Coupled Fluid-Structure Simulation for Turbomachinery Blade Rows

Sadeghi, Mani; Liu, Feng

doi:10.2514/6.2005-18

Cited by 26 publications

(20 citation statements)

References 29 publications

(19 reference statements)

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“…ParCAE has been previously demonstrated for computation of 3D turbomachinery flutter 8,10 in isolated blade rows. To demonstrate ParCAE's ability to perform multi-stage computations, NASA's Rotor 67 transonic compressor blade row has been used.…”

Section: Resultsmentioning

confidence: 99%

Mixing-Plane Method for Flutter Computation in Multistage Turbomachines

Culver

Liu

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The mixing-plane method for calculating the three-dimensional flow through multistage turbomachinery is used to perform flutter analysis on a single stage transonic compressor. The turbomachine considered is composed of an inlet guide vane (IGV) and a compressor blade (NASA Rotor 67). The mixing-plane boundary condition enables steady and unsteady computation of the flow through multiple blade rows. This allows incorporation of multi-stage effects without having to perform computationally intensive fully unsteady multi-stage flow computations. Forced motion flutter computations are performed for both the isolated compressor and with the IGV. Comparison between the damping ratio shows a decrease in stability when the IGV is included in the computation.

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Section: Resultsmentioning

confidence: 99%

Mixing-Plane Method for Flutter Computation in Multistage Turbomachines

Culver

Liu

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…To research the blade response in the unsteady flow, structural dynamics equation and fluid mechanics equation must resort to coupled solution [3][4] [5]. Through two-way coupling, the aeroelastic characteristic of blades is numerical analyzed.…”

Section: Methodsmentioning

confidence: 99%

Aeroelastic Stability Analysis of Compressor Blades in High-low Altitude

Zhang¹,

Chen²,

Huang³

2015

Proceedings of the 4th International Conference on Mechatronics, Materials, Chemistry and Computer Engineering 2015

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Abstract. Fluid-structure coupled method has been applied to research the aeroelastic stability of compressor blades, and the effects of high-low altitude on blade flutter characteristics are investigated through comparison. Results show that, these frequencies corresponding to displacement, elastic strain of blade are identical with the first order natural frequency based on frequency spectrum analysis, which means that there remains a strong possibility on the frequency in the event of blade flutter. The amplitude of displacement, elastic strain on the ground is greater than that in high altitude, so aeroelastic stability on the ground is lower than that in high altitude.

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“…The CVT method was presented by Goura et al [26] and subsequently improved and applied by Sadeghi et al [29] and Sadeghi and Liu [30]. As the name implies, it is based on forming a tetrahedron between each node on the aerodynamic surface and the three nearest structural nodes.…”

Section: Discussion Of Available Methodsmentioning

confidence: 99%

Unified fluid–structure interpolation and mesh motion using radial basis functions

Rendall

Allen

2007

Numerical Meth Engineering

294

205

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SUMMARYA multivariate interpolation scheme, using radial basis functions, is presented, which results in a completely unified formulation for the fluid-structure interpolation and mesh motion problems. The method has several significant advantages. Primarily, all volume mesh, structural mesh, and flow-solver type dependence is removed, and all operations are performed on totally arbitrary point clouds of any form. Hence, all connectivity and user-input requirements are removed from the computational fluid dynamics-computational structural dynamics (CFD-CSD) coupling problem, as only point clouds are required to determine the coupling. Also, it may equally well be applied to structured and unstructured grids, or structural and aerodynamic grids that intersect, again because no connectivity information is required. Furthermore, no expensive computations are required during an unsteady simulation, just matrix-vector multiplications, since the required dependence relations are computed only once prior to any simulation and then remain constant. This property means that the method is both perfectly parallel, since only the data relevant to each structured block or unstructured partition are required to move those points, and totally independent from the flow solver. Hence, a completely generic 'black box' tool can be developed, which is ideal for use in an optimization approach. Aeroelastic behaviour of the Brite-Euram MDO wing is analysed in terms of both static deflection and dynamic responses, and it is demonstrated that responses are strongly dependent on the exact CFD-CSD interpolation used. Mesh quality is also examined during the motion resulting from a large surface deformation. Global grid quality is shown to be preserved well, with local grid orthogonality also being maintained well, particularly at and near the moving surface, where the original orthogonality is retained.

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Coupled Fluid-Structure Simulation for Turbomachinery Blade Rows

Cited by 26 publications

References 29 publications

Mixing-Plane Method for Flutter Computation in Multistage Turbomachines

Mixing-Plane Method for Flutter Computation in Multistage Turbomachines

Aeroelastic Stability Analysis of Compressor Blades in High-low Altitude

Unified fluid–structure interpolation and mesh motion using radial basis functions

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