Investigation of Turbine-Outlet Temperature Distribution of XJ34-WE-32 Turbojet Engine

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Description

Turbine-outlet radial temperature distributions of an XJ34-WE-32 turbojet engine were investigated in the altitude wind tunnel at the NACA Lewis laboratory over a range of pressure altitudes, engine-inlet air temperatures and flight Mach numbers at or near rated engine conditions. From blade stress considerations, the turbine-outlet temperature distribution was considered satisfactory at altitudes up to 25,000 feet at corrected engine speeds corresponding to rated speed (12,500 rpm); however, operation at either higher corrected engine speeds or higher altitudes resulted in an inversion of the turbine temperature distribution that was detrimental to turbine life. Installation of a compressor-outlet mixer greatly improved ... continued below

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Prince, W R & Wintler, J T November 7, 1951.

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

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  • Main Title: Investigation of Turbine-Outlet Temperature Distribution of XJ34-WE-32 Turbojet Engine
  • Series Title: NACA Research Memorandums

Description

Turbine-outlet radial temperature distributions of an XJ34-WE-32 turbojet engine were investigated in the altitude wind tunnel at the NACA Lewis laboratory over a range of pressure altitudes, engine-inlet air temperatures and flight Mach numbers at or near rated engine conditions. From blade stress considerations, the turbine-outlet temperature distribution was considered satisfactory at altitudes up to 25,000 feet at corrected engine speeds corresponding to rated speed (12,500 rpm); however, operation at either higher corrected engine speeds or higher altitudes resulted in an inversion of the turbine temperature distribution that was detrimental to turbine life. Installation of a compressor-outlet mixer greatly improved the turbine radial temperature distribution.

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  • : 93R23307
  • URL: http://hdl.handle.net/2060/19930094388 External Link
  • Report No.: NACA-RM-E51K06
  • Center for AeroSpace Information Number: 19930094388
  • Archival Resource Key: ark:/67531/metadc63071

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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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  • November 7, 1951

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 31, 2017, 11:56 a.m.

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Prince, W R & Wintler, J T. Investigation of Turbine-Outlet Temperature Distribution of XJ34-WE-32 Turbojet Engine, report, November 7, 1951; (digital.library.unt.edu/ark:/67531/metadc63071/: accessed December 13, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.