Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

One of 5,163 reports in the series: NACA Research Memorandums available on this site.

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Description

Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow. For any fixed value of coolant flow ratio the percentage thrust reduction and percentage increase in specific fuel consumption decreased with ... continued below

Physical Description

24 p. : ill.

Creation Information

Arne, Vernon L. & Nachtigall, Alfred J. August 13, 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 280 times . More information about this report can be viewed below.

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  • Main Title: Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine
  • Series Title: NACA Research Memorandums

Description

Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow. For any fixed value of coolant flow ratio the percentage thrust reduction and percentage increase in specific fuel consumption decreased with altitude. Bleeding coolant at the compressor discharge resulted in an additional 1 percent loss in performance at sea level and in smaller increase in loss of performance at higher altitudes.

Physical Description

24 p. : ill.

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  • Accession or Local Control No: 93R16011
  • URL: http://hdl.handle.net/2060/19930086721 External Link
  • Report No.: NACA-RM-E51E24
  • Center for AeroSpace Information Number: 19930086721
  • Archival Resource Key: ark:/67531/metadc58909

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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

  • August 13, 1951

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

Description Last Updated

  • May 31, 2018, 4:50 p.m.

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Arne, Vernon L. & Nachtigall, Alfred J. Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine, report, August 13, 1951; (digital.library.unt.edu/ark:/67531/metadc58909/: accessed July 15, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.