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Experimental and Numerical Investigation of Losses in Low-Pressure Turbine Blade RowsExperimental data and numerical simulations of low-pressure turbines have shown that unsteady blade row interactions and separation can have a significant impact on the turbine efficiency. Measured turbine efficiencies at takeoff can be as much as two points higher than those at cruise conditions. Several recent studies have revealed that the performance of low-pressure turbine blades is a strong function of the Reynolds number. In the current investigation, experiments and simulations have been performed to study the behavior of a low-pressure turbine blade at several Reynolds numbers. Both the predicted and experimental results indicate increased cascade losses as the Reynolds number is reduced to the values associated with aircraft cruise conditions. In addition, both sets of data show that tripping the boundary layer helps reduce the losses at lower Reynolds numbers. Overall, the predicted aerodynamic and performance results exhibit fair agreement with experimental data.
Document ID
20000021567
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Dorney, Daniel J. (Virginia Commonwealth Univ. Richmond, VA, United States)
Lake, James P. (Air Force Research Lab. Edwards AFB, CA, United States)
King, Paul I. (Air Force Inst. of Tech. Wright-Patterson AFB, OH, United States)
Ashpis, David E. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2000-0737
NAS 1.15:209910
E-12137
NASA/TM-2000-209910
Meeting Information
Meeting: 38th Aerospace Science Meeting
Location: Reno, NV
Country: United States
Start Date: January 10, 2000
End Date: January 13, 2000
Funding Number(s)
PROJECT: RTOP 523-26-33
CONTRACT_GRANT: NCC3-645
Distribution Limits
Public
Copyright
Public Use Permitted.

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