Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet

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Description

From Summary: "An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area."

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21 p. : ill.

Creation Information

Rebeske, John J., Jr. & Rohlik, Harold E. March 10, 1953.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided by the UNT Libraries Government Documents Department to the UNT Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 1339 times. More information about this report can be viewed below.

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  • Main Title: Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet
  • Series Title: NACA Research Memorandums

Description

From Summary: "An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area."

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21 p. : ill.

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"I."

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  • Accession or Local Control No: 93R16756
  • URL: http://hdl.handle.net/2060/19930087466 External Link
  • Report No.: NACA-RM-E53A09
  • Center for AeroSpace Information Number: 19930087466
  • Archival Resource Key: ark:/67531/metadc59518

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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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  • March 10, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

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  • April 11, 2018, 11:09 a.m.

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Rebeske, John J., Jr. & Rohlik, Harold E. Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet, report, March 10, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59518/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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