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Design and experimental results for a turbine with jet flap stator and jet flapThe 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.
Document ID
19730015309
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bettner, J. L. (General Motors Corp. Indianapolis, IN, United States)
Blessing, J. O. (General Motors Corp. Indianapolis, IN, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2244
EDR-7389
Accession Number
73N24036
Funding Number(s)
CONTRACT_GRANT: NAS3-14303
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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