Literatura científica selecionada sobre o tema "Vulcain (Firm)"

Recycled polypropylene (PP) and sisal fiber, which are available in abundant ammount, can be used for producing a composite, a new material that reduce production costs and environmental damage. The new materials will be used for manufacturing floor tiles that are environmentally friendly, light but still technically qualified, and are expected to replace the ceramic tiles that are relatively heavy. However, the drawbacks in the application, natural fiber is a combustible material and it absorbs water easily (hydrophilic). To overcome these obstacles then a study on fiber chemical treatment was conducted. The purpose of this study is to determine the effect of chemical treatments on sisal fibers for fire resistance capability, the moisture resistance and tensile properties of the composites. So these composite materials can replace ceramic tile that is used for houses, hotels, ships and so on. In this research, sisal fibers with length of 10 mm were treated by NaOH and followed by Vulcan AF21 (Vulcan) of 5%, 10% and 20% for 2-hours for fire resistance, and other treatment with Acrylic acid (AA) of 1%, 5% and 10% for 1 hour at 50°C for moisture resistance. Fiber material that has been chemically treated is mixed with recycled PP. Test specimens were made in hot pressed. Fire resistance testing was conducted based on ASTM D635 standards, water absorption testing (ASTM D570), and tensile testing. The result shows that the higher the percentage of Vulcan treatment on sisal fiber is of 5%, 10% and 20%, the linear burning rate, the percentage of weight loss and weight loss rate of sisal fiber polypropylene composites decreases which means the composite is more resistant to fire. In general, the increase percentage of Vulcan on treatment sisal fibers shows a decrease in tensile strength and modulus of elasticity but a slight increase tensile strain of composite. Fiber treated with acrylic acid (AA) experienced a reduction of water absorption compared to the untreated of fiber composites.

In this paper, we report the first results of dosimetric analysis of broad-spectrum, multi-MeV laser accelerated proton beams obtained during experiments at the Rutherford Appleton Laboratory using the Chirped Pulse beam of the Vulcan laser. The spectra are retrieved by a numerical analysis that allows the reconstruction of the energetic profile of the proton beam from data obtained using radiochromic film.

The present work deals with numerical simulations concerning the international benchmark “Vulcain tests on 3 Walls” regarding fire tests conducted in CSTB in Paris, France. To this aim, sequentially-coupled thermo-mechanical analyses have been performed on three reinforced concrete walls, characterized by different load levels and boundary conditions. The numerical results show that the imposed compressive load and boundary conditions significantly influence the magnitude of the displacements. In the case of simply supported walls, the wall with the lower load level exhibited a gradual and monotonic increase of the displacements at mid-height (both in the tests and in the numerical analyses), while the wall with the higher load level exhibited a displacement reversal due to second-order effects after approximately 60 minutes of fire exposure. This reversal, which was obtained in the analyses, was not observed in the test. Load bearing capacity of all the three specimen walls was maintained in such a way that the collapse did not take place during two hours of fire exposure.

abstract: Ben Jonson's 1623 poem "An Execration upon Vulcan" responds to a fire in his house, which seemingly destroyed some books and papers. Scholarly interest in this work has largely been confined to what biographical information it reveals. Yet this poem is in dialogue with Cervantes's Don Quixote , Rabelais's Pantagruel , and Donne's The Courtier's Library , and it engages with the genre of the mock library catalogue. By bringing together these works, the essay not only contributes to ongoing study of such Jonsonian concerns as censorship, interpretation, and the value of learning but also highlights his interest in contemporary European comic literature and the closeness of his association with Donne. It sheds light on early modern literature's self-consciousness about the library as a malleable concept, a self-consciousness with important methodological implications for critics and historians of the period.

This paper reports on the development of a general-purpose Eurocode-compliant component-based connection finite element for steel-to-steel joints in fire. The development begins by utilising the temperature-dependent connection component characteristics previously developed at the University of Sheffield to create a component-based connection finite element to model flush endplate connections. Subsequently the element was extended to a new connection type with high ductility, the reverse channel. The component models have been developed for the reverse channel under tension and compression. The element has been incorporated into the nonlinear global structural analysis program Vulcan, in which it has been used along with a static-dynamic formulation. The use of the element is illustrated by modelling a fire test at the University of Manchester in which reverse channel connections were used.

ABSTRACTThis essay examines the evidence for the Domitianic ‘Arae Incendii Neroniani’, a presumed set of monumental altars dedicated to Vulcan in fulfilment of a vow dating back to the Neronian Fire ofa.d. 64. A close reading of the text of the dedicatory inscription creates a framework for exploring the larger historical and cultural context of these monuments, which offer a significant illustration of Flavian rhetoric concerning Rome's post-Neronian transformation. Reaffirming Julio-Claudian notions of civic identity, collective memory, and the ruler's privileged relationship with the gods, the Arae also constitute a conspicuous form of posthumous reproach to Nero.

