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Numerical analysis of hub cavity leakage

Numerical analysis of hub cavity leakage This paper aims to predict the effect of the hub cavity leakage on the overall performance with numerical simulations in the fan/booster of a high bypass ratio turbofan engine.Design/methodology/approachSimulations are conducted for leakage at the fan, the outlet of guide vane and the three-stage booster, as well as hub leakage (contain cavities and sealing). The results obtained are compared to the corresponding simulations without hub leakage.FindingsThe rotor/stator interaction locations are evaluated to discover a better location. The results show that the seal tooth structure produces secondary flow and turbulence in the root of blade suction surface, which increases the aerodynamic loss. The sealing clearance should be controlled to shrink the turbulent region and decrease the leakage.Practical implicationsThis work can provide a theoretical guidance and technical support for the compressor design, which avoid many repeated manufactures and reduce waste of resources.Originality/valueThis work improves the understanding of the impact mechanism of hub cavity leakage on the performance when the clearance size of seal is variable. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

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Publisher
Emerald Publishing
Copyright
© Emerald Publishing Limited
ISSN
1748-8842
DOI
10.1108/aeat-06-2018-0154
Publisher site
See Article on Publisher Site

Abstract

This paper aims to predict the effect of the hub cavity leakage on the overall performance with numerical simulations in the fan/booster of a high bypass ratio turbofan engine.Design/methodology/approachSimulations are conducted for leakage at the fan, the outlet of guide vane and the three-stage booster, as well as hub leakage (contain cavities and sealing). The results obtained are compared to the corresponding simulations without hub leakage.FindingsThe rotor/stator interaction locations are evaluated to discover a better location. The results show that the seal tooth structure produces secondary flow and turbulence in the root of blade suction surface, which increases the aerodynamic loss. The sealing clearance should be controlled to shrink the turbulent region and decrease the leakage.Practical implicationsThis work can provide a theoretical guidance and technical support for the compressor design, which avoid many repeated manufactures and reduce waste of resources.Originality/valueThis work improves the understanding of the impact mechanism of hub cavity leakage on the performance when the clearance size of seal is variable.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Aug 21, 2019

Keywords: Hub cavity leakage; Fan/booster; Clearance size; Numerical simulations.

References