Evaluation of the Principle of Aerodynamic Superposition in Forced Response Calculations

Schmitt, S.; Nürnberger, Dirk; Carstens, V.

doi:10.1007/1-4020-4605-7_11

Cited by 4 publications

(8 citation statements)

References 10 publications

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“…This approach is equivalent to the 'superposition' approach discussed by Schmitt et al (2003), which has been shown to closely resemble the coupled solution for typical cases without significant nonlinear damping characteristics. Based on the decoupled aerodynamic forces calculated at the blade natural frequency, the response curves are extrapolated around the resonant peak using Eqs.…”

Section: Article In Pressmentioning

confidence: 92%

“…Linear flow solvers combined with the decoupled method have been reported for both resonant (Kielb, 1999;Chiang and Kielb, 1993;Manwaring and Kirkeng, 1997;Campobasso and Giles, 2000), and transient forced vibration problems (Green and Marshall, 1999). The use of nonlinear time-marching schemes with the decoupled method, although less common, has been reported by Schmitt et al (2003) and Moyroud et al (2000).…”

Section: Introductionmentioning

confidence: 91%

“…It is commonly accepted that mode-shapes effectively remain unchanged for lightly-damped turbomachinery blades, and this assumption has been widely adopted (Kielb, 1999;Marshall and Imregun, 1996). Linear aerodynamic damping behaviour for two transonic fan rotors has been observed by Li and He (2002), and Schmitt et al (2003). Linear flow solvers combined with the decoupled method have been reported for both resonant (Kielb, 1999;Chiang and Kielb, 1993;Manwaring and Kirkeng, 1997;Campobasso and Giles, 2000), and transient forced vibration problems (Green and Marshall, 1999).…”

Section: Introductionmentioning

confidence: 91%

“…Decoupled and coupled aeroelastic methods have been developed fairly independently within the disciplines of linearized and time-accurate CFD and few comparative studies have been published (Schmitt et al, 2003;Tran et al, 2003;Marshall et al, 2000). Schmitt et al show that the aerodynamic forces of the coupled solution closely match the superimposed decoupled forces for a counter-rotating prop fan, and Tran et al show agreement between a variety of coupled and decoupled methods when calculating the aeroelastic stability of a transonic blade row.…”

Section: Introductionmentioning

confidence: 95%

“…However, there has not yet been any reported evidence showing significant nonlinear damping under typical forced response conditions. Two distinct approaches to the solution of the decoupled forced response equation are based on the principles of (a) equivalent viscous aerodynamic damping ; and (b) superposition of aerodynamic forces (Schmitt et al, 2003).…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

On decoupled and fully-coupled methods for blade forced response prediction

Moffatt¹,

He²

2005

Journal of Fluids and Structures

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Section: Article In Pressmentioning

confidence: 92%

Section: Introductionmentioning

confidence: 91%

Section: Introductionmentioning

confidence: 91%

Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

On decoupled and fully-coupled methods for blade forced response prediction

Moffatt¹,

He²

2005

Journal of Fluids and Structures

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Turbomachinery Aeroelasticity

Bendiksen¹,

Kielb²,

Hall³

2010

Encyclopedia of Aerospace Engineering

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This paper focuses on the validity of the used assumptions in the development of the Decoupled approaches which predict the aeroelasticity behavior of turbomachinery blades. A Decoupled approach is employed to evaluate the aerodynamic damping and the forced response of a low pressure compressor BluM T M induced by low engine order excitations. The validity of the assumptions like superposition principle, linearity of aerodynamic damping forces and the blade-motion independency of the aerodynamic forces are verified by employing the TWIN approach. Extensive experiments are also carried out to evaluate the overall performance of the approaches.

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Acoustic performance of a resonating perforated liner with incident axial and circumferential acoustic modes

Cassell

Carrotte

2019

Journal of Sound and Vibration

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Perforated liners are a common form of passive damping device used in engineering applications to damp acoustic pressure fluctuations. The liner has many orifices arranged over the surface with a rear cavity, where the liner can be designed to resonate akin to an array of Helmholtz resonators in parallel. However, whilst a Helmholtz resonator is insensitive to the incident mode, the large surface area and rear cavity of a perforated liner can generate internal mode shapes that affect the acoustic performance. This paper presents a quasi-one-dimensional analytical model capable of capturing the variation in acoustic performance as the internal cavity segmentation is altered with incident higher-order acoustic modes in a narrow annular duct. Thus, the model can allow the generation of circumferential mode shapes. The model shows, when the liner is highly segmented circumferentially, the liner behaviour is akin to that with an incident axial wave. The segmentation causes the internal cavity pressure to fluctuate uniformly at a similar frequency to a Helmholtz resonator with the same effective cavity dimensions. When the cavity length is significant relative to the wavelength, circumferential mode shapes are generated within the cavity and the frequency

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Evaluation of the Principle of Aerodynamic Superposition in Forced Response Calculations

Cited by 4 publications

References 10 publications

On decoupled and fully-coupled methods for blade forced response prediction

On decoupled and fully-coupled methods for blade forced response prediction

Turbomachinery Aeroelasticity

Acoustic performance of a resonating perforated liner with incident axial and circumferential acoustic modes

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