Blade tip gap effects in turbomachines
Subtitle: a review
By: R.E. Peacock
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1981
Place of publication: Monterey, California
Language: eng
Number of pages: 101
Subjects: Efficiency; Fluid dynamics; Compressors; Blades; Turbines; Turbomachines
Description: 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)
Notes: Title from cover.

"Prepared for: Naval Air Systems Command"--Cover.

"November 1981"--Cover.

"NPS67-81-016"--Cover.

DTIC Identifiers: Tip gap optimization, LPN-A310-3100/186-A/1R02-403-001, PE61153N.

Author(s) key words: Tip clearance losses, turbomachines, compressors and turbines.

Includes bibliographical references (p. 60-64).

"Approved for public release; distribution unlimited"--Cover.

Technical report; 1981.

kmc/kmc 10/23/09.