Development of a Thermal and Structural Analysis Procedure for Cooled Radial Turbines
Abstract
A procedure for computing the rotor temperature and stress distributions in a cooled radial turbine is considered. Existing codes for modeling the external mainstream flow and the internal cooling flow are used to compete boundary conditions for the heat transfer and stress analyses. An inviscid, quasi three dimensional code computes the external free stream velocity. The external velocity is then used in a boundary layer analysis to compute the external heat transfer coefficient. Coolant temperatures are computed by a viscous one dimensional internal flow code for the momentum and energy equation. These boundary conditions are input to a three dimensional heat conduction code for calculation of rotor temperatures. The rotor stress distribution may be determined for the given thermal, pressure and centrifugal loading. The procedure is applied to a cooled radial turbine which will be tested at the NASA Lewis Research Center. Representative results from this case are included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 09, 1988
- Accession Number
- ADA233526
Entities
People
- Ganesh N. Kumar
- Russell G. Deanna
Organizations
- National Aeronautics and Space Administration