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Analysis of Laminar-Turbulent Transition of a Low-Loss Generic Low Pressure Turbine Distribution
Citation key 2015_brueck_asme
Author Brück, C. and Lyko, C. and Peitsch, D. and Bode, C. and Friedrichs, J. and Kožulović, D. and Fiala, A. and Guendogdu, Y.
Pages GT2015-42824
Year 2015
ISBN 978-0-7918-5663-5
DOI 10.1115/GT2015-42824
Location Montreal, Quebec, Canada
Journal ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
Volume Volume 2A: Turbomachinery
Month 06
Note V02AT38A019,
Technische Universität Berlin:
C. Brück, C. Lyko, D. Peitsch
Technische Universität Braunschweig:
C. Bode, J. Friedrichs
Hochschule für Angewandte Wissenschaften Hamburg:
D. Kozulovic
MTU Aero-Engines AG, München:
A. Fiala, Y. Guendogdu
Editor ASME
Series Turbo Expo: Power for Land, Sea, and Air
Abstract The efficiency of modern Turbofan engines can be significantly increased by using a gearbox between compressor and turbine of the low pressure section. Rotational speed of the low pressure turbine (LPT) in a Geared Turbofan is much higher than in normal LPT’s which lead to necessary adjustments in blade design.This work has investigated the transition behavior of a modified profile geometry for low-loss at engine cruise conditions. Typical LPT conditions have thus been chosen as baseline for the experimental work. A pressure distribution has been created on a flat plate by means of contoured walls in a low speed wind tunnel. The paper will analyze the experimental results and show additionally the numerical predictions of the test case.The experimental part of this paper describe how the blade was Mach number scaled to obtain the geometry of the wind tunnel wall contour. The pressure distribution for the incompressible test case show a very good agreement to the compressible case. Boundary layer (BL) measurements with hot-wire-anemometry have been performed at high spatial resolution under a freestream turbulence of almost 8\\%. Different Reynolds numbers have been investigated and will be compared with special attention being paid to the transition on the suction side by contour plots (turbulence levels, turbulent intermittency) and integral BL parameters. It was found that the transition on the suction side is not completed for small Reynolds numbers but takes place at higher velocities.In the numerical part studies by means of steady RANS simulations with k-ω – SST turbulence model and γ-Reθ transition model have been conducted. The aim is to validate the RANS solver for the low-loss LPT application. Hence, comparison is made to the measured data and the transitional behavior of the BL. Furthermore, additional parameter variations have been conducted (turbulence intensity and Reynolds number).The numerical investigations show partially a good comparison for the BL development indicating the different transition modi with increasing Reynolds number and turbulence intensity.
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