Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine

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Description

The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage ... continued below

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Schurn, Harold J. July 11, 1957.

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  • Main Title: Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine
  • Series Title: NACA Research Memorandums

Description

The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage so that the first stage of the unit could be operated independently. The modified single-stage turbine was then operated over a range of stage pressure ratio and speed. The single-stage turbine operated at a peak brake internal efficiency of over 90 percent at an over-all stage pressure ratio of 1.4 and at 90 percent of design equivalent speed. Furthermore, the unit operated at high efficiencies over a relatively wide operating range. When the single-stage results were compared with the multistage results at the design operating point, it was found that the first stage produced approximately half the total multistage-turbine work output.

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  • URL: http://hdl.handle.net/2060/20050019426 External Link
  • Report No.: NACA-RM-E53L28A
  • Center for AeroSpace Information Number: 20050019426
  • Archival Resource Key: ark:/67531/metadc64338

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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 11, 1957

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 30, 2017, 1:48 p.m.

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Schurn, Harold J. Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine, report, July 11, 1957; (digital.library.unt.edu/ark:/67531/metadc64338/: accessed September 23, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.