to the program includes a description of the blade geometry, coolant supply conditions, outside thermal boundary conditions and wheel speed. Coolant-side heat transfer coefficients are calculated internally in the program, with the user specifying the mode of heat transfer at each internal flow station. Program output includes the temperature at each node, the coolant pressures and flow rates, and the inside heat transfer coefficients. A sample problem is discussed.
- Publication:
-
AIAA, Aerospace Sciences Meeting
- Pub Date:
- January 1978
- Bibcode:
- 1978aiaa.meetS....G
- Keywords:
-
- Air Cooling;
- Computer Programs;
- Heat Transfer;
- Jet Impingement;
- Transient Response;
- Turbine Blades;
- Air Jets;
- Coolants;
- Cross Flow;
- Flow Velocity;
- Gas Pressure;
- Gas Temperature;
- Heat Transfer Coefficients;
- Steady State;
- Thermal Boundary Layer;
- Vanes;
- Fluid Mechanics and Heat Transfer