Generation of Vortex Lift Through Reduction of Rotor/Stator Gap in Turbomachinery

Du, Lin; Sun, Xiaofeng; Yang, Vigor

doi:10.2514/1.b35858

Cited by 20 publications

(11 citation statements)

References 52 publications

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“…The numerical results agreed very well with the measurements reported by Park and Garcés [46]. Finally, the present method has also been used to investigate the effect of shedding vortices in the process of rotor/stator interaction in turbine engines when the axial gap between blade rows is reduced [23].…”

Section: Introductionsupporting

confidence: 84%

“…3, the immersed-boundary method is implemented to satisfy the no-slip boundary condition on blades. The details of the numerical scheme and many aspects of the present method can be found in the work of Du et al [23].…”

Section: Governing Equationsmentioning

confidence: 99%

“…where e is the internal energy, h is the enthalpy,τ ij is the viscous stress tensor, F l denotes the boundary forces, and the k-ε model is used to consider Reynolds stress tensors. The same numerical scheme is used in the study of Du et al [23]. A stage consisting of 2:3 rotor-stator blades is investigated, as depicted in Fig.…”

Section: Compressible and Turbulent Flowmentioning

confidence: 99%

“…In a separate work, we have proposed [23] reducing the axial gap between blade rows as a means of enhancing rotor/stator interaction to generate high unsteady lift and improve the stage loading. In the present work, a novel stage consisting of a rotor and a periodically pitched stator is proposed to further enhance rotor/stator interaction.…”

Section: Introductionmentioning

confidence: 99%

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Vortex-Lift Mechanism in Axial Turbomachinery with Periodically Pitched Stators

Sun

Yang

2016

Journal of Propulsion and Power

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Conventional aerodynamic theory of lift is based on the Kutta-Joukowski condition, in which the lift and drag coefficients are predicted based on the assumption that flow is attached and steady-state. Recent research on insect flight indicates, however, that the unsteady motion of a wing can generate much higher unsteady aerodynamic force through the flow induced by the shedding vortices. In the present work, therefore, we propose a novel type of stage consisting of rotor and periodically pitched stator to take advantage of unsteady vortex lift. The numerical results suggest that the flowfield around the leading and trailing edges of the blades are substantially modified by the interactions between the rotor and pitching stator. Several transient lift peaks can be generated for each period. If an appropriate pitching phase is chosen for the stator, stage performance can be improved through unsteady lift mechanism effects.

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Section: Introductionsupporting

confidence: 84%

Section: Governing Equationsmentioning

confidence: 99%

Section: Compressible and Turbulent Flowmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Vortex-Lift Mechanism in Axial Turbomachinery with Periodically Pitched Stators

Sun

Yang

2016

Journal of Propulsion and Power

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“…Under the frame of AMR, the wall boundary is normally modeled by the cut‐cell method or the IB methods, and it was thought that the IB methods could achieve a better calculation for the skin friction with less oscillation 53 . In the present study, a sharp interface IB method is employed, which was originally proposed by Gilmanov et al, 55 Gilmanov and Sotiropoulos, 30 and has been further validated and applied to a variety of FSI problems in Du et al, 56 Du and Sun, 57 and Du et al 58,59 …”

Section: Introductionmentioning

confidence: 97%

Adaptive mesh refinement for simulating fluid‐structure interaction using a sharp interface immersed boundary method

Wang

Sun

2020

Numerical Methods in Fluids

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Summary In this article, adaptive mesh refinement (AMR) is performed to simulate flow around both stationary and moving boundaries. The finite‐difference approach is applied along with a sharp interface immersed boundary (IB) method. The Lagrangian polynomial is employed to facilitate the interpolation from a coarse to a fine grid level, while a weighted‐average formula is used to transfer variables inversely. To save memory, the finest grid is only generated in the local areas close to the wall boundary, and the mesh is dynamically reconstructed based on the location of the wall boundary. The Navier‐Stokes equations are numerically solved through the second‐order central difference scheme in space and the third‐order Runge‐Kutta time integration. Flow around a circular cylinder rotating in a square domain is firstly simulated to examine the accuracy and convergence rate. Then three cases are investigated to test the validity of the present method: flow past a stationary circular cylinder at low Reynolds numbers, flow past a forced oscillating circular cylinder in the transverse direction at various frequencies, and a free circular cylinder subjected to vortex‐induced vibration in two degrees of freedom. Computational results agree well with these in the literature and the flow fields are smooth around the interface of different refinement levels. The effect of refinement level has also been evaluated. In addition, a study for the computational efficiency shows that the AMR approach is helpful to reduce the total node number and speed up the time integration, which could prompt the application of the IB method when a great near‐wall spatial resolution is required.

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