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Kazuya Kusano Last modified date:2022.09.29



Graduate School
Undergraduate School


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Homepage
https://kyushu-u.pure.elsevier.com/en/persons/kazuya-kusano
 Reseacher Profiling Tool Kyushu University Pure
Academic Degree
Doctor of Engineering
Country of degree conferring institution (Overseas)
No
Field of Specialization
Fluid Engineering
Total Priod of education and research career in the foreign country
00years00months
Research
Research Interests
  • Adjoint lattice Boltzmann method for flow-induced sound problems
    keyword : Adjoint method, Lattice Boltzmann method
    2020.04.
  • Flow and thermal simulation using data assimilation method
    keyword : ensemble Kalman filter
    2014.04~2017.03.
  • Aeroacoustic simulation method using lattice Boltzmann method
    keyword : flow induced sound, low-Mach-number flow, lattice Boltzmann method
    2011.04.
  • Flow structure in half-ducted propeller fan
    keyword : tip vortex, DES
    2009.04~2011.03.
Academic Activities
Papers
1. Kazuya Kusano, Adjoint sensitivity analysis method based on lattice Boltzmann equation for flow-induced sound problems, Computers & Fluids, 10.1016/j.compfluid.2022.105662, 248, 15, 2022.11.
2. Kazuya Kusano, Kazutoyo Yamada, Masato Furukawa, Aeroacoustic simulation of broadband sound generated from low-Mach-number flows using a lattice Boltzmann method, Journal of Sound and Vibration, 10.1016/j.jsv.2019.115044, 467, 2020.02.
3. Kazuya Kusano, Hironobu Yamakawa, Kenich Hano, A Parameter-Estimation Method Using the Ensemble Kalman Filter for Flow and Thermal Simulation in an Engine Compartment, Journal of Heat Transfer, 10.1115/1.4041188, 140, 12, 2018.12.
4. Three-dimensional structure of tip vortex in a half-ducted propeller fan
The tip vortex has an important role on the aerodynamic performance and noise of half-ducted propeller fans. The present paper provides better understanding on the three-dimensional structure of the tip vortex in a half-ducted propeller fan, aiming at the effective control of it. A numerical analysis was carried out using a detached eddy simulation (DES). DES results were validated by the comparison with LDV measurement data. Vortex centers around the propeller fan were identified by the critical point theory. The numerical results show that the tip vortex in the opened region upstream of the shroud leading edge is advected nearly along main stream, whereas the tip vortex in the ducted region covered by the shroud is turned toward the tangential direction by the interaction of the tip vortex with the shroud wall. The behavior of the tip vortex in its inception region does not depend on the flow rate, because the relative inflow angle at the leading edge near the blade tip is independent of the flow rate. On the other hand, the behavior of the tip vortex in the ducted region is sensitive to the flow rate. As the flow rate is decreased, the tip vortex interacts more strongly with the shroud wall, and as a result, its trajectory is inclined more largely in the tangential direction in the ducted region. In the opened region, the core radius and circulation of the tip vortex increase rapidly at constant growth rate in the streamwise direction. In the ducted region, on the other hand, the tip vortex decays gradually in the downstream direction. The maximum circulation of the tip vortex amounts to 6075% of the circulation of the bound vortices released from the near tip region of the blade. It is found that the jet-like axial velocity distribution is formed around the tip vortex center by the favorable pressure gradient along the tip vortex center resulting from its rapid growth in the opened region..