Investigation on laser shock peening capability by FE simulation

Laser shock peening is a technique similar to shot peening that imparts compressive residual stresses in materials for improving fatigue resistance. The ability to use a high energy laser pulse to generate shock waves, inducing a compressive residual stress field in metallic materials, has applications in multiple fields such as turbo-machinery, airframe structures, and medical appliances. The transient nature of the LSP phenomenon and the high rate of the laser's dynamic make real time in-situ measurement of laser/material interaction very challenging. For this reason and for the high cost of the experimental tests, reliable analytical methods for predicting detailed effects of LSP are needed to understand the potential of the process. Aim of this work has been the prediction of residual stress field after Laser Peening process by means of Finite Element Modeling. The work has been carried out in the Stress Methods department of Airbus Operations GmbH (Hamburg) and it includes investigation on compressive residual stresses induced by Laser Shock Peening, study on mesh sensitivity, optimization and tuning of the model by using physical and numerical parameters, validation of the model by comparing it with experimental results. The model has been realized with Abaqus/Explicit commercial software starting from considerations done on previous works. FE analyses are “Mesh Sensitive”: by increasing the number of elements and by decreasing their size, the software is able to probe even the details of the real phenomenon. However, these details, could be only an amplification of real phenomenon. For this reason it was necessary to optimize the mesh elements' size and number. A new model has been created with a more fine mesh in the trough thickness direction because it is the most involved in the process deformations. This increment of the global number of elements has been paid with an "in plane" size reduction of the elements far from the peened area in order to avoid too high computational costs. Efficiency and stability of the analyses has been improved by using bulk viscosity coefficients, a merely numerical parameter available in Abaqus/Explicit. A plastic rate sensitivity study has been also carried out and a new set of Johnson Cook's model coefficient has been chosen. These investigations led to a more controllable and reliable model, valid even for more complex geometries. Moreover the study about the material properties highlighted a gap of the model about the simulation of the surface conditions. Modeling of the ablative layer employed during the real process has been used to fill this gap. In the real process ablative layer is a super thin sheet of pure aluminum stuck on the masterpiece. In the simulation it has been simply reproduced as a 100µm layer made by a material with a yield point of 10MPa. All those new settings has been applied to a set of analyses made with different geometry models to verify the robustness of the model. The calibration of the model with the experimental results was based on stress and displacement measurements carried out on the surface and in depth as well. The good correlation between the simulation and experimental tests results proved this model to be reliable.

Separation control by means of oriented DBD plasma actuators: an experimental analysis in a wind tunnel

This thesis provides an experimental analysis of the effectiveness of oriented DBD plasma actuators over a NACA 0015 airfoil at low Reynolds numbers. Tests were performed in partnership with the Department of Electrical Engineering of Bologna University, in the wind tunnel of the Applied Aerodynamics Laboratory of Aerospace Engineering faculty. Lift coefficient measurements were carried out in order to verify how an oriented plasma jet succeeds in prevent boundary layer separation. Both actuators’ chord wise position and plasma jet orientation angle have been investigated to examine which configurations lead to the best results. A particular attention has been paid also to the analysis of results in steady and unsteady plasma actuation. Questa tesi offre un’analisi sperimentale sull’efficacia di attuatori al plasma orientabili, basati su una tecnologia DBD, installati su un profilo alare NACA 0015, a bassi numeri di Reynolds. Le prove sono state condotte in collaborazione con il Dipartimento di Ingegneria Elettrica dell’Università di Bologna, nella galleria del vento del Laboratorio di Aerodinamica Applicata della Facoltà di Ingegneria Aerospaziale di Forlì. Per verificare come un getto orientabile di plasma riesca a prevenire la separazione dello strato limite, sono state eseguite misure sul coefficiente di portanza. Sono state indagate sia la posizione degli attuatori lungo la corda che l’angolo con cui è orientato il getto di plasma, per vedere quali configurazioni conducono ai migliori risultati. Una particolare attenzione è stata riservata all’analisi dei risultati ottenuti con plasma continuo e pulsato.

Laser shock peening treatment to control and moderate fatigue crack growth in aircraft structure based on residual stress engineering approach

