Bibliographies thématiques / Aeromechanical characterization

Littérature scientifique sur le sujet « Aeromechanical characterization »

Auteur : Grafiati
Publié le 10 mars 2023

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Articles de revues sur le sujet "Aeromechanical characterization"

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Masarati, Pierangelo, Giuseppe Quaranta et Michael Jump. « Experimental and numerical helicopter pilot characterization for aeroelastic rotorcraft–pilot coupling analysis ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 227, no 1 (16 décembre 2011) : 125–41. http://dx.doi.org/10.1177/0954410011427662.

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Pilot–vehicle interaction represents a critical aspect of aircraft design. Very low-frequency, voluntary although unintentional interaction has been extensively investigated in fixed and rotary wing aeromechanics. Higher frequency, involuntary and thus passive interaction received similar attention in fixed wing aeromechanics, but not as much for rotary wing. The results of an experimental campaign for the characterization of the passive behaviour of rotorcraft pilots' biomechanics are presented. A flight simulator has been used to excite human subjects. The accelerations of their limbs and the motion induced by the vibrations of the limbs in the control inceptors have been recorded. The vertical, longitudinal and lateral directions have been independently excited, while measuring the motion of the arm directly involved in the control inceptor mostly affected by motion in each direction, namely the left and the right arms for the collective and the cyclic sticks, respectively. The frequency domain response has been evaluated; resulting noteworthy behaviour is discussed, addressing its relevance in modelling the passive behaviour of pilots within the bioaeroservoelastic rotorcraft analysis. The measurements of human body impedance, under realistic cockpit motion, are used to identify the direct transfer functions between the motion of the seat and the controls inadvertently fed back into the rotorcraft.
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Thèses sur le sujet "Aeromechanical characterization"

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Peruzzi, Lorenzo. « Aeromechanical characterization strategy for high pressure steam turbines ». Doctoral thesis, 2018. http://hdl.handle.net/2158/1127996.

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The thesis deals with a viable strategy of aeromechanical characterization of steam turbine blades for high pressure stages for industrial application In the first part of the work, the effects related to the fludo-structure interaction for the evaluation of aerodynamic damping are taken into consideration. In the second part the effects of the multi-row environment for the evaluation of the forcing effect of the adjacent stators on the rotor blade are studied. In confirmation of the strategy developed in the first part of the thesis, the work ends with the evaluation of aerodynamic damping in multi-rows environment, taking into consideration not only the unsteadiness related to the blade modeshape, but also those due to the interaction of wakes and potential fields of the stators adjacent to the rotor blade under examination.
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Actes de conférences sur le sujet "Aeromechanical characterization"

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Mariottini, Marco, Nicola Pieroni, Pietro Bertini, Beniamino Pacifici et Alessandro Giorgetti. « Wheel Box Test Aeromechanical Verification of New First Stage Bucket With Integrated Cover Plates for MS5002 GT ». Dans ASME Turbo Expo 2019 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90075.

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Abstract In the oil and gas industry, manufacturers are continuously engaged in providing machines with improved performance, reliability and availability. First Stage Bucket is one of the most critical gas turbine components, bearing the brunt of very severe operating conditions in terms of high temperature and stresses; aeromechanic behavior is a key characteristic to be checked, to assure the absence of resonances that can lead to damage. Aim of this paper is to introduce a method for aeromechanical verification applied to the new First Stage Bucket for heavy duty MS5002 gas turbine with integrated cover plates. This target is achieved through a significantly cheaper and streamlined test (a rotating test bench facility, formally Wheel Box Test) in place of a full engine test. Scope of Wheel Box Test is the aeromechanical characterization for both Baseline and New bucket, in addition to the validation of the analytical models developed. Wheel Box Test is focused on the acquisition and visualization of dynamic data, simulating different forcing frequencies, and the measurement of natural frequencies, compared with the expected results. Moreover, a Finite Elements Model (FEM) tuning for frequency prediction is performed. Finally, the characterization of different types of dampers in terms of impact on frequencies and damping effect is carried out. Therefore, in line with response assessment and damping levels estimation, the most suitable damper is selected. The proposed approach could be extended for other machine models and for mechanical audits.
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Peruzzi, Lorenzo, Juri Bellucci, Lorenzo Pinelli, Andrea Arnone, Lorenzo Arcangeli, Lorenzo Cosi et Marco Mazzucco. « Numerical Aerodynamic Damping Evaluation of High-Pressure Steam Turbine Blades for Aeromechanical Characterization ». Dans ASME Turbo Expo 2016 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56378.

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A validated non-linear uncoupled method for flutter stability analysis was employed to estimate the aerodynamic damping of an HP (High-Pressure) steam turbine blade row. Usually such blade rows are not affected to flutter instability problems, yet an estimation of the aerodynamic damping can be useful for an accurate aeromechanical characterization of these kind of blade rows. The geometry under investigation is a typical steam turbine blade row at design point. Computational aeroelastic analyses are performed on the more relevant modeshape, sampling the nodal diameters, in order to well describe the typical aeroelastic stability curve. The presence of the tip shroud implies a strong mechanical coupling between adjacent blades resulting in complex modeshapes with high frequency, significantly different from those usually analyzed in the flutter analysis. The results in term of aerodynamic damping curves are rather different from the usually sinusoidal shape. This is due to the large variation of the frequency over the analyzed nodal diameters, especially at low nodal diameters range. This results are useful to give a better insight in the aeroelastic response of this type of blades.
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Pinelli, Lorenzo, Federico Vanti, Lorenzo Peruzzi, Andrea Arnone, Andrea Bessone, Claudio Bettini, Roberto Guida, Michela Marré Brunenghi et Vaclav Slama. « Aeromechanical Characterization of a Last Stage Steam Blade at Low Load Operation : Part 2 — Computational Modelling and Comparison ». Dans ASME Turbo Expo 2020 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15409.

