Component Performance Investigation of J71 Experimental Turbine, Part 2, Internal-Flow Conditions with 97-Percent-Design Stator Areas

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An experimental investigation of the internal-flow conditions of a J71 experimental turbine equipped with 97-percent-design stator areas was conducted at equivalent design speed and near equivalent design work. The results of the investigation indicate that the stage work distribution closely approximates design, the actual distribution being 44.1, 33.4, and 22.5 percent for the first, second, and third stages, respectively. The first-, second-, and third-stage efficiencies were 0.894, 0.858, and 0.792, respectively. The first and second stages exhibited loss regions near the hub and tip at the rotor blade outlets. The hub loss region is attributed to stator secondary flows, and ... continued below

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Rebeske, John J., Jr. & Petrash, Donald A. April 11, 1956.

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  • Main Title: Component Performance Investigation of J71 Experimental Turbine, Part 2, Internal-Flow Conditions with 97-Percent-Design Stator Areas
  • Series Title: NACA Research Memorandums

Description

An experimental investigation of the internal-flow conditions of a J71 experimental turbine equipped with 97-percent-design stator areas was conducted at equivalent design speed and near equivalent design work. The results of the investigation indicate that the stage work distribution closely approximates design, the actual distribution being 44.1, 33.4, and 22.5 percent for the first, second, and third stages, respectively. The first-, second-, and third-stage efficiencies were 0.894, 0.858, and 0.792, respectively. The first and second stages exhibited loss regions near the hub and tip at the rotor blade outlets. The hub loss region is attributed to stator secondary flows, and a contributing factor to the tip loss region may be the high design diffusion on the rotor blade suction surface near the tip. The loss in the third stage is appreciably greater than that in the first or second stage. The fact that the third rotor is unshrouded and has a nominal tip clearance of 0.120 inch may contribute to the higher loss in the tip region of the third stage.

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  • URL: http://hdl.handle.net/2060/20050041779 External Link
  • Report No.: NACA-RM-E54L16-Pt-2
  • Center for AeroSpace Information Number: 20050041779
  • Archival Resource Key: ark:/67531/metadc64869

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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

  • April 11, 1956

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 5, 2018, 11:27 a.m.

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Rebeske, John J., Jr. & Petrash, Donald A. Component Performance Investigation of J71 Experimental Turbine, Part 2, Internal-Flow Conditions with 97-Percent-Design Stator Areas, report, April 11, 1956; (digital.library.unt.edu/ark:/67531/metadc64869/: accessed August 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.