Twenty-five years ago, in summer 1998, the first paper introducing the thin-film rotating disk electrode (TFRDE) method was published in the Journal of the Electrochemical Society [1]. At this time, we demonstrated that by preparing a thin layer of a supported Pt/Vulcan catalyst mixed with a small amount of Nafion could reliably be coated on top of a glassy carbon disk, electrochemical reactions like the hydrogen oxidation reaction could be measured on an RDE taking advantage of the well-known mass-transport conditions of an RDE. By keeping the layer thickness in the range of 1 micrometer, additional mass-transport resistances induced by the catalyst layer/Nafion film became negligible. That is, all equations valid on an RDE could be applied without modification. Further work on the oxygen reduction reaction by using the TF Rotating Ring-Disk electrode allowed detecting peroxide formation on a supported catalyst [2]. Both publications grounded the path for catalyst development in fuel cell. The method has been used since then as a standard method for catalyst screening and characterization in both academia and industries. In addition, many researchers improved the TFRDE method within their research. The application span of the TFRDE developed from fuel cell research, oxidation of small organic molecules, to work on Li-O2 batteries, water electrolysis, and CO2 reduction. This presentation will offer a journey over the last 25 years and the application of the TFRDE technique in catalyst development and characterization. [1] T.J. Schmidt, H.A. Gasteiger, G.D. Stäb, P. Urban, D.M. Kolb, R.J. Behm Characterization of High-Surface-Area Electrocatalysts Using a Rotating Disk Electrode Configuration J. Electrochem. Soc. 145 (1998) 2354-2358 [2] U.A. Paulus, T.J. Schmidt, H.A. Gasteiger, R.J. Behm Oxygen Reduction on a High-Surface Area Pt/Vulcan Carbon Catalyst: A Thin-Film Rotating Ring-Disk Study J. Electroanal. Chem. 495 (2001) 134-145 [3] T.J. Schmidt, H.A. Gasteiger Rotating Thin-Film Method for Supported Catalysts, in Handbook of Fuel Cells: Fundamentals, Technology and Applications, Vol. 2 Part 3, W. Vielstich, H.A. Gasteiger, A. Lamm (Eds.), John Wiley & Sons, New York, 316-333 (2003)

The fire beam element method is a tool for structural fire analyses that simplifies a structure into a skeletal frame consisting of only beam and column elements. It considers a shifting neutral axis of each beam element, which is updated throughout an analysis. This method was implemented in the OpenSees software environment by adding two subclasses: one for the fire beam element added to the element class, and one for the member section, in which the neutral axis is iteratively adjusted for non-uniform temperature profiles. To validate the implemented model, three benchmark case studies were sourced from literature: (1) a heated cantilever beam with an analytical solution, (2) a steel beam in a furnace with high axial and bending forces and (3) a two-dimensional steel frame in a fire with complex behaviour such as non-linear heating, restraint and buckling. For (1) the fire beam element predicts deformations identical to an analytical solution. For (2) the fire beam element method simulates deformations with good accuracy across the entire time domain relative to experimental data, and simulations in the literature using Vulcan, although with experimental deflections typically being underestimated. For (3) fire beam element predictions are compared to experimental data and models developed in CEFICOSS, ABAQUS, SAFIR and LS-DYNA. Trends are typically accurately captured, with percentage differences varying. Runaway failure is predicted with 2 min of experimental data. A sensitivity analysis of the fire beam element model on mesh size of elements and fibres showed the runtime to be more sensitive to the number of elements than the number of fibres per element.

A norma brasileira ABNT NBR 14323:2013 apresenta um método para o dimensionamento de lajes mistas de aço e concreto em situação de incêndio. No entanto, esse procedimento não inclui o efeito do comportamento de membrana da laje. Usando a teoria de placas para grandes deslocamentos, esta pesquisa estabelece que as altas temperaturas podem induzir uma considerável ação de membrana de tração, auxiliando na segurança da laje em situação de incêndio. No desenvolvimento de uma ferramenta para o dimensionamento a partir do método analítico de lajes mistas em situação de incêndio, uma série de estudos foi desenvolvida para a análise do comportamento de membrana de tração a altas temperaturas. O método analítico mais conhecido é o método de Bailey. Comparações entre os métodos de Bailey e da ABNT NBR 14323:2013, e análises empregando os programas Vulcan e MACS+ foram realizadas. Neste trabalho, compararam-se resultados empregando o método de Bailey e do programa de computador MACS+, que teve por base o próprio método de Bailey. Como esperado, os resultados foram similares. Ainda, neste trabalho, realizaram-se alguns estudos numéricos empregando o método dos elementos finitos, por meio do programa de computador Vulcan e compararam-se resultados entre o método de Bailey e Vulcan. Uma investigação sobre possíveis simplificações da formulação da ABNT NBR 14323:2013 também foi realizada.
The Brazilian standard ABNT NBR 14323:2013 presents a method for the composite slabs fire design. However, it doesnt include the effect of the slab behaving as a membrane. Using the theory of plates for large displacements, the research establishes that high temperatures can induce a considerable tensile membrane action, assisting in the safety of the slab in fire. In developing a tool for the analytical method composite slabs fire design, some studies were made to analyze the behavior of tensile membrane at high temperatures. The most popular analytical method is the Baileys method. In this study, analysis of the Baileys methods, the Brazilian standard and the Vulcan and MACS+ software were performed and the results were compared. As expected, the results were similar. Still, in this work, there have been some numerical studies employing the finite element method, using the computer program Vulcan, and results were compared between the Baileys method and Vulcan. An investigation about possible simplifications of the formulation presented by Brazilian standard were also developed.

