Contribution to Free and Forced Vibration Analysis of an Intentionally Mistuned Blisk

Schoenenborn, Harald; Junge, Michael; Retze, Ulrich

doi:10.1115/gt2012-68683

Cited by 18 publications

(11 citation statements)

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“…The effect of mistuning on the forced response of a rotor with aerodynamic damping is more complicated, and changes substantially with respect to the uniform material damping case. There is even the possibility of having a reduction (by a factor of 2 or more) of the forced response vibration amplitude by the effect of mistuning, as it has been reported in [11,12] and found in many configurations [13,14,15,16]. The reason for this change in the effect of mistuning relies in the fact that the aerodynamic damping has different values for the different travelling wave (TW) modes of the tuned structure.…”

Section: Introductionmentioning

confidence: 98%

Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping

Martel

Sánchez-Álvarez

2017

Journal of Sound and Vibration

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Mistuning can dangerously increase the vibration amplitude of the forced response of a turbomachinery rotor. In the case of damping coming from aerodynamic effects the situation is more complicated because the magnitude of the damping changes for the different travelling wave modes of the system. This damping variability modifies the effect of mistuning, and it can even result in a reduction of the mistuned forced response amplitude below that of the tuned case (this is not possible in the usual case of constant material damping). In this paper the Asymptotic Mistuning Model (AMM) methodology is used to analyze this situation. The AMM is a reduced order model that is systematically derived from the mistuned bladed disk full model using a perturbative procedure based on the small size of the mistuning and the damping. The AMM allows to derive a very simple expression for an upper bound of the maximum amplification factor of the vibration amplitude that the system can experience (an extension of the well known Whitehead 1966 result to include the effect of non-uniform aerodamping). This new upper bound gives information on the mechanisms involved in the amplification/reduction of the mistuned response: (i) the number of modes participating in the response, and (ii) the ratio between the aerodamping of the directly forced mode and that of the of the rest of the modes. A FEM of a mistuned bladed disk is also used to verify the AMM predictions for several different forcing configurations, and both results show a very good quantitative agreement.

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Section: Introductionmentioning

confidence: 98%

Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping

Martel

Sánchez-Álvarez

2017

Journal of Sound and Vibration

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“…A variety of approaches have now been documented. Some authors [15,16] measured the surface of the manufactured blades using white light stripe projection. In doing so, they directly countered the geometric manufacturing tolerance as a presumed cause of the mistuning.…”

Section: Introductionmentioning

confidence: 99%

Effective Mistuning Identification Method of Integrated Bladed Discs of Marine Engine Turbochargers

Píštěk

Kučera

Fomin

et al. 2020

JMSE

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Radial turbine and compressor wheels form essential cornerstones of modern internal combustion engines in terms of economy, efficiency and, in particular, environmental compatibility. As a result of the introduction of exhaust gas turbochargers in the extremely important global market for diesel engines, higher engine efficiencies are possible, which in turn reduce fuel consumption. The associated reduced exhaust emissions can answer questions that results from environmentally relevant aspects of the engine development. In shipping, the international Maritime Organisation (IMO) prescribes the step-by-step reduction of nitrogen oxide and other types of emissions. To reduce these emissions, various systems are being developed, in which turbochargers are an important part. The requirements for the reliability and service life of turbochargers are constantly increasing. Turbocharger blade vibration is one of the most important problems to be solved when designing the rotors. In the case of real rotors, so-called mistuning arises, which is a slight deviation of the properties of the individual blades from the design parameters. The article deals with an effective method of mistuning identification for cases of integrated bladed discs of marine engine turbochargers. Unlike approaches that use costly scanning laser Doppler vibrometers, this method is based on using only a simple laser vibrometer in combination with a computational model of the integrated bladed disc. The added value of this method is, in particular, a significant reduction in the cost of laboratory equipment and a reduction in the time required to obtain the results.

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“…Recently, efforts have been spent to mitigate the forced response by means of employing intentional mistuning patterns. This has proved to be a promising way by both Petrov [8] and Schoenenborn et al [9] if first the dedicated travelling wave mode of the tuned counterpart is weakly damped compared to most of the other travelling wave modes and second that sufficiently high differences are existing between the maximum and the minimum of inter blade phase angle-dependent aerodynamic modal damping ratios. Similar results are achieved in [10] for a high pressure compressor blisk, where a mistuning pattern has been derived by employing genetic algorithms which effects a forced response reduction down to a level of 52 % compared to the perfect design with identical blades.…”

Section: Introductionmentioning

confidence: 99%

Vibration analysis of an axial turbine blisk with optimized intentional mistuning pattern

Beirow

Figaschewsky

Kühhorn

et al. 2019

Journal of Sound and Vibration

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Aiming to limit the forced response of an axial turbine blisk for ship Diesel engine applications efforts have been made to increase the aerodynamic damping contribution for the most critical modes. In this regard the potential of intentional mistuning is investigated since it offers the opportunity to ensure a safe operation without a severe loss of aerodynamic performance. Genetic algorithms have been chosen to derive an optimized mistuning pattern. In order to keep the manufacturing effort within a limit only two possible blade geometries are allowed which means that an integer optimization problem has been formulated. For the purpose of demonstrating the benefit of the intentional mistuning pattern found, two blisk prototypes have been manufactured: One with and another one without employing intentional mistuning for purposes of comparison. Furthermore, this offers the opportunity for an experimental determination of mistuning being really manufactured and other modal properties as well. The experimental data basis is employed to update structural models which are well suited to demonstrate the forced response reduction under operational conditions.

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Contribution to Free and Forced Vibration Analysis of an Intentionally Mistuned Blisk

Cited by 18 publications

References 0 publications

Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping

Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping

Effective Mistuning Identification Method of Integrated Bladed Discs of Marine Engine Turbochargers

Vibration analysis of an axial turbine blisk with optimized intentional mistuning pattern

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