Laser Shock Peening (LSP) is a surface enhancement treatment which induces a significant layer of beneficial compressive residual stresses of up to several mm underneath the surface of metal components in order to improve the detrimental effects of the crack growth behavior rate in it. The aim of this thesis is to predict the crack growth behavior in metallic specimens with one or more stripes which define the compressive residual stress area induced by the Laser Shock Peening treatment. The process was applied as crack retardation stripes perpendicular to the crack propagation direction with the object of slowing down the crack when approaching the peened stripes. The finite element method has been applied to simulate the redistribution of stresses in a cracked model when it is subjected to a tension load and to a compressive residual stress field, and to evaluate the Stress Intensity Factor (SIF) in this condition. Finally, the Afgrow software is used to predict the crack growth behavior of the component following the Laser Shock Peening treatment and to detect the improvement in the fatigue life comparing it to the baseline specimen. An educational internship at the “Research & Technologies Germany – Hamburg” department of AIRBUS helped to achieve knowledge and experience to write this thesis. The main tasks of the thesis are the following: •To up to date Literature Survey related to “Laser Shock Peening in Metallic Structures” •To validate the FE model developed against experimental measurements at coupon level •To develop design of crack growth slowdown in Centered Cracked Tension specimens based on residual stress engineering approach using laser peened strip transversal to the crack path •To evaluate the Stress Intensity Factor values for Centered Cracked Tension specimens after the Laser Shock Peening treatment via Finite Element Analysis •To predict the crack growth behavior in Centered Cracked Tension specimens using as input the SIF values evaluated with the FE simulations •To validate the results by means of experimental tests

Daily modulation of the Heat shock proteins (Hsps) in three different species of scleractinian corals

Temperature and light intensity is the most important environmental parameters that influence circadian cycle of scleractinian corals. In this context, modulation of the biomarkers Hsp60 and Hsp70 in situ was investigated by three different healthy coral species (Acropora tenuis, Echinopora lamellosa and Porites lobata) not stress induced during time course of 24h. Significance species-specific modulation under natural conditions is displayed by all corals under study. A strong fluctuation in Hsps expression is shown by the most susceptible, branched coral A. tenuis, instead of fine and low modulation is shown by the massive coral P. lobata. From the results match between morphology difference and physiological difference response its suggest and similarity pattern between Hsps with different cellular compartments location is suggested too. Starting from this study health of coral reefs could be able to be investigated in the future with a set of biomarkers composed also by Hsps which will be set up.

Stability of the tunnel face reinforced by bolts under seepage flow conditions

Il presente lavoro tratta la stabilità del fronte di scavo, rinforzato con barre di consolidamento ed interessato da drenaggi in avanzamento, di gallerie sotto falda in rocce tenere o terreni. Tale studio è stato sviluppato dal progetto di Tesi attraverso l’analisi all’equilibrio limite che approssima il fronte di scavo con un rettangolo e considera un meccanismo di rottura composto da un cuneo, a tergo del fronte, caricato da un prisma. Il metodo descritto consente di tenere conto dell’effetto stabilizzante delle barre, mediante una distribuzione della pressione di supporto non uniforme. Nel caso di gallerie sotto falda, lo stesso metodo permette inoltre di considerare l’effetto destabilizzante dei gradienti idraulici. Sono state ricavate soluzioni analitiche per la valutazione della stabilità, ed implementate successivamente nel software di analisi numerica MATLAB. Dalle analisi condotte è emerso che il numero minimo di barre per garantire la stabilità del fronte di scavo è in molti casi elevato e risulta impossibile da porre in opera in terreni scarsamente coesivi o in gallerie sotto elevati battenti d’acqua. Per risolvere questa situazione si può prevedere l’inserimento di drenaggi in avanzamento, con lo scopo di diminuire i gradienti idraulici nei pressi del fronte della galleria. Il modello che descrive il nuovo andamento dei carichi idraulici, considerando la presenza di dreni, è stato realizzato con il software commerciale agli elementi finiti COMSOL. Una volta determinati gli andamenti dei carichi idraulici, sono stati condotti studi parametrici sull’effetto dei dreni combinato con gli elementi di rinforzo. Dopo tali analisi sono stati ricavati nomogrammi adimensionali che tengano conto della presenza contemporanea delle barre e dei dreni. Tali diagrammi costituiscono uno strumento utile e valido per la progettazione del rinforzo del fronte di scavo. Infine sono stati realizzati confronti fra casi di studio reali e risultati ottenuti dal modello.

Modelli Input-Output: un'analisi simultanea di shock domanda e offerta

La tesi analizza il modello Input-Output, introdotto da Leontief nel 1936, per studiare la reazione dei sistemi industriali di Germania, Spagna ed Italia alle restrizioni imposte dai governi per limitare la diffusione della pandemia da COVID-19. Si studiano le economie considerando gli scambi tra i settori produttivi intermedi e la domanda finale. La formulazione originale del modello necessita diverse modifiche per descrivere realisticamente le reti di produzione e comunque non è del tutto esaustiva in quanto si ipotizza che la produttività dei sistemi sia sempre tale da soddisfare pienamente la domanda che giunge per il prodotto emesso. Perciò si introduce una distinzione tra le variabili del problema, assumendo che alcune componenti di produzione siano indipendenti dalla richiesta e che altre componenti siano endogene. Le soluzioni di questo sistema tuttavia non sempre risultano appartenenti al dominio di definizione delle variabili. Dunque utilizzando tecniche di programmazione lineare, si osservano i livelli massimi di produzione e domanda corrisposta in un periodo di crisi anche quando i sistemi non raggiungono questa soglia poiché non pienamente operativi. Si propongono diversi schemi di razionamento per distribuire tra i richiedenti i prodotti emessi: 1) programma proporzionale in base alle domande di tutti i richiedenti; 2) programma proporzionale in base alle richieste, con precedenza ai settori intermedi; 3) programma prioritario in cui vengono riforniti i settori intermedi in base alla dimensione dell’ordine; 4) programma prioritario con fornitura totale degli ordini e ordine di consegna casuale. I risultati ottenuti dipendono dal modello di fornitura scelto, dalla dimensione dello shock cui i settori sono soggetti e dalle proprietà della rete industriale, descritta come grafo pesato.

