On tuned bladed disk dynamics: Some aspects of friction related mistuning

Muszynska, Agnieszka; Jones, D. I. G.

doi:10.1016/0022-460x(83)90947-1

Cited by 22 publications

(10 citation statements)

References 17 publications

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“…One of the main reasons behind some poor predictive capabilities of these two generations of ROMs is their partial intrinsic lack of capturing the physical deformation mechanisms existing in the blades or sectors. Although many important phenomena existing in rotors like damping mistuning [83,84], stress stiffening [51], spin softening [36], Coriolis effects [85,86] and inter-stage coupling [87][88][89] have been investigated and included into the ROMs, the fundamental understanding and modeling of some other physical aspects are still in development. These phenomena include the aerodynamic coupling, nonlinearities from contact friction and geometry, multistage rotor coupling and blade damage [79].…”

Section: Emerging Trendsmentioning

confidence: 99%

Efficient computational techniques for mistuning analysis of bladed discs: A review

Yuan

Scarpa

Allegri

et al. 2017

Mechanical Systems and Signal Processing

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This paper describes a review of the relevant literature about mistuning problems in bladed disc systems, and their implications for the uncertainty propagation associated to the dynamics of aeroengine systems. An emphasis of the review is placed on the developments of the multi-scale computational techniques to increase the computational efficiency for the linear mistuning analysis, especially with the respect to the reduced order modeling techniques and uncertainty quantification methods. The non-linearity phenomenon would not be considered in this paper. The first two parts describe the fundamentals of the mechanics of tuned and mistuned bladed discs, followed by a review of critical research efforts performed on the development of reduced order rotor models. The focus of the fourth part is on the review of efficient simulation methods for the stochastic analysis of mistuned bladed disc systems. After that, we will finally provide a view of the current state of the art associated to efficient inversion methods for the stochastic analysis, followed by a summary.

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Section: Emerging Trendsmentioning

confidence: 99%

Efficient computational techniques for mistuning analysis of bladed discs: A review

Yuan

Scarpa

Allegri

et al. 2017

Mechanical Systems and Signal Processing

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“…Friction damping, significant enough in traditional fan and compressor rotors to cause mistuned response [10] or change mistuned response [13], does not factor in IBR analysis where the dovetail slot/post interface does not exist. While not including friction damping is obvious, the exclusion of aerodynamic damping is limited for the same reason that CFD is not included.…”

Section: System Modelmentioning

confidence: 99%

“…Equation (10) shows the CDF values (F ) for a given stress level (x) of the cycles to failure (w). The CDF value of a standard normal statistic is Φ(•) and the Probability Density Function (PDF) of a normal statistic is φ(•).…”

Section: Materials Capacitymentioning

confidence: 99%

Probabilistic Rotor Life Assessment Using Reduced Order Models

Beachkofski

2009

Shock and Vibration

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Probabilistic failure assessments for integrally bladed disks are system reliability problems where a failure in at least one blade constitutes a rotor system failure. Turbine engine fan and compressor blade life is dominated by High Cycle Fatigue (HCF) initiated either by pure HCF or Foreign Object Damage (FOD). To date performing an HCF life assessment for the entire rotor system has been too costly in analysis time to be practical. Although the substantial run-time has previously precluded a full-rotor probabilistic analysis, reduced order models make this process tractable as demonstrated in this work. The system model includes frequency prediction, modal stress variation, mistuning amplification, FOD effect, and random material capability. The model has many random variables which are most easily handled through simple random sampling.

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“…More often than not, results obtained from such experiments have proven to be inconclusive for determining the optimum damper weight for a given bladed-disc assembly. One of the difficulties of damper weight optimisation via the experimental route has been the inevitable effects of mistuning [16][17][18][19][20][21]. There are mainly two problems associated with mistuning during damper optimisation: (i) the difficulty of distinguishing the effect of mistuning from that of the dampers and (ii) in general, not being able to instrument every blade on an assembly, which makes it very likely that the maximum response levels experienced by a single blade will not be detected.…”

Section: Introductionmentioning

confidence: 99%

Friction Damper Optimization: Simulation of Rainbow Tests

Şanlıtürk

Ewins

Elliott

et al. 1999

Journal of Engineering for Gas Turbines and Power

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Friction dampers have been used to reduce turbine blade vibration levels for a considerable period of time. However, optimal design of these dampers has been quite difficult due both to a lack of adequate theoretical predictions and to difficulties in conducting reliable experiments. One of the difficulties of damper weight optimization via the experimental route has been the inevitable effects of mistuning. Also, conducting separate experiments for different damper weights involves excessive cost. Therefore, current practice in the turbomachinery industry has been to conduct so-called “rainbow tests” where friction dampers with different weights are placed between blades with a predefined configuration. However, it has been observed that some rainbow test results have been difficult to interpret and have been inconclusive for determining the optimum damper weight for a given bladed-disk assembly. A new method of analysis—a combination of the harmonic balance method and structural modification approaches—is presented in this paper for the analysis of structures with friction interfaces and the method is applied to search for qualitative answers about the so-called “rainbow tests” in turbomachinery applications. A simple lumped-parameter model of a bladed-disk model was used and different damper weights were modeled using friction elements with different characteristics. Resonance response levels were obtained for bladed disks with various numbers of blades under various engine-order excitations. It was found that rainbow tests, where friction dampers with different weights are used on the same bladed-disk assembly, can be used to find the optimum damper weight if the mode of vibration concerned has weak blade-to-blade coupling (the case where the disk is almost rigid and blades vibrate almost independently from each other). Otherwise, it is very difficult to draw any reliable conclusion from such expensive experiments.

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On tuned bladed disk dynamics: Some aspects of friction related mistuning

Cited by 22 publications

References 17 publications

Efficient computational techniques for mistuning analysis of bladed discs: A review

Efficient computational techniques for mistuning analysis of bladed discs: A review

Probabilistic Rotor Life Assessment Using Reduced Order Models

Friction Damper Optimization: Simulation of Rainbow Tests

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