Off-design loss measurements in a compressor cascade
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Off-design loss measurements in a compressor cascade by Michael A. Classick

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Published by Naval Postgraduate School, Available from the National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in English


Book details:

Edition Notes

ContributionsShreeve, Raymond P.
The Physical Object
Pagination164 p.
Number of Pages164
ID Numbers
Open LibraryOL25479673M

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  Data acquisition software was written to recover the ability to make loss measurements using a five-hole pneumatic probe in a wind tunnel facility currently containing a modeled subsonic cascade of controlled diffusion (CD) stator blades. Acquisition, reduction and ancillary programs were written for a Hewlett Packard Series computer/HP Data Acquisition System in HP Cited by: 1. Off-design loss measurements in a compressor cascade. By Michael A. Classick. Get PDF (8 MB) Abstract. Approved for public release; distribution is unlimitedData acquisition software was written to recover the ability to make loss measurements using a five-hole pneumatic probe in a wind tunnel facility currently containing a modeled subsonic Author: Michael A. Classick. OFF-DESIGN LOSS MEASUREMENTS IN A COMPRESSOR CASCADE l A. Classick September Thesis Advisor: Raymond P. Shreeve I. A detailed investigation of the three-dimensional flow in a cascade of second-generation controlled-diffusion compressor stator blades, at off-design inlet-flow angle, is reported.

A commentary has been published: Discussion: “Loss and Stall Analysis of Compressor Cascades” (Lieblein, Seymour, , ASME J. Basic Eng., 81, pp. –) Views Icon Views Article contents. A method for predicting compressor cascade total pressure losses when the inlet relative Mach number is L., Answer to questionnaire on compressor loss and deviation angle correlations, AGARD-PEP, Working Group Modeling the Compressor Component, Design and Off-Design. In: Turbomachinery Flow Physics and Dynamic Performance.   The present study investigates profile losses in an axial compressor linear cascade using both RANS and wall-resolved large eddy simulation (LES), and compares with measurements. The analysis concentrates on “loss buckets,” local separation bubbles and boundary layer transition with high levels of free stream turbulence, as encountered in.   The compressor rotor blades exert forces on the working medium thereby increasing its total pressure. Based on efficiency and performance requirements, three types of compressor designs are applied. These are axial flow compressors, radial or .

Wake measurements identified a strong flow separation in the rear suction side dominating the transient character of the cascade flow. Towards the endwall this high loss region is reduced by the clearance flow and the resulting vortex, which is obviously not affected by the profile separation and the pulsating blockage frequency. Compressor stall was simulated in the Low Speed Cascade Wind Tunnel at the Turbopropulsion Laboratory. The test blades were of controlled-diffusion design with a solidity of , and stalling occurred at 10 degrees of incidence above the design inlet air angle. All measurements were taken at a flow Reynolds number, based on chord length, of. Cascade overall performance, blade-surface-pressure-distributions and flow-visualization are presented. The obtained results show that the blade shape has a strong influence on the loss behavior especially at off design conditions and on the shock system influencing the whole flow field of the blade row.   The results of two component laser-Doppler velocimeter (LDV) surveys made in the near wake (to one fifth chord) of a controlled diffusion (CD) compressor blade in a large scale cascade wind tunnel, are reported. The measurements were made at three positive incidence angles from near-design to angles thought to approach stall.