TY - GEN
T1 - The design of a steady aero thermal research turbine (START) for studying secondary flow leakages and airfoil heat transfer
AU - Barringer, Michael
AU - Coward, Andrew
AU - Clark, Ken
AU - Thole, Karen A.
AU - Schmitz, John
AU - Wagner, Joel
AU - Alvin, Mary Anne
AU - Burke, Patcharin
AU - Dennis, Rich
N1 - Publisher Copyright:
Copyright © 2014 by ASME.
PY - 2014
Y1 - 2014
N2 - This paper describes a new gas turbine research facility that was designed and is currently being constructed with a number of unique features that allow experiments which aim at developing and improving sealing and cooling technologies at a reasonable cost. Experiments will include enginerepresentative rotating turbine hardware in a continuous, steady-state, high-pressure flow environment. The facility includes a 1.5 stage turbine that will simulate the aerodynamic flow and thermal field interactions in the engine between the hot mainstream gas path and the secondary air flows at relevant corrected operating conditions and scaling parameters. Testing in the new facility is planned to begin in 2014 and will take place in two phases. The first phase is focused on understanding the behavior of inner-stage gap flow leakages in the presence of the main gas path and the rotating blade platform. The second phase is focused on developing and testing novel cooling methods for turbine airfoils, platforms, and disks, ultimately leading to an integrated approach for more effective use of the secondary cooling flow. The uniqueness of this facility includes a continuous duration facility with engine-relevant rotational and axial Reynolds and Mach numbers at the blade inlet.
AB - This paper describes a new gas turbine research facility that was designed and is currently being constructed with a number of unique features that allow experiments which aim at developing and improving sealing and cooling technologies at a reasonable cost. Experiments will include enginerepresentative rotating turbine hardware in a continuous, steady-state, high-pressure flow environment. The facility includes a 1.5 stage turbine that will simulate the aerodynamic flow and thermal field interactions in the engine between the hot mainstream gas path and the secondary air flows at relevant corrected operating conditions and scaling parameters. Testing in the new facility is planned to begin in 2014 and will take place in two phases. The first phase is focused on understanding the behavior of inner-stage gap flow leakages in the presence of the main gas path and the rotating blade platform. The second phase is focused on developing and testing novel cooling methods for turbine airfoils, platforms, and disks, ultimately leading to an integrated approach for more effective use of the secondary cooling flow. The uniqueness of this facility includes a continuous duration facility with engine-relevant rotational and axial Reynolds and Mach numbers at the blade inlet.
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U2 - 10.1115/GT2014-25570
DO - 10.1115/GT2014-25570
M3 - Conference contribution
AN - SCOPUS:84961362656
T3 - Proceedings of the ASME Turbo Expo
BT - Heat Transfer
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014
Y2 - 16 June 2014 through 20 June 2014
ER -