Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles, III, Efficiency with Standard Rotor Blades

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Description

A Mark 25 torpedo power plant modified to operate as a single-stage turbine was investigated to determine the performance with two nozzle designs and a standard first-stage rotor having 0.40-inch blades with a 17O met-air angle. Both nozzles had smaller port cross-sectional areas than those nozzles of similar design, which were previously investigated. The performance of the two nozzles was compared on the basis of blade, rotor, and brake efficiencies as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. At pressure ratios of 15 and 20, the blade efficiency obtained with the nozzle ... continued below

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Schum, Harold J. & Whitney, Warren J. January 1, 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 76 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, III, Efficiency with Standard Rotor Blades
  • Series Title: NACA Research Memorandums

Description

A Mark 25 torpedo power plant modified to operate as a single-stage turbine was investigated to determine the performance with two nozzle designs and a standard first-stage rotor having 0.40-inch blades with a 17O met-air angle. Both nozzles had smaller port cross-sectional areas than those nozzles of similar design, which were previously investigated. The performance of the two nozzles was compared on the basis of blade, rotor, and brake efficiencies as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. At pressure ratios of 15 and 20, the blade efficiency obtained with the nozzle having circular passages (K) was higher than that obtained with the nozzle having rectangular passages (J). At a pressure ratio of 8, the efficiencies obtained with the two nozzles were comparable for blade-jet speed ratios of less than 0.260. For blade-jet speed ratios exceeding this value, nozzle K yielded slightly higher efficiencies. The maximum blade efficiency of 0.569 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. At design speed and pressure ratio, nozzle K yielded a maximum blade efficiency of 0.534, an increase of 0.031 over that obtained with nozzle J. When the blade efficiencies of the two nozzles were compared with those of four other nozzles previously investigated, the maximum difference for the six nozzles with this rotor was 0.050. From, this comparison, no specific effect of nozzles size or shape on over-all performance was discernible.

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  • URL: http://hdl.handle.net/2060/20050019612 External Link
  • Report No.: NACA-RM-SE9H30
  • Center for AeroSpace Information Number: 20050019612
  • Archival Resource Key: ark:/67531/metadc64457

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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 1, 1949

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Dec. 20, 2017, 3:51 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, III, Efficiency with Standard Rotor Blades, report, January 1, 1949; (digital.library.unt.edu/ark:/67531/metadc64457/: accessed October 19, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.