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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

Numerical analysis of hub cavity leakage

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Publisher
Emerald Publishing
Copyright
© Emerald Publishing Limited
ISSN
1748-8842
DOI
10.1108/aeat-06-2018-0154
Publisher site
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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 Technology – Emerald Publishing

Published: Aug 21, 2019

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

References

  • Numerical investigation of a cantilevered compressor stator at varying clearance sizes
    Chengwu, Y.; Xingen, L.
  • The influence of shrouded stator cavity flows on the aerodynamic performance of a high-speed multistage axial-flow compressor
    Dai, K.; Mai, Y.
  • The aerodynamic interaction of stator shroud leakage and mainstream flows in compressors
    Demargne, A.A.J.; Longley, J.P.
  • Effect of tip clearance on compressor stability and performance
    Freeman, C.
  • Modeling of the hub cavity leakage flows in axial compressors
    Hasham, H.C.; Anand, D.
  • Stator seal cavity flow investigation
    Heidegger, N.J.; Hall, E.J.; Delaney, R.A.
  • Some shrouding and tip clearance effects in axial flow compressors
    Jefferson, J.L.; Turner, R.C.
  • Leakage characteristics of labyrinth seals with high rotating speed
    Komotori, K.; Miyake, K.
  • Aerodynamic analysis of nonuniform trailing edge blowing
    Liang, D.; Wang, W.; Thomas, P.J.
  • An experimental investigation of shrouded and cantilevered compressor stators at varying clearance sizes
    Martin, L.; Ronald, M.; Konrad, V.
  • Numerical modeling of cavities in multistage axial compressors
    Naylor, E.; Montomoli, F.; Hodson, H.; Lapworth, L.
  • Influence of the leakage flow tangential velocity on the loss generation and leakage flow kinematics in shrouded compressor axial Cascades
    Sohn, D.W.; Kim, T.; Song, S.J.
  • An experimental examination of cantilevered and shrouded stators in a multistage axial compressor
    Swoboda, M.; Ivey, P.C.; Wenger, U.; G¨ummer, V.
  • The influence of shrouded stator cavity flows on multistage compressor performance
    Wellborn, S.R.; Okiishi, T.H.
  • Modeling shrouded stator cavity flows in Axial-Flow compressors
    Wellborn, S.R.; Tolchinsky, I.; Okiishi, T.H.
  • Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance
    Wellborn, S.R.; Okiishi, T.H.
  • The influence of shrouded stator cavity flows on multistage compressor performance
    Wellborn, S.R.; Okiishi, T.H.