Investigation of two-stage air-cooled turbine suitable for flight at Mach number of 2.5 2: blade design

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

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Description

A blade design study is presented for a two-stage air-cooled turbine suitable for flight at a Mach number of 2.5 for which velocity diagrams have been previously obtained. The detailed procedure used in the design of the blades is given. In addition, the design blade shapes, surface velocity distributions, inner and outer wall contours, and other design data are presented. Of all the blade rows, the first-stage rotor has the highest solidity, with a value of 2.289 at the mean section. The second-stage stator also had a high mean-section solidity of 1.927, mainly because of its high inlet whirl. The ... continued below

Physical Description

37 p. : ill.

Creation Information

Miser, James W. & Stewart, Warner L. January 22, 1957.

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

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  • Main Title: Investigation of two-stage air-cooled turbine suitable for flight at Mach number of 2.5 2: blade design
  • Series Title: NACA Research Memorandums

Description

A blade design study is presented for a two-stage air-cooled turbine suitable for flight at a Mach number of 2.5 for which velocity diagrams have been previously obtained. The detailed procedure used in the design of the blades is given. In addition, the design blade shapes, surface velocity distributions, inner and outer wall contours, and other design data are presented. Of all the blade rows, the first-stage rotor has the highest solidity, with a value of 2.289 at the mean section. The second-stage stator also had a high mean-section solidity of 1.927, mainly because of its high inlet whirl. The second-stage rotor has the highest value of the suction-surface diffusion parameter, with a value of 0.151. All other blade rows have values for this parameter under 0.100.

Physical Description

37 p. : ill.

Notes

"II."

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  • Accession or Local Control No: 93R23076
  • URL: http://hdl.handle.net/2060/19930093766 External Link
  • Report No.: NACA-RM-E56K06
  • Center for AeroSpace Information Number: 19930093766
  • Archival Resource Key: ark:/67531/metadc62782

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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

  • January 22, 1957

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

Description Last Updated

  • April 24, 2018, 10:38 a.m.

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Miser, James W. & Stewart, Warner L. Investigation of two-stage air-cooled turbine suitable for flight at Mach number of 2.5 2: blade design, report, January 22, 1957; (digital.library.unt.edu/ark:/67531/metadc62782/: accessed July 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.