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Journal of Thermal Science

, Volume 27, Issue 3, pp 294–303 | Cite as

Influence of Reynolds Number on the Unsteady Aerodynamics of Integrated Aggressive Intermediate Turbine Duct

  • Hongrui Liu
  • Jun Liu
  • Lucheng Ji
  • Qiang Du
  • Guang Liu
  • Pei Wang
Article
  • 48 Downloads

Abstract

The ultra-high bypass ratio turbofan engine attracts more and more attention in modern commercial engine due to advantages of high efficiency and low Specific Fuel Consumption (SFC). One of the characteristics of ultra-high bypass ratio turbofan is the intermediate turbine duct which guides the flow leaving high pressure turbine (HPT) to low pressure turbine (LPT) at a larger diameter, and this kind of design will lead to aggressive intermediate turbine duct (AITD) design concept. Thus, it is important to design the AITD without any severe loss. From the unsteady flow’s point of view, in actual operating conditions, the incoming wake generated by HPT is unsteady which will take influence on boundary layer’s transition within the ITD and LPT. In this paper, the three-dimensional unsteady aerodynamics of an AITD taken from a real engine is studied. The results of fully unsteady three-dimensional numerical simulations, performed with ANSYS-CFX (RANS simulation with transitional model), are critically evaluated against experimental data. After validation of the numerical model, the physical mechanisms inside the flow channel are analyzed, with an aim to quantify the sensitivities of different Reynolds number effect on both the ITD and LPT nozzle. Some general physical mechanisms can be recognized in the unsteady environment. It is recognized that wake characteristics plays a crucial role on the loss within both the ITD and LPT nozzle section, determining both time-averaged and time-resolved characteristics of the flow field. Meanwhile, particular attention needs to be paid to the unsteady effect on the boundary layer of LPT nozzle’s suction side surface.

Keywords

Intermediate Turbine Duct Unsteady Simulation Reynolds Number Flow Field Analysis 

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Notes

Acknowledgements

The authors wish to thank the National Natural Science Foundation of China for sponsoring the research described in the current paper (51776200).

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Copyright information

© Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2018

Authors and Affiliations

  • Hongrui Liu
    • 1
    • 2
    • 3
  • Jun Liu
    • 2
    • 3
  • Lucheng Ji
    • 1
  • Qiang Du
    • 2
    • 3
  • Guang Liu
    • 2
    • 3
  • Pei Wang
    • 2
    • 3
  1. 1.School of Aerospace EngineeringBeijing Institute of TechnologyBeijingChina
  2. 2.Key Laboratory of Light-Duty Gas-Turbine, Institute of Engineering ThermophysicsChinese Academy of SciencesBeijingChina
  3. 3.University of Chinese Academy of SciencesBeijingChina

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