Instrumentation Interference in a Transonic Linear Cascade

Abstract A major challenge when testing high-speed flows in turbomachinery applications concerns instrumentation intrusiveness. The current work exposes the impact of aerodynamic probes, placed upstream and downstream article, on aerodynamics a transonic low-pressure turbine blade investigated linear cascade at engine-representative outlet Mach Reynolds numbers. effect probe can be perceived as far to inlet cascade. quantification is presented loading well used monitor operating conditions during testing. It shown that presence partially compensated. this compensation loss reported.