Design Geometry and Design/off-Design Performance Computer Codes for Compressorsand Turbines

摘要

This report summarizes some NASA Lewis (i.e., government owned) computer codescapable of being used for airbreathing propulsion system studies to determine the design geometry and to predict the design/off-design performance of compressors and turbines. These are not CFD codes; velocity-diagram energy and continuity computations are performed fore and aft of the blade rows using meanline, spanline, or streamline analyses. Losses are provided by empirical methods. Both axial-flow and radial-flow configurations are included.