Advanced Modeling of Underplatform Friction Dampers for Analysis of Bladed Disk Vibration

Petrov, E. P.; Ewins, D. J.

doi:10.1115/1.2372775

Cited by 79 publications

(47 citation statements)

References 16 publications

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“…Normally, the static load on the damper due to the centrifugal force is assumed to be constant and equally distributed between the two platforms [6,20]. However, when enough contact elements are used, non-uniform pressure distributions can be represented with a good approximation.…”

Section: Input Parameters Studymentioning

confidence: 99%

“…This might lead to an uneven pressure distribution at the interface, which is often neglected during the modelling phase and replaced by a constant value [20]. In this case, the initial pressure σ 0 on each side of the damper can be evaluated, taking friction in the contact into account, as follows:…”

Section: Contact Pressure Distributionmentioning

confidence: 99%

“…Difficulties encountered during the validation of the latter models suggested that the required hypotheses were not always realistic [6]. In more advanced models [16][17][18][19][20], these hypotheses were removed and the damper motion is calculated purely as the result of its interaction with the blades by means of the nonlinear contact forces. To reproduce damper motions, advanced 3D friction contact elements were employed; these account for normal load variation with separation effects and 2D tangential in plane motion [21].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Modelling the nonlinear behaviour of an underplatform damper test rig for turbine applications

Pesaresi

Salles

Jones

et al. 2017

Mechanical Systems and Signal Processing

134

108

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Underplatform dampers (UPD) are commonly used in aircraft engines to mitigate the risk of high-cycle fatigue failure of turbine blades. The energy dissipated at the friction contact interface of the damper reduces the vibration amplitude significantly, and the couplings of the blades can also lead to significant shifts of the resonance frequencies of the bladed disk. The highly nonlinear behaviour of bladed disks constrained by UPDs requires an advanced modelling approach to ensure that the correct damper geometry is selected during the design of the turbine, and that no unexpected resonance frequencies and amplitudes will occur in operation. Approaches based on an explicit model of the damper in combination with multi-harmonic balance solvers have emerged as a promising way to predict the nonlinear behaviour of UPDs correctly, however rigorous experimental validations are required before approaches of this type can be used with confidence.In this study, a nonlinear analysis based on an updated explicit damper model having different levels of detail is performed, and the results are evaluated against a newly-developed UPD test rig. Detailed linear finite element models are used as input for the nonlinear analysis, allowing the inclusion of damper flexibility and inertia effects. The nonlinear friction interface between the blades and the damper is described with a dense grid of 3D friction contact elements which allow accurate capturing of the underlying nonlinear mechanism that drives the global nonlinear behaviour. The introduced explicit damper model showed a great dependence on the correct contact pressure distribution. The use of an accurate, measurement based, distribution, better matched the nonlinear dynamic behaviour of the test rig. Good agreement with the measured frequency response data could only be reached when the zero harmonic term (constant term) was included in the multi-harmonic expansion of the nonlinear problem, highlighting its importance when the contact interface experiences large normal load variation. The resulting numerical damper kinematics with strong translational and rotational motion, and the global blades frequency response were fully validated experimentally, showing the accuracy of the suggested high detailed explicit UPD modelling approach.

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Section: Input Parameters Studymentioning

confidence: 99%

Section: Contact Pressure Distributionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Modelling the nonlinear behaviour of an underplatform damper test rig for turbine applications

Pesaresi

Salles

Jones

et al. 2017

Mechanical Systems and Signal Processing

134

108

View full text Add to dashboard Cite

show abstract

“…However, most of the existing experimental contributions assumed or observed weakly nonlinear behaviors. In parallel, substantial efforts were made to address the numerical modeling of complex, nonlinear aerospace structures (see, e.g., [11,12]). Analysis using advanced numerical continuation techniques was also carried out in [13,14].…”

Section: Introductionmentioning

confidence: 99%

Complex dynamics of a nonlinear aerospace structure: numerical continuation and normal modes

2014

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This paper investigates the dynamics of a real-life aerospace structure possessing a strongly nonlinear component with multiple mechanical stops. A full-scale finite element model is built for gaining additional insight into the nonlinear dynamics that was observed experimentally, but also for uncovering additional nonlinear phenomena, such as quasiperiodic regimes of motion. Forced/unforced, damped/undamped numerical simulations are carried out using advanced techniques and theoretical concepts such as numerical continuation and nonlinear normal modes.

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“…The contact interface elements developed in [12] are used to model the nonlinear interactions at contact interfaces and analytical expressions for the multiharmonic representation of the nonlinear contact forces and stiffnesses. The nonlinear algebraic system of the reduced model is obtained using a hybrid reduction method developed by Petrov [14,15] leading to a nonlinear system in the frequency domainQ…”

Section: Nonlinear Dynamic Analysismentioning

confidence: 99%

A Multiscale Approach for Nonlinear Dynamic Response Predictions With Fretting Wear

Armand

Pesaresi

Salles

et al. 2016

Journal of Engineering for Gas Turbines and Power

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Accurate prediction of the vibration response of aircraft engine assemblies is of great importance when estimating both the performance and the lifetime of their individual components. In the case of underplatform dampers, for example, the motion at the frictional interfaces can lead to a highly nonlinear dynamic response and cause fretting wear at the contact. The latter will change the contact conditions of the interface and consequently impact the nonlinear dynamic response of the entire assembly. Accurate prediction of the nonlinear dynamic response over the lifetime of the assembly must include the impact of fretting wear. A multi-scale approach that incorporates wear into the nonlinear dynamic analysis is proposed, and its viability is demonstrated for an underplatform damper system. The nonlinear dynamic response is calculated with a multiharmonic balance approach, and a newly developed semi-analytical contact solver is used to obtain the contact conditions at the blade-damper interface with high accuracy and low computational cost. The calculated contact conditions are used in combination with the energy wear approach to compute the fretting wear at the contact interface. The nonlinear dynamic model of the blade-damper system is then updated with the worn profile and its dynamic response is recomputed. A significant impact of fretting wear on the nonlinear dynamic behaviour of the blade-damper system was observed, highlighting the sensitivity of the nonlinear dynamic response to changes at the contact interface. The computational speed and robustness of the adopted multi-scale approach are demonstrated.

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Advanced Modeling of Underplatform Friction Dampers for Analysis of Bladed Disk Vibration

Cited by 79 publications

References 16 publications

Modelling the nonlinear behaviour of an underplatform damper test rig for turbine applications

Modelling the nonlinear behaviour of an underplatform damper test rig for turbine applications

Complex dynamics of a nonlinear aerospace structure: numerical continuation and normal modes

A Multiscale Approach for Nonlinear Dynamic Response Predictions With Fretting Wear

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