Evaluation of miniaturized fast resposnse probes

Measurements of aerodynamic performances in turbomachinery require continuous development of miniaturized instruments capable to capture the unsteadiness of the flow. Two new prototypes of miniaturized fast response pressure probes for total pressure measurements and flow directions are developed. A state of the art single hole pressure probe is selected as a reference design for the prototypes. A smaller transducer is chosen to get further miniaturization. Geometrical dimensions are scaled and optimized accordingly. To increase angular insensitivity for total pressure measurements a Kiel shaped shield is introduced. Aerodynamic performances of probes in operating conditions are also modelled numerically solving URANS equations with Numeca FINE/Open™. A multi parameters approach is implemented and adopted to assess the convergence of unsteady computations. Two prototypes are manufactured and preliminary tests for angular sensitivity are executed.