Review and analysis of fire and explosion accidents in maritime transportation

The globally expanding shipping industry has several hazards such as collision, capsizing, foundering, grounding, stranding, fire, and explosion. Accidents are often caused by more than one contributing factor through complex interaction. It is crucial to identify root causes and their interactions to prevent and understand such accidents. This study presents a detailed review and analysis of fire and explosion accidents that occurred in the maritimetransportation industry during 1990–2015. The underlying causes of fire and explosion accidents are identified and analysed. This study also reviewed potential preventative measures to prevent such accidents. Additionally, this study compares properties of alternative fuels and analyses their effectiveness in mitigating fire and explosionhazards. It is observed that Cryogenic Natural Gas (CrNG), Liquefied Natural Gas (LNG) and methanol have properties more suitable than traditional fuels in mitigating fire risk and appropriate management of their hazards could make them a safer option to traditional fuels. However, for commercial use at this stage, there exist several uncertainties due to inadequate studies, and technological immaturity. This study provides an insight into fire and explosion accident causation and prevention, including the prospect of using alternative fuels for mitigating fire and explosion risks in maritime transportation

GT2004-53622 PRELIMINARY STUDY OF A NOVEL R718 TURBO-COMPRESSION CYCLE USING A 3-PORT CONDENSING WAVE ROTOR

ABSTRACT Using a novel 3-port condensing wave rotor enhancing the turbo-compression in a R718 refrigeration cycle, which uses only water as a refrigerant, has been introduced. The waverotor implementation can increase efficiency and reduce size and cost of R718 units. The condensing wave rotor employs pressurized water to pressurize, desuperheat, and condense the refrigerant vapor -all in one dynamic process. The underlying phenomena of flash evaporation, shock wave compression, desuperheating, and condensation inside the wave rotor channels are described in a wave and phase-change diagram. The thermodynamic process is shown in pressure-enthalpy and temperature-entropy diagrams. A computer program based on a thermodynamic model was generated to evaluate the performance of R718 baseline and wave-rotor-enhanced cycles. The effect of some key parameters on the performance enhancement is demonstrated as an aid for optimization. A performance map summarizes the findings. It shows optimum wave rotor pressure ratio and maximum relative performance improvement of R718 cycles by using the 3-port condensing wave rotor

GT2004-53496 NUMERICAL PREDICTION OF NON-REACTING AND REACTING FLOW IN A MODEL GAS TURBINE COMBUSTOR GT2004-53496

ABSTRACT INTRODUCTION The three-dimensional, viscous, turbulent, reacting and non-reacting flow characteristics of a model gas turbine combustor operating on air/methane are simulated via an unstructured and massively parallel Reynolds-Averaged Navier-Stokes (RANS) code. This serves to demonstrate the capabilities of the code for design and analysis of real combustor engines. The effects of some design features of combustors are examined. In addition, the computed results are validated against experimental data. Computational fluid dynamics (CFD) has become an integral part in the design process of aeropropulsion engines, and a viable tool in understanding complex physical features of flowfields associated with various components of these engines. Use of CFD allows experimentation with new innovative design ideas that was not possible before, due to the excessive cost associated with manufacturing and testing of the prototypes. Thus CFD is able to improve design, reduce development cost, contribute to improved performance, and increase understanding of flowfield induced in yet not fabricated configurations. The numerical model encompasses the whole experimental flow passage, including the flow development sections for the air annulus and the fuel pipe, twelve channel air and fuel swirlers, the combustion chamber, and the tail pipe. A cubic non-linear low-Reynolds number K-e turbulence model is used to model turbulence, whereas the eddy-breakup model of Magnussen and Hjertager is used to account for the turbulence combustion interaction. Several RANS calculations are performed to determine the effects of the geometrical features of the combustor, and of the grid resolution on the flow field. The final grid is an all-hexahedron grid containing approximately two and one half million elements. In particular, gas turbine combustion modeling involves many complex physical processes that occur simultaneously such as combustion, turbulence, turbulence chemistry interaction, reaction kinetics, turbulence spray interaction, heat transfer, and radiation. In addition to solving the ReynoldsAveraged Navier-Stokes equations with a turbulence model, one may need to solve tens of individual species mass balance. The required partial differential equations to be solved could easily add up to 30 to 40 equations, depending on the number of species involved in the reaction kinetics. Considering various physical processes that are modeled and the resolution required for the grid to resolve scales of these processes, computational resources needed may become extensive and costly. In addition the complexities of the geometries of the combustors raise the daunting task of curvilinear grid generation. To provide an inlet condition to the main combustion chamber, consistent with the experimental data, flow swirlers are adjusted along the flow delivery inlet passage. Fine details of the complex flow structure such as helicalring vortices, recirculation zones and vortex cores are well captured by the simulation. Consistent with the experimental results, the computational model predicts a major recirculation zone in the central region immediately downstream of the fuel nozzle, a second recirculation zone in the upstream corner of the combustion chamber, and a lifted flame. Further, the computed results predict the experimental data with reasonable accuracy for both the cold flow and for the reacting flow. It is also shown that small changes to the geometry can have noticeable effects on the combustor flowfield. However, to apply CFD in real-world design applications, the complex 3-D geometries, and many of the physical processes involved need to be resolved. With decreasing computing cost, increasing CPU speed, and the development of the parallel computing platform, computational cost and time is reduced to a level that fit in the design cycle time frame. Furthermore, with the advance of the numerical schemes using unstructured or Chimera meshes, mesh generation is becoming less intimidating than it used to be. The major task still remains

