Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages

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"The performance of a 16-stage axial-flow compressor, in which two modifications of unloaded inlet stages were combined with loaded exit stages, has been determined. In the first modification the exit stages were loaded by decreasing the twelfth through fifteenth stage stator angles 3 deg. as compared with the blade angles in the original compressor, and the inlet stages were unloaded by increasing the blade angles the following amounts: guide vanes and first-stage stator, 6 deg; second- and third-stage stators, 4 deg.; and fourth-stage stators, 3 deg. The over-all performance of this configuration was compared with that of the compressor with ... continued below

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9 p.

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Hatch, James E. & Medeiros, Arthur A. March 17, 1952.

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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 33 times . More information about this report can be viewed below.

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  • Main Title: Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages
  • Series Title: NACA Research Memorandums

Description

"The performance of a 16-stage axial-flow compressor, in which two modifications of unloaded inlet stages were combined with loaded exit stages, has been determined. In the first modification the exit stages were loaded by decreasing the twelfth through fifteenth stage stator angles 3 deg. as compared with the blade angles in the original compressor, and the inlet stages were unloaded by increasing the blade angles the following amounts: guide vanes and first-stage stator, 6 deg; second- and third-stage stators, 4 deg.; and fourth-stage stators, 3 deg. The over-all performance of this configuration was compared with that of the compressor with the original blade angles" (p. 1).

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9 p.

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"IV."

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  • URL: http://hdl.handle.net/2060/20090025892 External Link
  • Report No.: NACA-RM-E53C14
  • Center for AeroSpace Information Number: 20090025892
  • Archival Resource Key: ark:/67531/metadc65426

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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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  • March 17, 1952

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • May 31, 2018, 5:25 p.m.

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Hatch, James E. & Medeiros, Arthur A. Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages, report, March 17, 1952; (digital.library.unt.edu/ark:/67531/metadc65426/: accessed December 11, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.