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

One of 5,163 reports in the series: NACA Research Memorandums available on this site.

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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 ... continued below

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Mahoney, John J.; Dugan, Paul D.; Budinger, Raymond E. & Goelzer, H. Fred November 28, 1950.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 260 times . More information about this report can be viewed below.

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  • Main Title: Investigation of blade-row flow distributions in axial-flow-compressor stage consisting of guide vanes and rotor-blade row
  • Series Title: NACA Research Memorandums

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.

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  • Accession or Local Control No: 93R15513
  • URL: http://hdl.handle.net/2060/19930086223 External Link
  • Report No.: NACA-RM-E50G12
  • Center for AeroSpace Information Number: 19930086223
  • Archival Resource Key: ark:/67531/metadc58498

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • November 28, 1950

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

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  • April 10, 2018, 2:41 p.m.

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Mahoney, John J.; Dugan, Paul D.; Budinger, Raymond E. & Goelzer, H. Fred. Investigation of blade-row flow distributions in axial-flow-compressor stage consisting of guide vanes and rotor-blade row, report, November 28, 1950; (digital.library.unt.edu/ark:/67531/metadc58498/: accessed June 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.