Ngauruhoe is an active basaltic andesite to andesite composite cone volcano at the southern end of the Tongariro volcanic complex, and most recently erupted in 1954-55 and 1974-75. These eruptions constructed the inner crater of Ngauruhoe, largely composed of 1954-55 deposits, which are the basis of this study. The inner crater stratigraphy, exposed on the southern wall, is divided into seven lithostratigraphic units (A to G), while the northern stratigraphy is obscured by the inward collapse of the crater rim. The units are, from oldest to youngest: Unit A, (17.5 m thick), a densely agglutinated spatter deposit with sharp clast outlines; Unit B, (11.2 m) a thick scoria lapilli deposit with local agglutination and scattered spatter bombs up to 1 m in length; Unit C, (6.4 m thick) a clastogenic lava deposit with lateral variations in agglutination; and Unit D, (10 m thick) a scoria lapilli with varying local agglutination. The overlying Unit E (15 cm thick) is a fine ash fallout bed that represents the final vulcanian phase of the 1954-55 eruption. Unit F is a series of six lapilli and ash beds that represent the early vulcanian episode of the 1974-75 eruption. The uppermost Unit G (averaging 10 m thick) is a densely agglutinated spatter deposit that represents the later strombolian phase of the 1974-75 eruption. Units A-D juvenile clasts are porphyritic, with phenocrysts of plagioclase, orthopyroxene, clinopyroxene, minor olivine, within a microlitic glassy groundmass. Quartzose and greywacke xenoliths are common in most units, and are derived from the underlying basement. The 1954-55 and 1974-75 eruptions are a product of a short-lived, continental arc medium-K calc-alkaline magma. The magma originated from the mantle, then filtered through the crust, undergoing assimilation and fractionation, and evolving to basaltic andesite and andesite compositions. The magma body stagnated in shallow reservoirs where it underwent further crustal assimilation and fractionation of plagioclase and olivine, and homogenisation through magma mixing. Prior to the 1954-55 eruption a more primitive magma body was incorporated into the melt. The melt homogenised and fed both the 1954-55 and 1974-75 eruptions, with a residence time of at least 20 years. The 1954-55 eruption produced alternating basaltic andesite and andesite strombolian activity and more intense fire fountaining, erupting scoria and spatter that built up the bulk of the inner crater. A period of relative quiescence allowed the formation of a cooled, solid cap rock that resulted in the accumulation of pressure due to volatile exsolution and bubble coalescence. The fracturing of the cap rock then resulted in a vulcanian eruption, depositing a thin layer of fine ash and ballistic blocks. The 1974-75 eruption commenced with the rupturing of the near-solid cap rock from the 1954-55 eruption in an explosive vulcanian blast, the result of decompressional volatile exsolution and bubble coalescence, and possible magma-water interaction. The eruption later changed to strombolian style, producing a clastogenic lava that partially flowed back into the crater.

