Performance of Compressor of XJ-41-V Turbojet Engine VI - Analysis of Compressor Flow Choking, 6, Analysis of Compressor Flow Choking

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An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-v turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow area was utilized in the original compressor and 94percent in the revised com$ressor. The increase in maximum weight flow obtained with the revised compressor was disproportionate ... continued below

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Creagh, John W. R. & Ginsburg, Ambrose March 23, 1948.

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  • Main Title: Performance of Compressor of XJ-41-V Turbojet Engine VI - Analysis of Compressor Flow Choking, 6, Analysis of Compressor Flow Choking
  • Series Title: NACA Research Memorandums

Description

An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-v turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow area was utilized in the original compressor and 94percent in the revised com$ressor. The increase in maximum weight flow obtained with the revised compressor was disproportionate to the increased effective critical throat area because. the air density at the revised vaned-collector entrance for maximum flow was lower than that obtained in the original compressor. This reduction in density resulted from the large pressure losses near the impeller inlet of the revised compressor, which is indicative of impending flow choking in the impeller, The.calculated maximum corrected weight-flow capacity of a compressor consisting of the revised vaneless diffuser and vaned collector with a theoretical impeller that combined peak impeller pressure ratio and peak impeller efficiency at the . maximum flow point would be 112 pounds per second for an equivalent impeller speed of 11,500 rpm;.

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  • URL: http://hdl.handle.net/2060/20090011946 External Link
  • Report No.: NACA-RM-SE8C12
  • Center for AeroSpace Information Number: 20090011946
  • Archival Resource Key: ark:/67531/metadc64998

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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 23, 1948

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 30, 2017, 1:53 p.m.

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Creagh, John W. R. & Ginsburg, Ambrose. Performance of Compressor of XJ-41-V Turbojet Engine VI - Analysis of Compressor Flow Choking, 6, Analysis of Compressor Flow Choking, report, March 23, 1948; (digital.library.unt.edu/ark:/67531/metadc64998/: accessed June 23, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.