Prediction of unsteady cascade aerodynamics by an arbitrary Lagrangian-Eulerian finite element method

Gottfried, Dana A.; Fleeter, Sanford

doi:10.2514/6.1998-3746

Cited by 3 publications

(5 citation statements)

References 4 publications

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“…The constitutive relations used for the blade are those for a linear elastic isotropic solid. The elemental energy is updated by application of Equation 7, and the shock smearing factor is updated according to its governing equation [3].…”

Section: Updating Elemental Valuesmentioning

confidence: 99%

“…However, the fluid mesh cannot continue moving in a Lagrangian fashion, otherwise the solution will be destroyed as the mesh exits the solution domain with the fluid. Therefore, before proceeding to the next time level it is necessary to relax the fluid mesh to a new position and calculate new fluid mesh quantities via an advection calculation [3].…”

Section: Mesh Relaxation and Advectionmentioning

confidence: 99%

“…However, consistency is obtained by varying the static pressure at the exit until the average density and internal energy of the elements along the inflow boundary match the specified density and energy. Note that both boundary conditions are reflective [3,6].…”

Section: Inflow and Outflow Boundariesmentioning

confidence: 99%

“…The resulting Turbomachinery Aero-Mechanics corle is called TAM-ALE3D, with its ability to model unsteady turbnmachinery aerodynamics validated [3].…”

mentioning

confidence: 99%

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Aerodynamic damping predictions for turbomachine blade rows using a three-dimensional time marching simulation

Gottfried

Fleeter

1999

35th Joint Propulsion Conference and Exhibit

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Flow induced vibration of turbomachine blade rows is a coupled fluid-structure problem. Thus, rather than separate fluid and structural models, a coupled interacting fluid-structures analysis is needed. This research addresses this need by extending the finite element code ALE3D that solves the three-dimensional Euler equations to model the unsteady aerodynamics of turbomachine blade rows. The same finite element model is applied to both the blading and the fluid, resulting in consistency between the fluid and structure. This coupled interacting fluid-structure analysis enables the aerodynamic damping of multiple vibration modes to be predicted from a single time domain flow simulation. This novel approach to predict aerodynamic damping is demonstrated by considering a modem transonic compressor blade row. The blading is first impulsed in its first bending and first torsion modes in a vacuum. It is then immersed in the designpoint flow field and impulsed in its first bending and first torsion modes again. Signal processing tools applied to the predicted blade response time history extract the difference in the decay rate of both modes. spatial coordinate, i = I. 2, 3 nodal value. node number spatial coordinate, j = 1.2, 3 Descr;pl;on time step level node-centered element quantity

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Section: Updating Elemental Valuesmentioning

confidence: 99%

Section: Mesh Relaxation and Advectionmentioning

confidence: 99%

Section: Inflow and Outflow Boundariesmentioning

confidence: 99%

“…The resulting Turbomachinery Aero-Mechanics corle is called TAM-ALE3D, with its ability to model unsteady turbnmachinery aerodynamics validated [3].…”

mentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic damping predictions for turbomachine blade rows using a three-dimensional time marching simulation

Gottfried

Fleeter

1999

35th Joint Propulsion Conference and Exhibit

Self Cite

View full text Add to dashboard Cite

show abstract

“…Provide a an effective way to link the Lagrangian coordinate system in solid to the Eulerian coordinate system in fluid, so just discrete two physical domains into an arbitrary coordinate system, the movement of the grid becomes a movement part of the equation does not require separate treatment [30][31]. For solving the problem of the nonlinear coupling also need a large number of in-depth research work [32][33].…”

mentioning

confidence: 99%

A Review of the Research on Aeroelasticity in Aero Turbomachinery

2013

AMR

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Aeroelasticity in the form of blade flutter is a major concern for designers in the field of turbomachinery. This paper presents a review of the research and development on blade flutter modeling, including the unsteady aerodynamic model, the structural model and flutter prediction methods. Based on the presentation of these models, the fundamental mechanism and effects of different treatments are discussed. At the end of paper, some deficiencies in the research of flutter and difficulties in modeling fluid-solid coupling effects are pointed out, to which attention should be paid in future.

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Turbomachine blade row interaction predictions with a three-dimensional finite element method

Gottfried

Fleeter

2000

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Prediction of unsteady cascade aerodynamics by an arbitrary Lagrangian-Eulerian finite element method

Cited by 3 publications

References 4 publications

Aerodynamic damping predictions for turbomachine blade rows using a three-dimensional time marching simulation

Aerodynamic damping predictions for turbomachine blade rows using a three-dimensional time marching simulation

A Review of the Research on Aeroelasticity in Aero Turbomachinery

Turbomachine blade row interaction predictions with a three-dimensional finite element method

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