The current dissertation, titled “Fire Response of Composite aerostructures” deals with a crucial subject of the aeronautics industry that is the fire response of composite aerostructures, more specifically the issue of interest in this work is the fuselage fire burnthrough from an external liquid jet-fuel pool fire. Other fire issues that “bother” the aeronautics industry are the fire spread inside the cabin, smoke generation and toxicity of the fumes, but these are not handled in the current dissertation. Aircraft structures are designed to withstand various loading scenarios during their operational life. These loading scenarios are associated to a great extent with normal aircraft operation (flight manoeuvres, take-off and landing). However there are situations where the aircraft structures are required to assure the safety of the passengers and crew. In the case of an emergency crash landing, the threat of an external jet-fuel fire always exists. Considering that the aircraft structure survives the impact, the survivability of the passengers and crew onboard the aircraft depends solely on the fire resistance of the aircraft structure. A measure of the fire resistance of an aircraft structure is the time needed for the flames to penetrate the fuselage and spread inside the cabin, the so-called, burn-through time. So far, the aircraft fire resistance has been extensively studied by conducting lab, medium and full scale tests. The early lab scale tests were performed by the Federal Aviation Administration (FAA) and involved the Bunsen-burner flammability test of coupons for developing fire safe interior materials. As the application of polymer materials on aircrafts kept increasing, the problem of fire burn-through due to external fire emerged. Marker was one of the first to perform full-scale fuselage burn-through tests to access the insulating performance of materials. Also a statistical analysis was performed by Cherry and Warren that accessed and analyzed data from past accidents and their work resulted in proving the importance of fuselage fire hardening and the passengers’ lives that could be saved using low-cost solutions. These works led the FAA to proposed new fire testing procedures for aircraft materials. The scope of this dissertation was to assess the performance of various structural materials in a pool-fire scenario. A simplified approach is made, approximating the pool-fire conditions with a flat panel burn-through test in accordance to the ISO2685:1998(E) Standard. The originality of the present work comes from the fact that it incorporates a multistage approach in order to investigate the behaviour and response of composite aircraft structures in the possibility of a fire event. The current approach goes down on material level in order to investigate and model the deterioration (decomposition) of the polymer composite. Thus, it investigates and proposes a methodology of how the thermophysical properties of the composite are deteriorated due to the fire event. It proceeds into developing a progressive-damage material model (material properties varying with the deterioration degree) and finally implementing this custom material model into a commercial FE package and solving the loading scenarios. Being more specific the current work begins with a quick review of the literature where incidents and work done on the burnthrough event for the past 20-30 years are summarized. It progresses then to presenting the various types of polymers used in the aircraft industry and their basic decomposition mechanisms, from the unsaturated polyesters to the epoxies and phenolics and in the end reference to the thermoplastics is made. Every organic material, hence, polymers used in aerospace applications, present a set of response characteristics when subjected to fire, specifically the heat release rate, thermal stability index, limiting oxygen index, flammability index, time-to-ignition, surface flame spread, mass loss, smoke density and smoke toxicity. Following is the backbone of this dissertation, the kinetics modelling. Two approaches are made, one simplified using single stage kinetics where the decomposition degree a is calculated based on the Arrhenius reaction theory and using the kinetic triplets (kinetic parameters) extracted from thermogravimetry, TGA, data using the Friedman multi-curve method. The second approach is more complicated and considers multi-stage decomposition of the polymer composite. Specifically a 3-stage reaction network is considered for every material, the LY-Ref, and the two modified batches, one with ammonium polyphosphate AP423 and the other both with AP423 and multi-wall carbon nanotubes MWCNT. Again the kinetic parameters, activation energy EA, frequency factor A, and reaction order n, are extracted for every step using the van Krevelen methodology. In the end using the reaction rates equations the reconstruction of the TGA curves is achieved with an error of less than 5% from the test data. Correlations that consider the material deterioration and affect the thermophysical properties of the materials are proposed. Those expressions are being developed for both of the two kinetic approaches, the single and multi stage. Another crucial part of this work is the measurement and calibration of the applied fire load. Again two fire load approaches are used, one according to the ISO2685 Standard where a propane burner was manufactured and calibrated according to the Standard for medium scale samples testing and a lab scale butane burner for small samples. The ISO2685 burner was also CFD simulated and the models calibrated against analytical expressions, ISO requirements and real measurements. The CFD simulations were performed so the heat flux or heat transfer coefficient to be extracted and used as input for the later thermal FE burnthrough models. The heat flux distribution of the lab-scale AML burner on the specimen surface was measured via a water cooled Schmit-Boelter SBG01 heat flux sensor manufactured by Hukseflux. Manufacturing and material details are presented concerning the samples used for every test campaign. Metallic (AL2024-T3) samples, CFRP neat and modified, and hybrid GLARE ones where manufactured. Also the experimental work performed is described. Cone calorimetry testing data are available, results from thermogravimetry tests, differential scanning calorimetry, and finally the burnthrough tests with both the testing apparatuses, the ISO2685 one and the AML lab-scale burner. The modelling