Turbomachinery Aeroelasticity

Bendiksen, Oddvar O.; Kielb, Robert E.; Hall, Kenneth C.

doi:10.1002/9780470686652.eae156

Cited by 8 publications

(15 citation statements)

References 28 publications

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“…3 Furthermore, the structural dynamics and unsteady aerodynamic loading caused by bird damage induce a complex aeroelastic response problem that can lead to aeroelastic instability. 4,5 Predicting the aeroelastic behavior of a bird damaged fan blade represents a significant design barrier in the development of improved-efficiency turbofan engines.…”

Section: Nomenclaturementioning

confidence: 99%

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Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Muir

Friedmann

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The aeroelastic response of a bird-damaged fan stage at the inlet of a high-bypass ratio turbofan engine is examined using a combined CFD/CSD model. ANSYS CFX is used for the computational fluid dynamic (CFD) calculations combined with the ANSYS Multifield (MFX) solver that couples ANSYS CFX with ANSYS Mechanical APDL to perform aeroelastic response calculations. The damaged fan sector consists of 5 blades that represent the geometry resulting from a numerical bird strike simulation. The forced response of the undamaged blades downstream of the damaged sector exhibits the highest level of structural response. The structural response of these undamaged blades is dominated by the first bending mode and increases in amplitude with time. The aeroelastic response shows a similar behavior, with the downstream undamaged blades exhibiting a growing structural response that is dominated by the first bending mode. The aeroelastic response of the damaged blades also contains contributions from the second torsion mode. An examination of the work exerted by the aerodynamic forces suggests that the growth in blade response for the upstream damaged blade is due to an aeroelastic behavior that may be indicative of a potential instability. Nomenclature D Number of RBF driver pointṡ mMass flow ratė m R Referred mass flow rate q m

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Section: Nomenclaturementioning

confidence: 99%

“…(5). Within ANSYS CFX, the aerodynamic forces are first calculated at each CFD node on the blade surface using Eq.…”

Section: Aerodynamic Load and Structural Deformation Transfermentioning

confidence: 99%

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Muir

Friedmann

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…The compressor design has an increasing trend towards higher blade loading and thinner blade shape. However, this also increases the occurrence probability of aeroelastic instability which can be mainly divided into forced response, nonsynchronous vibration, acoustic resonance and flutter [1,2]. The former three types rely on the unsteady aerodynamic forces generated by external disturbances.…”

Section: Introductionmentioning

confidence: 99%

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

Xin,

He,

et al. 2024

J. Phys.: Conf. Ser.

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Flutter is a highly destructive aeroelastic problem in modern compressors, which hinders the improvements of aero-engine performance and reliability. Because the aerodynamic work is mainly concentrated in the blade tip region, the tip clearance which is associated to the complex tip clearance flow has a considerable effect on the flutter stability. In this paper, in order to investigate the influence mechanism of the tip clearance on the flutter stability at different nodal diameters (ND), a series of compressor models were established with different tip clearances based on a transonic compressor rotor. The aerodynamic damping at each ND is obtained by influence coefficient method (ICM), while phase-shifted boundary method (PSB) is adopted to analyze the influence of the tip clearance on the flutter stability at different NDs. The results indicate the worst flutter stability for each tip clearance always appears at ND=1, where the aerodynamic damping exhibits a nonmonotonic trend of increasing first and decreasing thereafter along with the rising tip clearance. Two kinds of action are exerted by the tip clearance flow on the flow structures to alter the flutter stability: one is the tip clearance vortices which is generated on the suction side and impinge on the pressure side; the other is the interference of tip clearance vortices to the shock wave and to the flow separation. Besides, the influence of the changing aerodynamic coupling effect makes the above action bring about more drastic fluctuations to the unsteady pressure. At larger NDs, the unsteady pressure amplitude and phase fluctuate more sharply for larger tip clearances. Therefore, diverse change trends of the aerodynamic damping with the increasing tip clearance appear at different NDs, while the impingement of tip clearance vortices on the adjacent pressure side has a constantly stabilizing effect at different NDs.

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“…Also, it has been shown that any loss of symmetry in the flow field may cause an LEO forced response [ 1 , 4 , 5 , 6 ]. However, the stator vanes of the turbine, as high-temperature components downstream of the combustion chamber, experience creep, fatigue, oxidation and corrosion, and sudden damage failures at the trailing edges occur regularly [ 7 , 8 , 9 ]. Geometric changes in the stator vanes not only affect the work of the stator row but may also destroy the circumferential symmetry of the design flow and cause the LEO forced response on rotor blades.…”

Section: Introductionmentioning

confidence: 99%

Low-Engine-Order Forced Response Analysis of a Turbine Stage with Damaged Stator Vane

Zheng,

Jin,

Yang

2023

Entropy

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A damaged stator vane can disrupt the circumferential symmetry of the design flow for turbine assemblies, which can lead to a low-engine-order (LEO) forced response of rotor blades. To help engineers be able to better address sudden vane damage failures, this paper conducts a mechanism analysis of the LEO forced response of rotor blades induced by a single damaged vane using an in-house computational fluid dynamic code (Hybrid Grid Aeroelasticity Environment). Firstly, it is found that the damaged vane introduces a family of LEO aerodynamic excitations with high amplitudes by full-annulus unsteady aeroelastic simulations of a single-stage turbine. In particular, the LEO forced response of the rotor blades excited by 3EO is 2.01 times higher than the resonance response excited by vane passing frequency, and the LEO resonance risk of the rotor blades is greatly increased. Then, by analyzing the flow characteristics of the wake and potential field of the stator row with a damaged vane, the localized high transient pressure in the notch cavity and the radial redistribution of the secondary vortex at the stator exit are the main sources of the low-order harmonic components in the flow field. Importantly, the interaction mechanisms in two regions with high LEO excitation amplitude on the rotor blade surface are revealed separately. Finally, an evaluation and comparison of a single damaged vane in terms of aerodynamic performance and LEO forced response was carried out. The results of this paper provide a good theoretical basis for engineers to effectively control the resonance response of rotor blades caused by a damaged stator vane in turbine design.

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Turbomachinery Aeroelasticity

Cited by 8 publications

References 28 publications

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

Low-Engine-Order Forced Response Analysis of a Turbine Stage with Damaged Stator Vane

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