Development of a Temperature-Pneumatic Probe and Application at the Rotor Exit in a Transonic Compressor
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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The development is reported of a new combination temperature- pneumatic probe specifically to determine the blade element performance of the rotor in a transonic compressor. The design incorporates a fine wire thermocouple sensor which provides a measure of temperature rise that is insensitive to Mach number. With simultaneous measurements from four pneumatic sensors, the velocity vector was determined locally in radial surveys downstream of the compressor rotor. The probe was calibrated in a free jet. The calibration measurements were reduced to a set of equations to allow off-line reduction of compressor measurements using a Hewlett-Packard Model 9830A calculator and peripherals. The design, development, calibration, and application of the probe are described and initial results of measurements in the compressor are given.
- Test Facilities, Equipment and Methods
- Jet and Gas Turbine Engines