Accession Number : ADA111892

Title :   Blade Tip Gap Effects in Turbomachines - A Review.

Descriptive Note : Final rept. 1 Oct-30 Sep 80,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Peacock,Roy E

PDF Url : ADA111892

Report Date : Nov 1981

Pagination or Media Count : 103

Abstract : A review is presented of experiments examining the effects of blade tip gaps encountered in turbomachines and the methods by which the synthesised data are currently used in turbomachinery design and performance analysis. Data gained since the 1930's is subdivided for convenience into diffusing, or compressor-type flows, and accelerating, or turbine-type flows. There is a further sub-division into cascade and rotating machinery data. The overall trend university is that an increasing tip gap whose effect can reach over most or all of the blade height brings reduced overall performance of a turbomachine. Turbine data are in general more regular than the body of compressor data, possibly due in part to the enhanced effect of, usually, undefined boundary layers in diffusing flow. there is some evidence among the compressor and compressor cascade data that an optimum gap exists when the opposing effects of secondary flows, and tip leakage with rotor/wall relative movement tend to balance. Comment is made upon the prediction and design models published in the literature. (Author)

Descriptors :   *Gas turbines, *Axial flow compressors, *Compressor blades, *Aerodynamics, Literature surveys, Boundary layer, Clearances, Cascade structures, Inviscid flow, Mass flow, Efficiency, Mathematical models, Compressors

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE