Item Details

Design and Experimental Results for a Turbine With Jet Flap Stator and Jet Flap

by James L. Bettner and Jerry O. Blessing
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1973.
Language
English
Series
NASA Contractor Report
Summary
The overall performance and detailed stator performance of a negative hub reaction turbine design featuring a moderately low solidity jet flap stator and a jet flap rotor were determined. Testing was conducted over a range of turbine expansion ratios at design speed. At each expansion ratio, the stator jet flow and rotor jet flow ranged up to about 7 and 8 percent, respectively, of the turbine inlet flow. The performance of the jet flap stator/jet flap rotor turbine was compared with that of a turbine which used the same jet flap rotor and a conventional, high solidity plan stator. The effect on performance of increased axial spacing between the jet stator and rotor was also investigated.
Description
xi, 154 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2244."
  • Performing organization report no.: EDR 7389.
  • "May 1973."
  • Cover title.
  • Includes bibliographical references (p. 44-45).
Series Statement
NASA contractor report ; NASA CR-2244
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Bettner, James L.
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    a| Design and experimental results for a turbine with jet flap stator and jet flap / c| by James L. Bettner and Jerry O. Blessing.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1973.
    300
      
      
    a| xi, 154 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2244
    500
      
      
    a| "NASA CR-2244."
    500
      
      
    a| Performing organization report no.: EDR 7389.
    500
      
      
    a| "May 1973."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 44-45).
    520
      
      
    a| The overall performance and detailed stator performance of a negative hub reaction turbine design featuring a moderately low solidity jet flap stator and a jet flap rotor were determined. Testing was conducted over a range of turbine expansion ratios at design speed. At each expansion ratio, the stator jet flow and rotor jet flow ranged up to about 7 and 8 percent, respectively, of the turbine inlet flow. The performance of the jet flap stator/jet flap rotor turbine was compared with that of a turbine which used the same jet flap rotor and a conventional, high solidity plan stator. The effect on performance of increased axial spacing between the jet stator and rotor was also investigated.
    536
      
      
    a| Prepared by General Motors Corporation, Indianapolis, Ind. for Lewis Research Center b| NAS 3-14303
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Variable geometry structures. 2| nasat
    650
      
    7
    a| Stators. 2| nasat
    650
      
    7
    a| Rotors. 2| nasat
    650
      
    7
    a| Performance tests. 2| nasat
    650
      
    7
    a| Inlet flow. 2| nasat
    650
      
    7
    a| Turbine blades. 2| nasat
    650
      
    7
    a| Jet flaps. 2| nasat
    650
      
    7
    a| Aerodynamic characteristics. 2| nasat
    700
    1
      
    a| Blessing, Jerry O.
    710
    2
      
    a| Lewis Research Center.
    710
    2
      
    a| General Motors Corporation.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106860874 y| 1973 r| pd q| bib

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