Study of ram-air heat exchangers for reducing turbine cooling-air temperature of a supersonic aircraft turbojet engine

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

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The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude of 70,000 feet. A compressor-bleed-air weight flow of 2.7 pounds per second was assumed for the coolant; ram air was considered as the other fluid. Pressure drops and inlet states of both ... continued below

Physical Description

33 p. : ill.

Creation Information

Diaguila, Anthony J.; Livingood, John N. B. & Eckert, Ernst R. G. August 3, 1956.

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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 293 times , with 9 in the last month . More information about this report can be viewed below.

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  • Main Title: Study of ram-air heat exchangers for reducing turbine cooling-air temperature of a supersonic aircraft turbojet engine
  • Series Title: NACA Research Memorandums

Description

The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude of 70,000 feet. A compressor-bleed-air weight flow of 2.7 pounds per second was assumed for the coolant; ram air was considered as the other fluid. Pressure drops and inlet states of both fluids were prescribed, and ranges of compressor-bleed-air temperature reductions and of the ratio of compressor-bleed to ram-air weight flows were considered.

Physical Description

33 p. : ill.

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  • Accession or Local Control No: 93R18693
  • URL: http://hdl.handle.net/2060/19930089403 External Link
  • Report No.: NACA-RM-E56E17
  • Center for AeroSpace Information Number: 19930089403
  • Archival Resource Key: ark:/67531/metadc62770

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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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  • August 3, 1956

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

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  • May 17, 2018, 11:41 a.m.

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Diaguila, Anthony J.; Livingood, John N. B. & Eckert, Ernst R. G. Study of ram-air heat exchangers for reducing turbine cooling-air temperature of a supersonic aircraft turbojet engine, report, August 3, 1956; (digital.library.unt.edu/ark:/67531/metadc62770/: accessed June 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.