ABSTRACT
Gas turbine propulsion system development traditionally proceeds from design conceptualization to analysis to individual component/stage perfor-mance testing before the complete engine is assembled and run. The objective of this chapter is to introduce methodologies, techniques, and suggested procedures for turbomachinery component aerodynamic perfor-mance testing. Turbomachinery component testing reduces design and development risks while verifying engineering analysis and performance estimates. Inlets, fans, compressors, combustors, turbines, and exhaust nozzle components are all traditionally tested individually as part of the gas turbine development process. Even after an engine has been assembled and tested, component tests are often used to support performance improve-ments and diagnostic testing.
