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Research Papers: Gas Turbines: Aircraft Engine

Secondary Air System Component Modeling for Engine Performance Simulations

[+] Author and Article Information
A. Alexiou

Laboratory of Thermal Turbomachines, National Technical University of Athens, P.O. Box 64069, Athens 15710, Greecea.alexiou@ltt.ntua.gr

K. Mathioudakis

Laboratory of Thermal Turbomachines, National Technical University of Athens, P.O. Box 64069, Athens 15710, Greecekmathiou@central.ntua.gr

J. Eng. Gas Turbines Power 131(3), 031202 (Feb 13, 2009) (9 pages) doi:10.1115/1.3030878 History: Received June 30, 2008; Revised July 09, 2008; Published February 13, 2009

This paper describes the modeling of typical secondary air system elements such as rotating orifices, seals, and flow passages with heat and work transfer from the surrounding surfaces. The modeling is carried out in an object-oriented simulation environment that allows the creation of different configurations in a simple and flexible manner. This makes possible to compare the performance between different designs of individual components or complete secondary air systems as well as integrate them directly in whole engine performance models. The modeling is validated against published experimental data and computational results. An example of implementation in an engine model is also presented.

Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Secondary air system

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Figure 2

Generic component model

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Figure 3

Orifice component model

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Figure 4

Labyrinth seal component model

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Figure 5

Variation of Θ with βin

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Figure 6

Variation of βmix with βin

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Figure 7

Nondimensional temperature reduction

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Figure 9

Tangential velocity variation with disk speed

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Figure 10

Variation of nondimensional temperature change with buoyancy number

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Figure 11

Variation of CD with i

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Figure 12

Variation of CD with βmix

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Figure 13

Variation of CD with βmix for midradius preswirl system

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Figure 14

Variation of CD with i for radial rotating holes

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Figure 15

Variation of Θ with βmix for midradius preswirl cavity

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Figure 16

Engine performance model with secondary air system

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Figure 17

Effect of turbine rotor cooling air mass flow rate variation on preswirl system performance

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