NDLI: Investigation of blade-row flow distributions in axial-flow-compressor stage consisting of guide vanes and rotor-blade row

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Investigation of blade-row flow distributions in axial-flow-compressor stage consisting of guide vanes and rotor-blade row

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1950
Description	A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determine individual blade-row performance, interblade-row effects, and outer-wall boundary-layer conditions. Velocity gradients at guide-vane outlet without rotor approximated design assumptions, when the measured variation of leaving angle was considered. With rotor in operation, Mach number and rotor-blade effects changed flow distribution leaving guide vanes and invalidated design assumption of radial equilibrium. Rotor-blade performance correlated interpolated two-dimensional results within 2 degrees, although tip stall was indicated in experimental and not two-dimensional results. Boundary-displacement thickness was less than 1.0 and 1.5 percent of passage height after guide vanes and after rotor, respectively, but increased rapidly after rotor when tip stall occurred.
File Size	25727067
Page Count	58
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930086223
Archival Resource Key	ark:/13960/t0jt40m51
Language	English
Publisher Date	1950-11-28
Access Restriction	Open
Subject Keyword	Compressors - Axial Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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