Research Papers

Low Pressure Turbine Secondary Vortices: Reynolds Lapse

[+] Author and Article Information
Matthias Kuerner

Georg A. Reichstein1

Daniel Schrack, Martin G. Rose, Stephan Staudacher

 Institute of Aircraft Propulsion Systems, Stuttgart University,Pfaffenwaldring 6, D-70569 Stuttgart, Germany

Jochen Gier, Karl Engel

MTU Aero Engines GmbH,Dachauer Strasse 665, D-80995 Munich, Germany


Corresponding author.

J. Turbomach 134(6), 061022 (Sep 04, 2012) (7 pages) doi:10.1115/1.4006299 History: Received July 12, 2011; Revised July 25, 2011; Published September 04, 2012; Online September 04, 2012

A two-stage turbine is tested in a cooperation between the Institute of Aircraft Propulsion Systems (ILA) and MTU Aero Engines GmbH (MTU). The experimental results taken in the Altitude Test Facility (ATF) are used to assess the impact of cavity flow and leakage on vortex structures. The analysis focuses on a range of small Reynolds numbers, from as low as 35,000 up to 88,000. The five hole probe area traverse data is compared to steady multistage CFD predictions behind the second vane. The numerical model compares computations without and with cavities modeled. The simulation with cavities is superior to the approach without cavities. The vortex induced blockage is found to be inversely proportional to the Reynolds number. The circulation of the vortices is dependent on the Reynolds number showing a reversing trend to the smallest Reynolds numbers. The steady numerical model as of yet is unsuitable to predict these trends. A first unsteady simulation suggests major improvements.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Meridional view of the ATRD-Rig as numerically modeled. Cavities (not included for ideal annulus analysis) are shaded.

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Figure 2

Isentropic efficiency ηis versus Reynolds number of vane 2 ReV2

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Figure 3

Blade row efficiency ηrow at the lowest Reynolds number, ReV2  = 35,000. Experimental data shown with traverse grid and frame indicating annulus position. Position of trailing edge is marked for all cases.

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Figure 4

(a) Circumferential blockage factor over relative height; ReV2  = 35k; (-··) marks regions of analysis. (b)-(d) Normalized circumferential blockage factor ιover Reynolds number of vane 2 ReV2 . Values are relative to the respective CBF at the highest Reynolds number. (- -)indicates turbulent estimate Re−0.5 ; (-·) indicates laminar estimate Re−0.2 .

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Figure 5

Boundaries of the control volumes (black circles) used to evaluate axial circulation

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Figure 6

Circulation Γ over Reynolds number of vane 2 ReV2




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