Accession Number:

ADA955082

Title:

Tip-Clearance Flow and Losses for an Isolated Compressor Blade,

Descriptive Note:

Corporate Author:

AERONAUTICAL RESEARCH COUNCIL LONDON (ENGLAND)

Personal Author(s):

Report Date:

1963-01-01

Pagination or Media Count:

28.0

Abstract:

The effect of a gap in an isolated aerofoil spanning a tunnel has been investigted both theoretically and experimentally. Two flow models have been suggested one is valid for moderately large gapchord ratios and the other for the small gapchord ratios used in turbomachinery practice. The latter model takes into account the lift retained at the tip due to circulation bridging the gap. At samll gapchord ratios the decrease in total lift and the increase in drag are very small and the flow disturbance at the tip has very little effect on the pressure distributions at small distances from the tip. Flow visualization and vorticity measurements indicate that the position and strength of the tip vortex varies with the gap size. At small gapchord ratios, the leakage flow is very nearly perpendicular to the chord. It forms a vortex sheet which rolls up into a single discrete vortex at some distance from the suction surface and its spanwise distance from the tip is very small. At high gapchord ratios the leakage flow takes place at an anlge to the chord. It shows a tendency to roll up into a single vortext immediately it reaches suction surface and the core of this vortex is located a little inwards from the tip.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE