An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

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Description

From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region ... continued below

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68 p. : ill.

Creation Information

Esgar, Jack B September 8, 1952.

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

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  • Main Title: An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades
  • Series Title: NACA Research Memorandums

Description

From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region of the blade, there are very large variations in the chordwise temperature distribution because of improper permeability variation."

Physical Description

68 p. : ill.

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  • : 93R16518
  • URL: http://hdl.handle.net/2060/19930087228 External Link
  • Report No.: NACA-RM-E52G01
  • Center for AeroSpace Information Number: 19930087228
  • Archival Resource Key: ark:/67531/metadc59331

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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).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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Creation Date

  • September 8, 1952

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • Aug. 16, 2017, 11:52 a.m.

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Citations, Rights, Re-Use

Esgar, Jack B. An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades, report, September 8, 1952; (digital.library.unt.edu/ark:/67531/metadc59331/: accessed October 17, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.