Land and Sea exhibition documentation, 2015

Our newest artists book acquisitions are from Land and Sae, a small press based in Oakland, CA, run by Maria Otero Aand Chris Duncan (CCA Alumnas). From the publisher: Land and Sea began during the final days of 2009 and have consistently been punlishing small editions of books and records by artists from the bay area and beyond. Under the same moniker, Chris and Maria organize gatherings that celebrate the artists the artists they work with as well as the communities they are apart of. Land and Sea are proud to have their editions in the collections of the SFMOMA, The Berkeley Art Museum, Standford Liubrary, and the NYMOMA

GT2003-38234 MODEL BASED GAS TURBINE PARAMETER CORRECTIONS

ABSTRACT Ambient conditions have a significant impact on the temperatures and pressures in the flow path and on the fuel flow of any gas turbine. Making observed data comparable requires a correction of the raw data to sea level Standard Day conditions. The most widely applied gas turbine parameter correction method is based on keeping some dimensionless Mach number similarity parameters invariant. These similarity parameters are composed of the quantity to be corrected multiplied by temperature to the power 'a' and pressure to the power 'b' with exponent 'a' being theoretically either 0, +0.5 or -0.5 and 'b' either 0 or 1.0. To improve the accuracy of this approach it is common practice to empirically adapt the temperature and pressure exponents 'a' and 'b' in such a way that the correction process leads to a better correlation of the data. INTRODUCTION The purpose of correcting measured data from a gas turbine test is to make the results comparable with those from other engines or with acceptance test criteria, for example. The basic question to be answered is: What would be the engine performance if the test would have been at Standard Day conditions? This question applies not only to measurements taken on a normal test bed where the local altitude and the weather conditions dictate the conditions of the incoming air but also to experiments in an altitude test facility (ATF) if due to facility limitations the conditions at the engine face are not as desired, for example. Data correction algorithms are applied also when monitoring engine deterioration: it is essential to compare data which has been corrected to the same ambient conditions. Finding empirical exponents requires either many consistently measured data that cover a wide range of ambient temperatures and pressures or a computer model of the engine. A high fidelity model is especially well suited for creating optimally matched exponents and for exploring the phenomena that make these exponents deviate from their theoretical value. This paper discusses the questions that arise when creating empirical exponents with a thermodynamic model of the gas turbine

GT2003-38394 EXPERIMENTAL INVESTIGATION AND CHARACTERIZATION OF THE ROTATING STALL IN A HIGH PRESSURE CENTRIFUGAL COMPRESSOR. PART IV: IMPELLER INFLUENCE ON DIFFUSER STABILITY

