Performance of J33-A-23 Turbojet-Engine Compressor, Part 1, Over-All Performance Characteristics of Compressor with 17-Blade Impeller

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The production-model 333-A-23 turbojet-engine compressor with a 17-blade impeller was operated at ambient and 0 F inlet temperatures and at inlet pressures of 14 and 5 inches mercury absolute for equivalent impeller speeds from 6000 to 12,750 rpm. The results of this investigation are compared with those of the 533-A-21 compressor. At the design equivalent speed of 11,750 rpm the maximum pressure ratio was 4.39. This occurred at the surge point at which the equivalent weight flow was 80.8 pounds per second, ana the adiabatic temperature-rise efficiency was 0.757. The maximum flow at the design equivalent speed was 88.0 pounds ... continued below

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Beede, William L. & Kottas, Harry July 20, 1948.

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

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  • Main Title: Performance of J33-A-23 Turbojet-Engine Compressor, Part 1, Over-All Performance Characteristics of Compressor with 17-Blade Impeller
  • Series Title: NACA Research Memorandums

Description

The production-model 333-A-23 turbojet-engine compressor with a 17-blade impeller was operated at ambient and 0 F inlet temperatures and at inlet pressures of 14 and 5 inches mercury absolute for equivalent impeller speeds from 6000 to 12,750 rpm. The results of this investigation are compared with those of the 533-A-21 compressor. At the design equivalent speed of 11,750 rpm the maximum pressure ratio was 4.39. This occurred at the surge point at which the equivalent weight flow was 80.8 pounds per second, ana the adiabatic temperature-rise efficiency was 0.757. The maximum flow at the design equivalent speed was 88.0 pounds per second. The maximum adiabatic temperature-rise efficiency of 0.799 was obtained at an equivalent speed of 10,000 rpm, and equivalent weight flow of 62.9 pounds per second, and a pressure ratio of 3.20. At the maximum equivalent speed investigated (12,750 rpm), a peak pressure ratio of 4.90 was attained at an equivalent weight flow of 85.4 pounds per second and an efficiency of 0.680.

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  • URL: http://hdl.handle.net/2060/20050019250 External Link
  • Report No.: NACA-RM-SE8F15-Pt-1
  • Center for AeroSpace Information Number: 20050019250
  • Archival Resource Key: ark:/67531/metadc64097

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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

  • July 20, 1948

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 30, 2017, 2:08 p.m.

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Beede, William L. & Kottas, Harry. Performance of J33-A-23 Turbojet-Engine Compressor, Part 1, Over-All Performance Characteristics of Compressor with 17-Blade Impeller, report, July 20, 1948; (digital.library.unt.edu/ark:/67531/metadc64097/: accessed May 26, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.