Accession Number:

ADP003086

Title:

Annulus Wall Boundary Layer Development in a Compressor Stage Including the Effects of Tip Clearance,

Descriptive Note:

Corporate Author:

PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING

Report Date:

1983-09-01

Pagination or Media Count:

17.0

Abstract:

The end-wall boundary layer development in a compressor stage, including the inlet guide vane IGV passage and the rotor passage, was measured. Measurements upstream of the rotor and inside the IGV passage were carried out with a five-hole probe. The data blade-to-blade inside the rotor passage were measured using a three-sensor rotating hot-wire below the tip clearance region and a V configuration probe inside the clearance region. Rotor exit measurements blade-to-blade were acquired with a laser doppler velocimeter. Velocity profiles and the integral properties are presented and interpreted. The boundary layer is comparatively well behaved up to the leading edge of the rotor, beyond which complex interactions result in very unconventional profiles. The momentum thicknesses decrease in the leakage flow region of the rotor. The momentum thicknesses and the limiting streamline angles predicted from a momentum integral technique agree well with the data up to the leading edge of the rotor. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE