Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles, II, Efficiency with 20 Degrees-Inlet-Angle Rotor Blades

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A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated. The maximum blade efficiency of 0.571 ... continued below

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Schum, Harold J. & Whitney, Warren J. August 25, 1949.

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

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  • Main Title: Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles, II, Efficiency with 20 Degrees-Inlet-Angle Rotor Blades
  • Series Title: NACA Research Memorandums

Description

A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated. The maximum blade efficiency of 0.571 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.296. The difference in blade efficiency was negligible at a pressure ratio of 8 at the low speeds; the maxim difference was 0.040 at a pressure ratio of 20 and a blade-jet speed ratio of 0.260.

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  • URL: http://hdl.handle.net/2060/20050019363 External Link
  • Report No.: NACA-RM-SE9H09
  • Center for AeroSpace Information Number: 20050019363
  • Archival Resource Key: ark:/67531/metadc64236

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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

  • August 25, 1949

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Dec. 20, 2017, 3:50 p.m.

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Schum, Harold J. & Whitney, Warren J. Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles, II, Efficiency with 20 Degrees-Inlet-Angle Rotor Blades, report, August 25, 1949; (digital.library.unt.edu/ark:/67531/metadc64236/: accessed September 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.