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Numerical analysis of hub cavity leakage

Ye Xia (AECC Commercial Aircraft Engine Co., Ltd, Shanghai, China)
Yadong Xie (AECC Commercial Aircraft Engine Co., Ltd, Shanghai, China)
Danwang Li (AECC Commercial Aircraft Engine Co., Ltd, Shanghai, China)
Wenjie Wang (Beihang University, Beijing, China and University of Warwick, Coventry, UK)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 20 June 2019

Issue publication date: 21 August 2019




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.


Simulations 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.


The 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 implications

This work can provide a theoretical guidance and technical support for the compressor design, which avoid many repeated manufactures and reduce waste of resources.


This work improves the understanding of the impact mechanism of hub cavity leakage on the performance when the clearance size of seal is variable.



Xia, Y., Xie, Y., Li, D. and Wang, W. (2019), "Numerical analysis of hub cavity leakage", Aircraft Engineering and Aerospace Technology, Vol. 91 No. 8, pp. 1086-1092.



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