work in this dissertation involved thermal models that were developed into a commercial FE package. It was not part of this work to develop a thermal solver so a commercial one was selected and all the developed methodology was adapted to its requirements and specifications. The boundary conditions on the models are presented both for the ‘hot’ front surface and the rear ‘cooling’ one. For the ‘hot’ one the heat flux distribution is used and for the ‘cooling’ one an equivalent convection is applied that accounts for both convective and radiative cooling. The decomposing material model is implemented into to FE solver via user defined subroutines for the single stage kinetics and the multi-stage approach. Finally the simulations were run and the results and models were compared against the available experimental results. Since so far the burnthrough response of aerostructures was limited to coupon, samples and medium size flat panels. A more realistic approach was performed by developing a mathematical model of a real size test. The certification tests conducted by the FAA are for full size fuselage sectors under the fire load of a burning jet-fuel pan pool-fire. A burning jet-fuel pool fire is a complex phenomenon on its own, combining it with a decomposing fuselage structure make the modeling approach even more difficult to simulate if not impossible. Required data for the pool-sizes under investigation were not available, so data for large external hydrocarbon pool fires from literature were used. Also, because the main characteristic of a jet-fuel (kerosene) pool fire is that the flames are not clear, on the contrary, great amount of shoot is produced making combustion modeling and radiative heat transfer to the fuselage even more of a challenge to model, it was decided to try and tackle this full-scale approach by a simplified the modeling approach. Instead of liquid fuel combustion, an equal hot air stream with mass flow, velocity and temperature properties extracted from literature correlation data was performed. Conclusively, in terms of completeness the benefit analysis performed by Cherry and Warren is presented in brief. The objective of their analysis was to assess the potential benefits, in terms of reduction of fatalities and injuries, resulting from improvements in fuselage burnthrough resistance to ground pool fires. Fire hardening of fuselages will provide benefits in terms of enhanced occupant survival and may be found to be cost beneficial if low-cost solutions can be found. The maximum number of lives saved per year in worldwide transport aircraft accidents, over the period covered by the data, if hardening measures were applied, was assessed to be 12.5 for the aircraft in its actual configuration (when the accidents occurred) and 10.5 for the aircraft configured to later airworthiness requirements. These figures are completely significant and give an extra confirmation that this work on investigating the fire response of composite aerostructures is on the right track. As the work of Cherry and Warren concluded, the fire hardening measures in order to be applicable need to be cost efficient. The concept under which this whole dissertation stepped on was to investigate the fire response of composite aerostructures and the possibility of hardening the structure itself without the use of extra protective layers that add cost and weight to the overall aircraft and its maintenance. In the end it was concluded that there is the possibility of hardening the fuselage structure by design and by material. Incorporating composites into the structure it is possible to prolong the burnthrough time at least for 4-5 minutes before auto ignition occurs on the inner side of the fuselage. Auto ignition of the inner side fuselage cabin materials is mentioned since in NONE of the burnthrough tests of the CFRP composites and the GLARE samples flame penetration was observed.
Στην παρούσα διατριβή με τίτλο «Ανάλυση της απόκρισης σύνθετων πολυμερών υλικών υπό συνθήκες φωτιάς. Εφαρμογή σε αεροπορικές κατασκευές» πραγματοποιείται εργασία στην αριθμητική προσομοίωση και πειραματική διερεύνηση της συμπεριφοράς αεροπορικών κατασκευών σε συνθήκες φωτιάς. Στην μέχρι τώρα βιβλιογραφία οι διάφοροι έλεγχοι για πιστοποίηση των αεροπορικών υλικών αλλά και των αεροσκαφών στο σύνολό τους αποτελούνταν από εκτενείς πειραματικές δοκιμές σε μεσαία κλίμακα καθώς και σε πλήρους κλίμακας κατασκευές. Οι προδιαγραφές των ελέγχων ορίζονται από την Ομοσπονδιακή Διεύθυνση Αεροπλοΐας των Ηνωμένων Πολιτειών της Αμερικής, Federal Aviation Administration FAA. Όπως γίνεται αντιληπτό πλήρους κλίμακας δοκιμές είναι χρονοβόρες αλλά και οικονομικά ασύμφορες, για τον λόγο αυτό τα τελευταία χρόνια πραγματοποιούνται προσπάθειες από την FAA για καθιέρωση Προτύπων ελέγχου μικρής κλίμακας τα οποία σε συνδυασμό με αριθμητικά μοντέλα θα είναι σε θέση να προβλέπουν την συμπεριφορά των αεροπορικών κατασκευών σε συνθήκες φωτιάς από την φάση του σχεδιασμού τους. Θα εξασφαλίζεται έτσι καλύτερη διαχείριση οικονομικών και υλικών πόρων. Στην βιβλιογραφία ο μεγαλύτερος όγκος αριθμητικής μοντελοποίησης έχει πραγματοποιηθεί στους τομείς της ναυπηγικής και των θαλάσσιων κατασκευών καθώς επίσης και τα τελευταία χρόνια στον τομέα της αστικής δόμησης. Αριθμητική δουλεία πάνω στην συμπεριφορά των αεροπορικών κατασκευών είναι υπερβολικά περιορισμένη και εκεί στοχεύει να συμβάλει η παρούσα διατριβή. Οι αεροπορικές κατασκευές εκτός των περιορισμών και προδιαγραφών που θέτουν οι άλλες εφαρμογές απαιτούν την ελαχιστοποίηση του προστιθέμενου βάρους στην κατασκευή. Διάφοροι τύποι πολυμερών συνθέτων υλικών χρησιμοποιούνται στην βιομηχανία, διακρινόμενα σε θερμοσκληρυνόμενα και θερμοπλαστικά. Αρχικά παρουσιάζονται τα θερμοσκληρυνόμενα ξεκινώντας από τους ευρέως χρησιμοποιούμενους πολυεστέρες και βινυλεστέρες, στις φαινολικές και εποξικές ρητίνες καταλήγοντας στους υψηλής θερμοκρασίας κυανεστέρες. Εν συνεχεία γίνεται αναφορά στα συνήθη χρησιμοποιούμενα θερμοπλαστικά, πολυπροπυλένιο PP, Poly-ether ether-ketone PEEK και polyphenylene Sulphide PPS. Φυσικά δεν παραλείπεται να γίνει σύντομη αναφορά και στις τυπικές διεργασίες θερμικής αποσύνθεσης των προαναφερθέντων πολυμερών. Η συμπεριφορά των σύνθετων πολυμερών υλικών σε συνθήκες φωτιάς περιγράφεται από κάποια χαρακτηριστικά μεγέθη τα οποία χρησιμοποιούνται για την ποιοτική και ποσοτική σύγκριση των διαφόρων υποψήφιων αεροπορικών υλικών. Συγκεκριμένα τα μεγέθη αυτά είναι: Heat Release Rate HRR, Thermal Stability Index TSI, Limited Oxygen Index LOI, Extinction Flammability