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Highly loaded multi-stage fan drive turbine - performance of initial seven configurationsExperimental results of a three-stage highly loaded fan drive turbine test program are presented. A plain blade turbine, a tandem blade turbine, and a tangentially leaned stator turbine were designed for the same velocity diagram and flowpath. Seven combinations of bladerows were tested to evaluate stage performances and effects of the tandem blading and leaned stator. The plain blade turbine design point total-to-total efficiency was 0.886. The turbine with the stage three leaned stator had the same efficiency with an improved exit swirl profile and increased hub reaction. Two-stage group tests showed that the two-stage turbine with tandem stage two stator had an efficiency of 0.880 compared to 0.868 for the plain blade two-stage turbine.
Document ID
19740011283
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wolfmeyer, G. W. (General Electric Co. Cincinnati, OH, United States)
Thomas, M. W. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1974
Publication Information
Publisher: NASA
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-2362
R73AEG154
Accession Number
74N19396
Funding Number(s)
CONTRACT_GRANT: NAS3-14304
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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