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Abstract This paper is part of a two-part publication that aims to experimentally and numerically evaluate the aerodynamic and mechanical damping of a last stage ST blade at low load operation. A three-stage downscaled steam turbine with a snubbered last stage moving blade LSMB has been tested in the T10MW test facility of Doosan Skoda Power R&D Department in the context of the FLEXTURBINE European project (Flexible Fossil Power Plants for the Future Energy Market through new and advanced Turbine Technologies). Aerodynamic and flutter simulations of different low load conditions have been performed. The acquired data are used to validate the unsteady CFD approach for the prediction of the aerodynamic damping in terms of logarithmic decrement. Numerical results have been achieved through an upgraded version of the URANS CFD solver, selecting appropriate and robust numerical setups for the simulation of very low load conditions, such as increased condenser pressure at the exhaust hood outlet. The numerical methods for blade aerodamping estimation are based on the computation of the unsteady pressure response caused by the row vibration. They are usually classified in time-linearized, harmonic balance and non-linear approaches both in frequency and time domain. The validation of all these methods historically started in the field of aeronautical low-pressure turbines and has been gradually extended to compressor blades and steam turbine rows. For the analysis of a steam turbine last rotor blade operating at strong part load conditions, non-linear methods are recommended as these approaches are able to deal with strong nonlinear phenomena such as shock waves and massive flow separations inside the domain. Experimental data have been used to separate the contributions of mechanical and aerodynamic damping, extrapolating to zero mass flow the total measured damping. Finally, the comparisons between the aerodynamic damping coming from measurements and CFD results have been reported in order to highlight the capability to properly predict the last stage blade flutter stability at low load conditions. Such comparisons confirms the flutter free design of the new snubbered LSMB blade.
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Bessone, A., R. Guida, M. Marrè Brunenghi, S. Patrone, L. Carassale, Z. Kubin, A. Arnone et L. Pinelli. « Aeromechanical Characterization of a Last Stage Steam Blade at Low Load Operation : Part 1 — Experimental Measurements and Data Processing ». Dans ASME Turbo Expo 2020 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15450.

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Abstract This paper is the first of a two-part publication that aims to experimentally evaluate, simulate and compare the aerodynamic and mechanical damping for a last stage steam turbine rotor blade at part load operation. Resulting strong off-design partial load regimes expose the last stage moving blade (LSMB) to the possible onset of aero-elastic instabilities, such as stalled and un-stalled flutter. This interaction can lead to asynchronous blade vibrations and then the risk of blade failures for high cycle fatigue. In this framework, it is necessary to develop and validate new tools for extending operating ranges, controlling non-synchronous phenomenon and supporting the design of new flutter resistant LSMB. To this end, a 3-stage downscaled steam turbine with a snubbered LSMB was designed by Ansaldo Energia and tested in the T10MW test facility of Doosan Skoda Power R&D Department within the FlexTurbine European project. The turbine was operated in a wet steam environment at very low volume flow conditions simulating different part load regimes. The steady flow field throughout the LSMB was characterized and the occurrence of flutter was investigated by inducing the blade resonance through an AC magnet excitation and measuring the overall damping. The results presented in this paper indicate that the blade always operates over the flutter stability margin validating this new blade design. In the second part of this work, the mechanical and aerodynamic contribution to the damping will be separated in order to validate the aerodynamic damping prediction of an upgraded CFD tool, already adopted in the design phase of the blade at design point.
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Lottini, Fabrizio, Andrea Agnolucci, Lorenzo Pinelli, Roberto Pacciani, Lorenzo Toni, Alberto Guglielmo et Angelo Grimaldi. « Impact of Operating Conditions on Rotor/Stator Interaction of a High-Pressure Ratio Centrifugal Compressor ». Dans ASME Turbo Expo 2022 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82108.

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Abstract The current design trend of centrifugal compressors is aimed at obtaining compact machines with high pressure ratios and performance. This leads to high circumferential speeds and lighter components, thus increasing static stresses and dynamic forcing due to rotor/stator interactions. Therefore, the aerome-chanical characterization of these machines is a fundamental step of the design chain. This paper presents an in-depth aerome-chanical study of a high-pressure ratio centrifugal compressor using CFD. Firstly, the computational setup is validated against the experimental data; then, the same numerical setup is used to characterize the aeromechanical interactions between the impeller and the upstream and downstream static components. The URANS simulations are carried out at three different operating points (near stall, design, near choke), and the unsteady flow field is time and space decomposed showing higher forcing functions at near stall and near choke conditions with respect to the design point, as confirmed by the experimental acquisitions. The presented results highlight the importance of extending the aeromechanical evaluations to different operating points in order to avoid unexpected vibration responses when operating at off-design conditions. Finally, by virtue of an acoustic post-processing techniques, the unsteady pressure coupling in the inter-row region is analyzed to discern the main sources of the overall unsteady interaction.
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