Laser Velocimetry Study of Stator/Rotor Interactions in a Multi-Stage Gas Turbine Compressor,
PRATT AND WHITNEY AIRCRAFT GROUP EAST HARTFORD CT
Pagination or Media Count:
Measurement of airflow through multi-stage compressor rigs has generally been limited to use of flow perturbing pressure and temperature probes. The advent of the laser doppler velocimeter with its nonperturbing nature is expected to develop into the preferred instrumental method. In an exploratory program to assess the feasibility of using an LDV in these flows, a multi-stage compressor rig, consisting of 6th through 15th compressor stages, was outfitted with windows between the 6th stator-7th rotor, 9th stator-10th-rotor, and 13th stator-14th rotor. The windows, extending circumferentially one stator gap wide, permitted hub to tip traversing midway between the stator trailing edge and the rotor leading edge both in and out of the stator wakes. A confocal two color, two component back scatter LDV system developed for use in gas turbine environs was employed to obtain detailed mappings of velocity magnitude and air angle as a function of rotor position at several spanwise and gapwise positions downstream of the 6th and 9th compressor stators. The equipment used and the difficulties encountered are described.
- Fluid Mechanics
- Jet and Gas Turbine Engines
- Test Facilities, Equipment and Methods