Index ESI, Time-to-Ignition, Surface Flame Spread, Mass Loss, Smoke Density, Smoke Toxicity. Οι διαδικασίες ελέγχου και τα υπολογιζόμενα μεγέθη γίνονται βάσει διεθνών Προτύπων που κυρίως για τον τομέα της αεροναυπηγικής ορίζονται από την Ομοσπονδιακή Διεύθυνση Αεροπλοΐας FAA. Η αριθμητική προσομοίωση προυποθέτει γνώση της συμπεριφοράς των πολυμερών υλικών σε συνθήκες υψηλής θερμοκρασίας, για τον σκοπό αυτό πραγματοποιήθηκαν πειράματα απώλειας μάζας με χρήση θερμογραβιμετρίας TGA κατά την διάρκεια της οποίας η απώλεια μάζας καθώς και ο ρυθμός αυτής παρακολουθούνται και καταγράφονται σαν συνάρτηση του ρυθμού θέρμανσης. Μέσα από αυτά τα δεδομένα μπορεί να πραγματοποιηθεί εκτίμηση του τρόπου αποσύνθεσης του πολυμερούς. Αρχικά πραγματοποιήθηκε η θεώρηση της μονοβάθμιας αντίδρασης (single-stage reaction) που αποτελεί και την πλέον απλουστευμένη προσέγγιση. Στην θεώρηση αυτή θεωρείται πως η πολυμερής μήτρα περνάει από την «παρθένα» κατάσταση στην απανθρακομένη μέσα σε ένα βήμα. Η περιγραφή της αντίδρασης αυτής γίνεται με μια μονοβάθμια αντίδραση τύπου Arrhenius. Σε δεύτερο βήμα χρησιμοποιήθηκε κινητική θεωρία πολλαπλών σταδίων (multi-stage kinetics) σύμφωνα με την οποία πραγματοποιήθηκε ακριβέστερη προσέγγιση της απόσύνθεσης της πολυμερούς μήτρας των συνθέτων υλικών με απόκλιση μικρότερη του 5% από τα πειραματικά δεδομένα της θερμογραβιμετρείας (thermogravimetry). Και στις δύο προσεγγίσεις της αποσύνθεσης υπολογίσθηκαν οι κινηματικές παράμετροι: συντελεστής συχνότητας A (frequency factor), ενέργεια ενεργοποίησης ΕΑ (activation energy), τάξη αντίδρασης n (reaction order) για κάθε στάδιο. Με την ολοκλήρωση αυτού του σταδίου υπήρχε μια αξιόπιστη δυνατότητα αναπαράστασης της διαδικασίας αποσύνθεσης στο πείραμα της θερμογραβιμετρίας. Είναι γνωστό ότι οι διακυμάνσεις της θερμοκρασίας επηρεάζουν της τιμές των θερμοφυσικών ιδιοτήτων των υλικών. Αναλογιζόμενοι ότι στην διαρκεία της επιβολής της φλόγας στα σύνθετα υλικά όχι μόνο η θερμοκρασία αλλά και η σύσταση μεταβάλλεται συνεχώς λόγω της αποσύνθεσης κρίθηκε αναγκαία η ανάπτυξη μιας μεθοδολογίας που θα συμπεριλαμβάνει την επίδραση της αποσύνθεσης στην μεταβολή των θερμοφυσικικών ιδιοτήτων (θερμική αγωγιμότητα, ειδική θερμοχωρητικότητα και πυκνότητα) της πολυμερούς μήτρας και κατά συνέπεια του συνθέτου υλικού. Οι εξαγόμενες μαθηματικές σχέσεις χρησιμοποιήθηκαν στην αριθμητική προσομοίωση που ακολούθησε. Με σκοπό την ορθή αριθμητική μοντελοποίηση κρίνεται αναγκαία η μέτρηση και βαθμονόμηση του θερμικού φορτίου τον πειραματικών δοκιμών. Το μετρούμενο θερμικό φορτίου χρησιμοποιήθηκε εν συνεχεία ως φόρτιση στα αναπτυχθέντα μοντέλα. Χρησιμοποιήθηκαν δύο πειραματικές διατάξεις εφαρμογής φλόγας, μία μεσαίας κλίμακας σύμφωνα με τις διατάξεις του FAA Standard, που περιγράφεται στο ISO2685:1998(E) “Aircraft – Environmental test procedure for airborne equipment – Resistance to fire in designated fire zones” και μίας εργαστηριακής κλίμακος. Πραγματοποιήθηκε μέτρηση με θερμοζεύγη και καλορίμετρο νερού καθώς και αριθμητική μοντελοποίηση με χρήση CFD για την πρώτη διάταξη. Ενώ για την εργαστηριακής κλίμακας έγινε μέτρηση με θερμοζεύγη και ενός αισθητήρα θερμικού φορτίου «water-cooled Hukseflux Schmit-Boelter SBG01 sensor». Εν συνεχεία πραγματοποιήθηκε η κατασκευή των δοκιμίων των υποψήφιων υλικών καθώς και οι πειραματικές δοκιμές και έλεγχοι τους. Συγκεκριμένα πραγματοποιήθηκε: Θερμιδομετρία κώνου (cone calorimetry), Θερμογραβιμετρία (thermogravimetry), Θερμιδομετρία Διαφορικής Ανίχνευσης (Differencial Scanning Calorimetry, DSC), Μέτρηση Θερμικής αγωγιμώτητας, Δοκιμή διείσδυσης φλόγας (Fire burnthrough penetration). Καθώς ο χαρακτηρισμός της αποσύνθεσης των πολυμερών υλικών, η μεταβολή των θερμοφυσικών ιδιοτήτων, η μέτρηση και βαθμονόμηση του επιβαλλόμενου θερμικού φορτίου καθώς και οι πειραματικές δοκιμές έχουν ολοκληρωθεί ακολουθεί η αριθμητική προσομοίωση. Οι συνοριακές συνθήκες θερμικού φορτίου και ψύξης επιλέχθησαν ως εξής. Ως φόρτιση θεωρήθηκε η κατανομή του θερμικού φορτίου (σε kW/m2) στην εμπρός επιφάνεια του πάνελ. Στην ψύξη της πίσω επιφάνειας λήφθηκε υπόψη τόσο η ελεύθερη μεταφορά θερμότητας με επαφή όσο και η ακτινοβολία. Το μοντέλο της συμπεριφοράς του υλικού διαμορφώθηκε κατάλληλα ώστε να γίνει κατανοητό από τις απαιτήσεις ενός εμπορικού κώδικα Πεπερασμένων Στοιχείων επίλυσης θερμικών προβλημάτων και προσομοιώθηκαν οι πειραματικές δοκιμές διείσδυσης φλόγας των δύο πειραματικών διατάξεων, μεσαίας και εργαστηριακής κλίμακος. Πλέον της αριθμητικής προσομοίωσης της συμπεριφοράς σε φωτιά επίπεδων δοκιμίων αεροπορικών κατασκευών, πραγματοποιήθηκε προσπάθεια απλουστευμένης μοντελοποίησης των συνθηκών φλόγας ενός λιμνάζοντος όγκου καυσίμου αεροσκαφών στο εξωτερικό μιας ατράκτου. Δημιουργήθηκε ένα τρισδιάστατο ρευστομηχανικό μοντέλο πρόβλεψης του θερμικού φορτίου στην επιφάνεια μιας τυπικής ατράκτου σύμφωνα με τις προδιαγραφές γεωμετρίας του Προτύπου “Full-scale test evaluation of Aircraft fuel fire burnthrough resistance improvements” DOT/FAA/AR-98/52,1999. Τα ρευστομηχανικά αποτελέσματα συγκρίθηκαν με δεδομένα βιβλιογραφίας για μεγάλες φλεγόμενες δεξαμενές λιμνάζοντος καυσίμου. Εκτός από την μελέτη της απόκρισης των αεροπορικών κατασκευών σε συνθήκες φλόγας σκοπός της παρούσας εργασίας είναι και η παρουσίαση λύσεων οι οποίες θα έχουν την δυνατότητα της βελτίωσης της συμπεριφοράς των υπαρχουσών δομών καθώς και των μελλοντικών σύνθετων δομών. Ενδεικτικά αναφέρεται η δυνατότητα χρήσης νανοεγκλεισμάτων, και βελτιωμένων μονωτικών υλικών, π.χ. aerogels. Όπως έχει ήδη αναφερθεί οι αεροπορικές κατασκευές θέτουν τον περιορισμό της ελαχιστοποίησης του προστιθέμενου βάρους, για τον λόγο αυτό η ενίσχυση των συνθέτων υλικών θα πρέπει να πραγματοποιηθεί σε επίπεδο υλικού και σχεδιασμού. Πρέπει δηλαδή η ίδια η κατασκευή που είναι ικανή να φέρει τα μηχανικά φορτία να εξασφαλίζει και την πιστοποίηση της FAA για συνθήκες φωτιάς. Συνοψίζοντας, η παρούσα διατριβή πραγματοποιεί μια καινοτόμο, γρήγορη και αρκετά ακριβή προσέγγιση του σημαντικότατου ζητήματος της συμπεριφοράς των πολυμερικών σύνθετων αεροπορικών δομών σε συνθήκες φωτιάς Η πολυπλοκότητα του όλου φαινομένου επέβαλε την πραγματοποίηση παραδοχών και απλουστεύσεων. Καθώς όμως με την αυξανόμενη χρήση των συνθέτων υλικών στις αεροπορικές κατασκευές, ο τομέας της ασφάλειας σε συνθήκες φλόγας είναι συνεχώς αυξανόμενος και απαιτητικός. Για αυτό οι παραδοχές και θεωρήσεις της παρούσας διατριβής μπορούν να βελτιωθούν με χρήση νέων υπολογιστικών μεθόδων και πειραματικών δεδομένων με στόχο την ακόμα ακριβέστερη πρόβλεψη της συμπεριφοράς τον αεροπορικών δομών σε συνθήκες φλόγας.

