Case Wall Pressures in a Multistage Axial Compressor with Tip Clearance Variation
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Authors
Moyle, I.N.
Shreeve, R.P.
Walker, G.J.
Subjects
Advisors
Date of Issue
1996
Date
Publisher
AIAA
Language
Abstract
Large cyclical pressure excursions from stator-averaged values are observed on the suction side of a
rotor blade at the case wall in a multistage compressor as the rotor moves relative to the stator. The
pressure changes correlate well with stator relative position, occur in the passage away from the blade,
and are only slightly modified by tip clearance changes. Close to the entry and exit of the tip gap, however,
the pressures remain stable. The pressures near the gap are only slightly affected by stator proximity
and primarily vary with tip gap height.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/3.24129
Presented as Paper 93-2389 at the AIAA/SAE/ASME/ASEE 29th Joint Propulsion Conference, Monterey, CA, June 28-30, 1993
Presented as Paper 93-2389 at the AIAA/SAE/ASME/ASEE 29th Joint Propulsion Conference, Monterey, CA, June 28-30, 1993
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Air Systems Command
Air Breathing Propulsion Research Program
Air Breathing Propulsion Research Program
Funder
Format
7 p.
Citation
Moyle, I. N., R. P. Shreeve, and G. J. Walker. "Case wall pressures in a multistage axial compressor with tip clearance variation." Journal of propulsion and power 12.5 (1996): 967-973.
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.