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Gas Turbines: Structures and Dynamics

Coupled Fluid-Structure Transient Thermal Analysis of a Gas Turbine Internal Air System With Multiple Cavities

[+] Author and Article Information
Vlad Ganine1

 Thermo-Fluid Systems UTC, Faculty of Engineering and Physical Sciences, University of Surrey Guildford, Surrey GU2 7XH, United Kingdomv.ganine@surrey.ac.uk

Umesh Javiya, Nick Hills, John Chew

 Thermo-Fluid Systems UTC, Faculty of Engineering and Physical Sciences, University of Surrey Guildford, Surrey GU2 7XH, United Kingdom

1

Corresponding author.

J. Eng. Gas Turbines Power 134(10), 102508 (Aug 22, 2012) (8 pages) doi:10.1115/1.4007060 History: Received June 20, 2012; Revised June 22, 2012; Published August 22, 2012; Online August 22, 2012

This paper presents the transient aerothermal analysis of a gas turbine internal air system through an engine flight cycle featuring multiple fluid cavities that surround a HP turbine disk and the adjacent structures. Strongly coupled fluid-structure thermal interaction problems require significant computational effort to resolve nonlinearities on the interface for each time step. Simulation times may grow impractical if multiple fluid domains are included in the analysis. A new strategy is employed to decrease the cost of coupled aerothermal analysis. Significantly lower fluid domain solver invocation counts are demonstrated as opposed to the traditional coupling approach formulated on the estimates of heat transfer coefficient. Numerical results are presented using 2D finite element conduction model combined with 2D flow calculation in five separate cavities interconnected through the inlet and outlet boundaries. The coupled solutions are discussed and validated against a nominal stand-alone model. Relative performance of both coupling techniques is evaluated.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Axisymmetric model of HP rotor assembly showing each component’s rotational speed

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Figure 2

y+ values at maximum power condition

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Figure 3

Stream lines and swirl ratio at maximum power condition in drive cone (1), preswirl lower (2), preswirl upper (3), bore (4) and rear (5) cavities. Inlet and outlet boundaries are marked by blue and red arrows.

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Figure 4

Transient cycle definition for HP rotor disk

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Figure 5

Temperature evolution at reference point 1. The coupled prediction is compared to the engine test measurement.

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Figure 6

Location of the reference points on high pressure turbine disk

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Figure 7

Nominal and coupled prediction differences with the measured temperature next to the blade root shown as a percentage of the test data

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Figure 8

Nominal and coupled prediction differences with the measured temperature inside the rear cavity shown as a percentage of the test data

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Figure 9

Nominal and coupled prediction differences with the measured temperature inside the preswirl inner cavity shown as a percentage of the test data

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Figure 10

Metal temperature profile predicted at maximum power condition t=4700 sec by the baseline model

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Figure 11

Metal temperature profile predicted at maximum power condition t=4700 sec by the coupled method

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Figure 12

Cumulative number of fluid-solid cycles

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Figure 13

Total number fluid domain calls

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