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Research Papers

Transonic Turbine Stage Heat Transfer Investigation in Presence of Strong Shocks

[+] Author and Article Information
A. de la Loma, G. Paniagua, D. Verrastro

Turbomachinery and Propulsion Department,  von Karman Institute, Rhode Saint Genèse B1640, Belgium

P. Adami

Energy Department “Sergio Stecco,”  University of Florence, Florence 50139, Italy

J. Turbomach 130(3), 031019 (May 06, 2008) (8 pages) doi:10.1115/1.2777193 History: Received May 21, 2007; Revised May 27, 2007; Published May 06, 2008

This paper reports the external convective heat transfer distribution of a modern single-stage transonic turbine together with the physical interpretation of the different shock interaction mechanisms. The measurements have been performed in the compression tube test rig of the von Karman Institute using single- and double-layered thin film gauges. The three pressure ratios tested are representative of those encountered in actual aeroengines, with M2,is ranging from 1.07 to 1.25 and a Reynolds number of about 106. Three different rotor blade heights (15%, 50%, and 85%) and the stator blade at midspan have been investigated. The measurements highlight the destabilizing effect of the vane left-running shock on the rotor boundary layer. The stator unsteady heat transfer is dominated by the fluctuating right-running vane trailing edge shock at the blade passing frequency.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Vane and rotor blades instrumented

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Figure 2

(Left) Blade to blade view of the stage and (right) detail of the structured grid close to the airfoil

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Figure 3

Vane Mach and Nusselt number distributions

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Figure 4

(a) Time-averaged isopressure lines at low-pressure ratio, (b) Time-averaged isopressure lines at high-pressure ratio, and (c) instantaneous shock interaction at two time steps

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Figure 5

FFT analysis of gauges mounted in the vane

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Figure 6

Vane unsteady heat transfer and shock patterns present in the vane-rotor gap

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Figure 7

Nusselt number and M2r,is at midspan for three pressure ratios

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Figure 8

FFT analysis of gauges mounted in the rotor blade

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Figure 9

Effect of the pressure ratio on the unsteady heat transfer

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Figure 10

Effect of the blade height at nominal pressure ratio

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Figure 11

Shock schematic, fluctuations in Gauges 14 and 5 in phase

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Figure 12

Shock pattern comparison at three different blade heights

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