This chapter focuses on the influence that the Black Power movement and rise of employment discrimination litigation had on the Vulcan Society and Black firefighters across the country. The dialectical relationships between the civil rights and Black Power movements and the Vulcan Society’s old and new guard eventually transformed the organization and its objectives and helped facilitate the IABPFF, a national Black caucus group formed to combat discrimination and increase Black representation in — and community control of — urban fire departments. Both the IABPFF and the Vulcan Society embraced “separatism without separation,” and used their “outsider status within a white-dominated institution,” as well as shifts in employment discrimination case law, to “reveal the inner workings of institutional racism” within the FDNY and urban fire departments more generally. This shift was instrumental in the fight to establish legal remedies to address institutionalized racism and its impact on the racial composition of urban fire departments and became the primary method used by the Vulcan Society and the IABPFF and its local affiliates to make fire departments more representative of and responsive to the people and communities they served

In a historic 2012 decision, Eastern District Court Judge Nicholas Garaufis ruled that the New York City Fire Department (FDNY) had knowingly and intentionally implemented and maintained racially discriminatory hiring processes throughout its history. The case, United States and Vulcan Society v. City of New York...

This chapter looks at the Black experience in the FDNY during the last quarter of the 20^th Century. During this period, the City, fire department, and the fire unions all vigorously resisted efforts by the Vulcan Society and the United Women Firefighters to address structural and institutional racism and sexism. Black representation, after growing slightly and then stalling in the mid 1980s, receded slowly and steadily as the century closed.

