Research Papers

Experimental Heat Transfer Investigation of an Aggressive Intermediate Turbine Duct

[+] Author and Article Information
Carlos Arroyo Osso

Volvo Aero Corporation,Trollhättan, Sweden;  Chalmers University of Technology, Göteborg, Sweden

T. Gunnar Johansson

 Chalmers University of Technology, Göteborg, Sweden

Fredrik Wallin

Volvo Aero Corporation, Trollhättan, Sweden

Nusselt number correlation for a turbulent boundary layer on a flat plate with constant temperature: Nux=0.0296Re0.8Pr1/3, from Incropera [17].

J. Turbomach 134(5), 051026 (May 24, 2012) (10 pages) doi:10.1115/1.4004779 History: Received May 06, 2011; Revised July 28, 2011; Published May 24, 2012; Online May 24, 2012

In most designs of two-spool turbofan engines, intermediate turbine ducts (ITDs) are used to connect the high-pressure turbine (HPT) with the low-pressure turbine (LPT). Demands for more efficient engines with reduced emissions require more “aggressive ducts,” ducts which provide both a higher radial offset and a larger area ratio in the shortest possible length, while maintaining low pressure losses and avoiding nonuniformities in the outlet flow that might affect the performance of the downstream LPT. The work presented in this paper is part of a more comprehensive experimental and computational study of the flowfield and the heat transfer in an aggressive ITD. The main objectives of the study were to obtain an understanding of the mechanisms governing the heat transfer in ITDs and to obtain high quality experimental data for the improvement of the CFD-based design tools. This paper presents and discusses the results of the experimental study. The duct studied was a state-of-the-art “aggressive” design with nine thick nonturning structural struts. It was tested in a large-scale low-speed experimental facility with a single-stage HPT. In this paper measurements of the steady convective heat transfer coefficient (HTC) distribution on both endwalls and on the strut for the duct design inlet conditions are presented. The heat transfer measurement technique used is based on infrared thermography. Part of the results of the flow measurements is also included.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Layout of the core of the experimental facility

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Figure 2

Intermediate turbine duct showing the planes for the 5-hole probe measurements

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Figure 3

One-dimensional heat transfer model

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Figure 4

View of the hub heated element. For the shroud a similar arrangement was used.

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Figure 5

View of the strut used for the heat transfer experiments. (Picture on the right shows the strut before the black coating and the markers were applied.)

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Figure 6

General layout of the heat transfer experiment

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Figure 7

Relative axial velocity at planes 2, 4, and 6

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Figure 8

Swirl angle at planes 2, 4, and 6

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Figure 9

Axial vorticity at planes 2, 4, and 6

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Figure 10

Circumferentially averaged heat transfer coefficient on the endwalls for the design case

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Figure 11

Detail of the HTC streaks on the hub

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Figure 12

Heat transfer coefficient distribution in the duct

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Figure 13

Relative variation of the heat transfer coefficient respect to the circumferential average

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Figure 14

Heat transfer coefficient on the strut

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Figure 15

Heat transfer coefficient on the strut at 10%, 50%, and 90% of the span

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Figure 16

Measurement relative uncertainty for the endwalls




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