ABSTRACT Vaneless diffuser rotating stall is a major problem for centrifugal compressors since it is a limit to their working range. In particular the last stage seems to be the most critical. In the literature some good correlations for predicting stall inception can be found but they do not adequately cover the case of the last stage configuration, especially for very low blade-outlet-width-to-impeller-radius-ratio impellers typically used in high-pressure applications. Extensive research has been performed to define diffuser stall limits for this family of stages: three impellers characterized by different blade-outletwidth-to-impeller-radius-ratios are tested with different diffuser configurations (different pinch shapes, diffuser widths and diffusion ratios). Part I and II report the results of these geometry modifications on diffuser stability for the first impeller. Part III, those for the second impeller. In this part the comparison of these results in terms of impeller influence on diffuser stability is reported

Plan of Management - Anindilyakwa Indigenous Protected Area

Made available by the Northern Territory Library via the Publications (Legal Deposit) Act 2004 (NT).This Plan of Management (PoM) coincides with the extension of the Anindilyakwa Indigenous Protected Area (IPA) to include sea country (see Box 1). It is intended as an update to the 2006 Anindilyakwa IPA PoM (which included prescriptions for land only) and builds on the draft PoM compiled in 2013. Together with the ALC 15 Year Strategic Plan (ALC, 2012), this PoM outlines how the Anindilyakwa IPA will be managed for the next ten years. This PoM, prepared by the Anindilyakwa Land Council (ALC) Land and Sea Management (LSM) Unit, reflects traditional owner concerns, aspirations and priorities regarding the future management of their country. - Page 10A message from traditional owners -- Purpose and scope of plan -- Part A: Background - Warnumamalya people - Country - Land and sea uses - Conservation significance - Management framework - Guiding principles - Management regions - Governance of the IPA - Resourcing the IPA - Our vision for culture and country. Part B: Management themes - Healthy people, healthy country - Looking after ariba - Looking after makarda. Part C: Monitoring and evaluation - Monitoring and evaluation scope - Monitoring and evaluation plan . Appendices I - XII.Includes message from traditional owners - page 9. Bibliographical references - Pages 126-12

GT2003-38774 INTER-LABORATORY DYNAMIC MODELING OF A CARBONATE FUEL CELL FOR HYBRID APPLICATION Internal resistance of the fuel cell

ABSTRACT A detailed comparison of dynamic models developed for carbonate fuel cells used in hybrid fuel cell gas turbine systems is presented. The two models are nearly similar in that both treat the bulk behavior of the system (e.g., through lumped or one-dimensional solutions of the fundamental equations. However, both models are implemented independently by different research groups using disparate simulation software programs. As a test case for the comparison, a generic molten carbonate hybrid fuel cell gas turbine system is identified. Such comparison-work benefits all parties by ensuring sub-mo del reliability prior to integration into a complete hybrid system model. Detailed results for the carbonate fuel cell models are presented. For a generic planar design, voltage and current behavior are shown following step changes in load resistance and fuel flow. The time scales for thermal dynamic response are much greater than those required for the initial electrochemical dynamic response as is expected. These results provide understanding of some of the operational characteristics of fuel cells and indicate the complexity of the dynamic response of fuel cell hybrid components. The results from the two models are not identical, but compare sufficiently well to provide confidence in each of the model's reliability, enabling them to be integrated for hybrid system simulation. Results from the integrated simulations will provide guidance on future hybrid technology development needs. NOMENCLATUR

Report to the Northern Australia Ministerial Forum

Made available by the Northern Territory Library via the Publications (Legal Deposit) Act 2004 (NT).This is the second of two major forums being delivered by NAILSMA Ltd under its arrangement with the Office of Northern Australia, which is due to end 1 June 2013. The second forum will be the final opportunity to develop a position and provide strategic direction on how to best leverage Indigenous interests in future northern development agendas.Executive summary -- Background -- Welcome -- Setting the agenda -- Indigenous investment in Northern Development -- An Indigenous prospectus for participating in the sustainable development of North Australia -- Key outcomes -- Closing remarks -- Appendices 1-7This report was funded by the Australian Government Department of Regional Australia, Local Government, Arts and Sports through its Office of Northern Australia. Chairman Patrick Dodson, Deputy Chairman Peter Yu

Dugong and Marine Turtle: teaching resource and information package. Written and compiled by the Torres Strait Regional Authority's Land and Sea Management Unit.

Made available by the Northern Territory Library via the Publications (Legal Deposit) Act 2004 (NT).CDROM not include