Abstract Although Venus was the goddess of love, no one remembers her wedding to Vulcan, just the gossip that followed it. As Mercury said to Apollo in Lucian’s Dialogues of the Gods, what was a stunning girl like Venus doing with a crippled blacksmith for a husband? He was probably all sweaty and covered in soot from the forge. It was easy to see his point. From the Farnesina onwards, the workshop of Vulcan was often depicted over fire places, and you could sense the heat and the smoke as you approached. Venus is not always there, partly because she did not appear in the ancient relief that influenced the school of Raphael, but also because almost the only time she went to see her husband was when she seduced him into manufacturing arms for Aeneas (her son by another man). The story is found in Virgil and the scene is popular in sixteenth century northern art, beginning with Maarten van Heemskerck’s painting of 1536. Vulcan’s team of Cyclopes were making Jupiter’s thunderbolts when they were interrupted by Venus’s order. But that was not all they produced. Cornelis van Haarlem’s Venus and Vulcanof 1590 displays the range of Vulcan’s output, and the protoindustrial scale of his operation (Fig. 65). It is a clever painting, composed to look like a fireplace. Inside the hearth the group with raised hammers is from a print after Heemskerck – the motif relegated to the back of the shop like any superseded design.

Abstract A written play-text must be written somewhere. One such space is evoked in Jonson’s ‘An Execration upon Vulcan’, written after fire destroyed his rooms and books in November 1623; the poem is a partial inventory both of his own books and of his mental furniture, suggesting the range of sources on which he drew. He mentions verse and prose romances, tales of adventure that many of his characters know and admire or scorn, the Talmud and Koran, classical works and translations, his own English Grammar, some poems, and a substantial work-in-progress about Henry V; books in Latin, Greek, and Hebrew borrowed from three notable scholars, Richard Carew (1555-1620), Robert Cotton (1571-1631), and John Selden (1584-1654), may have been among those destroyed.

A pool model has been developed to predict the evaporation of a liquid fuel from a surface in response to a fire. The model exists in the Fuego, Kameleon, and Vulcan fire codes. The model solves for the mass evolution based on what are thought to be the dominant input boundary conditions. Some empirical assumptions are made to predict the behavior of lower order physics. The performance of the model is evaluated by comparing predicted results with measurements for a variety of test cases in Fuego. Qualitative performance of the model is found to be reasonable. The model is found to yield quantitative results of mixed accuracy, suggesting the worth of considering improvements to the model. Evidence from the study helps indicate the future direction for improving this class of model.

Recent development efforts have resulted in new models that are capable of predicting water spray interactions with solid surfaces for a wide range of drop sizes and velocities. These models provide a reasonable approximation to single drop impact events, and significantly improve the expected accuracy of the splash. The models are implemented in the Vulcan software, a CFD code for fire modeling. We wanted to understand how important the splash is to a suppression scenario and the implications of common simplifying assumptions. A scenario with several rectangular objects located beneath a water suppression system is examined. This scenario was designed to be representative of an industrial fire and suppression situation. We compare the deposition masses on the surfaces for three cases, one with the recently developed model, another assuming no splash, and another assuming all splashing drops eject an excessive fraction of their mass. The results of the higher fidelity predictions compared with the more commonly employed and simpler assumptions suggest the importance of splashing to the outcome of an industrial water sprinkler fire suppression event.

Considerable interest exists in the application of single wall carbon nanotubes (SWNTs) to proton exchange membrane fuel cells (PEMFCs). Proposed applications include use as anode materials in both hydrogen and direct methanol fuel cells, solid polymer electrolyte additives, active cathode materials, and bipolar plate interconnects. SWNTs have extremely high electrical conductivity and catalytic surface areas which make them potentially outstanding active materials for PEMFC electrodes. Additionally the enhanced mechanical properties may play a roll in developing new fuel cell designs such as thin-film microelectronic fuel cells. In a previous study SWNTs were combined with commercially obtained E-TEK Vulcan XC-72 and Nafion® to produce composite cathode membranes. The addition of nanotubes resulted in enhanced fuel cell performance over an equivalent weight percent doping of E-TEK alone. This increased performance was achieved with a 50% reduction in the quantity of platinum present in the cathode. In the present study we investigate fuel cell performance when both the anode and cathode membranes contain graphite, platinum and SWNTs. The SWNTs were characterized by use of thermogravimetric analysis, Raman and UV/VIS/NIR spectroscopes as well as high resolution field emission scanning electron microscopy. Fuel cell performance was determined by comparison of the IV characteristics.