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Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade at Low Inlet TurbulenceAerodynamic measurements obtained in a transonic linear cascade were used to assess the impact of large incidence angle and Reynolds number variations on the 3-D flow field and midspan loss and turning of a 2-D section of a variable-speed power-turbine (VSPT) rotor blade. Steady-state data were obtained for ten incidence angles ranging from +15.8 deg to −51.0 deg. At each angle, data were acquired at five flow conditions with the exit Reynolds number (based on axial chord) varying over an order-of-magnitude from 2.12×10(exp 5) to 2.12×10(exp 6). Data were obtained at the design exit Mach number of 0.72 and at a reduced exit Mach number of 0.35 as required to achieve the lowest Reynolds number. Midspan total-pressure and exit flow angle data were acquired using a five-hole pitch/yaw probe surveyed on a plane located 7.0 percent axial chord downstream of the blade trailing edge plane. The survey spanned three blade passages. Additionally, three-dimensional half-span flow fields were examined with additional probe survey data acquired at 26 span locations for two key incidence angles of +5.8 deg and −36.7 deg. Survey data near the endwall were acquired with a three-hole boundary-layer probe. The data were integrated to determine average exit total-pressure and flow angle as functions of incidence and flow conditions. The data set also includes blade static pressures measured on four spanwise planes and endwall static pressures. Tests were conducted in the NASA Glenn Transonic Turbine Blade Cascade Facility. The measurements reflect strong secondary flows associated with the high aerodynamic loading levels at large positive incidence angles and an increase in loss levels with decreasing Reynolds number. The secondary flows decrease with negative incidence as the blade becomes unloaded. Transitional flow is admitted in this low inlet turbulence dataset, making it a challenging CFD test case. The dataset will be used to advance understanding of the aerodynamic challenges associated with maintaining efficient power turbine operation over a wide shaft-speed range. deg
Document ID
20140002506
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Flegel-McVetta, Ashlie B. (NASA Glenn Research Center Cleveland, OH, United States)
Giel, Paul W. (Vantage Partners, LLC Brook Park, OH, United States)
Welch, Gerard E. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
March 31, 2014
Publication Date
August 1, 2013
Subject Category
Aerodynamics
Report/Patent Number
GT2013-94695
E-18745
NASA/TM-2013-218069
Meeting Information
Meeting: ASME Turbo Expo 2013
Location: San Antonio, TX
Country: United States
Start Date: June 3, 2013
End Date: June 7, 2013
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
CONTRACT_GRANT: NNC06E03lT
WBS: WBS 877868.02.07.03.01.02.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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