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Study of Boundary Layer Development in a Two-Stage Low-Pressure TurbineExperimental data from jet-engine tests have indicated that unsteady blade row interactions and separation can have a significant impact on the efficiency of low-pressure turbine stages. Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Several recent studies have revealed that Reynolds number effects may contribute to the lower efficiencies at cruise conditions. In the current study numerical simulations have been performed to study the boundary layer development in a two-stage low-pressure turbine, and to evaluate the transition models available for low Reynolds number flows in turbomachinery. The results of the simulations have been compared with experimental data, including airfoil loadings and integral boundary layer quantities. The predicted unsteady results display similar trends to the experimental data, but significantly overestimate the amplitude of the unsteadiness. The time-averaged results show close agreement with the experimental data.
Document ID
19990019324
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Dorney, Daniel J.
(Virginia Commonwealth Univ. Richmond, VA United States)
Ashpis, David E.
(NASA Lewis Research Center Cleveland,OH United States)
Halstead, David E.
(General Electric Co. Cincinnati, OH United States)
Wisler, David C.
(General Electric Co. Cincinnati, OH United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1999
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-1999-208913
AIAA Paper 99-0742
NAS 1.15:208913
E-11544
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 11, 1999
End Date: January 14, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 523-26-33
CONTRACT_GRANT: NCC3-645
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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