Structural health of a road tunnel intersecting a large and active rockslide

This work presents the case of the San Lorenzo road tunnel, a transportation infrastructure located in the northern part of Italy, involved in the so-called Passo della Morte landslide. This tunnel crosses a large rockslide characterized by slow movements. Damages like water seepage inside the tunnel and concrete lining detachments have surfaced through the years, increasing the risk. This work develops the objective of tracing back the landslide-induced stresses directly responsible for the cracks’ pattern on the most damaged segments of the tunnel. The first section of this work gives information about the global framework: site geography and its strategic relevance, geological setting, hydrological and climate conditions will be provided. The road tunnel infrastructure and its interaction with the landslide phenomena will be discussed together with the active monitoring system, which has been working for more than 20 years. In the second part the several steps and tools used to add more details about the road damages are reported. A visualization of the actual state of the most damaged portions of the road has been reached. Then the attention has been addressed to the stresses acting on the road tunnel’s aforesaid portions, developing a FEM model of a section of the tunnel through a selected software. This latter process can be deemed as a beginning for further developments. Some preliminary results are shown to demonstrate the goodness of the assumptions made. The possible future set by this work aims at constant enlargement of information to be provided to the FEM software, and at the validation of the obtained results through the monitoring data interpretative tools.

Numerical Analysis and Redesign of a High Speed Linear Cascade Wind Tunnel for Aircraft Gas Turbine Engines Testing

Linear cascade testing serves a fundamental role in the research, development, and design of turbomachines as it is a simple yet very effective way to compute the performance of a generic blade geometry. These kinds of experiments are usually carried out in specialized wind tunnel facilities. This thesis deals with the numerical characterization and subsequent partial redesign of the S-1/C Continuous High Speed Wind Tunnel of the Von Karman Institute for Fluid Dynamics. The current facility is powered by a 13-stage axial compressor that is not powerful enough to balance the energy loss experienced when testing low turning airfoils. In order to address this issue a performance assessment of the wind tunnel was performed under several flow regimes via numerical simulations. After that, a redesign proposal aimed at reducing the pressure loss was investigated. This consists of a linear cascade of turning blades to be placed downstream of the test section and designed specifically for the type of linear cascade being tested. An automatic design procedure was created taking as input parameters those measured at the outlet of the cascade. The parametrization method employed Bézier curves to produce an airfoil geometry that could be imported into a CAD software so that a cascade could be designed. The proposal was simulated via CFD analysis and proved to be effective in reducing pressure losses up to 41%. The same tool developed in this thesis could be adopted to design similar apparatuses and could also be optimized and specialized for the design of turbomachines components.

Development and Automatization of a Planar Jet Wind Tunnel for the X-wire Calibration

The scope of this study is to design an automatic control system and create an automatic x-wire calibrator for a facility named Plane Air Tunnel; whose exit creates planar jet flow. The controlling power state as well as automatic speed adjustment of the inverter has been achieved. Thus, the wind tunnel can be run with respect to any desired speed and the x-wire can automatically be calibrated at that speed. To achieve that, VI programming using the LabView environment was learned, to acquire the pressure and temperature, and to calculate the velocity based on the acquisition data thanks to a pitot-static tube. Furthermore, communication with the inverter to give the commands for power on/off and speed control was also done using the LabView VI coding environment. The connection of the computer to the inverter was achieved by the proper cabling using DAQmx Analog/Digital (A/D) input/output (I/O). Moreover, the pressure profile along the streamwise direction of the plane air tunnel was studied. Pressure tappings and a multichannel pressure scanner were used to acquire the pressure values at different locations. Thanks to that, the aerodynamic efficiency of the contraction ratio was observed, and the pressure behavior was related to the velocity at the exit section. Furthermore, the control of the speed was accomplished by implementing a closed-loop PI controller on the LabView environment with and without using a pitot-static tube thanks to the pressure behavior information. The responses of the two controllers were analyzed and commented on by giving suggestions. In addition, hot wire experiments were performed to calibrate automatically and investigate the velocity profile of a turbulent planar jet. To be able to analyze the results, the physics of turbulent planar jet flow was studied. The fundamental terms, the methods used in the derivation of the equations, velocity profile, shear stress behavior, and the effect of vorticity were reviewed.