Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems最新文献

{"title":"Numerical Investigation of an Inverted Brayton Cycle Micro Gas Turbine Based on Experimental Data","authors":"Eleni Agelidou, M. Henke, T. Monz, M. Aigner","doi":"10.1115/GT2018-76377","DOIUrl":"https://doi.org/10.1115/GT2018-76377","url":null,"abstract":"Residential buildings account for approximately one fifth of the total energy consumption and 12 % of the overall CO2 emissions in the OECD countries. Replacing conventional boilers by a co-generation of heat and power in decentralized plants on site promises a great benefit. Especially, micro gas turbine (MGT) based combined heat and power systems are particularly suitable due to their low pollutant emissions without exhaust gas treatment. Hence, the overall aim of this work is the development of a recuperated inverted MGT as heat and power supply for a single family house with 1 kWel. First, an inverted MGT on a Brayton cycle MGT was developed and experimentally characterized, in previous work by the authors. This approach allows exploiting the potential of using the same components for both cycles. As a next step, the applicability of the Brayton cycle components operated in inverted mode needs to be evaluated and the requirements for a component optimization need to be defined, both, by pursuing thermodynamic cycle simulations. This paper presents a parametrization and validation of in-house 1D steady state simulation tool for an inverted MGT, based on experimental data from the inverted Brayton cycle test rig. Moreover, a sensitivity analysis is conducted to estimate the influence of every major component on the overall system and to identify the necessary optimizations. Finally, the component requirements for an optimized inverted MGT with 1 kWel and 16 % of electrical efficiency are defined. This work demonstrates the high potential of an inverted MGT for a decentralized heat and power generation when optimizing the system components.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124415358","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Experimental and Numerical Investigation of Early Phase of Laser Ignition Under Stoichiometric and Lean Conditions","authors":"D. Coombs, N. Peters, B. Akih-Kumgeh","doi":"10.1115/GT2018-77238","DOIUrl":"https://doi.org/10.1115/GT2018-77238","url":null,"abstract":"Forced ignition, the initiation of combustion processes by rapid and localized introduction of energy, is central to the successful operation of many combustion systems. It is therefore of interest to investigate this process, starting from the introduction of energy to the emergence of self-sustained flame or the quenching of an otherwise initialized flame kernel. Since the process is highly non-equilibrium and involves various complex kinetic phenomena, it is important to understand the key aspects that control failed or successful ignition. Detailed studies of the early phases of the ignition process can lead to knowledge of more general characteristics of the problem so that reduced models of the ignition process can be developed. These reduced versions can be used in less costly computational studies to assess various ignition events. This paper reports an experimental and numerical investigations of the early phase of laser ignition. The gas mixtures, air, methane/N2 and methane/air are considered to bring out the effect of heat release on the early flow field. The mixtures are studied at three different energy levels and the Jones blast wave theory is used to deduce the energy responsible for the development of the attendant shock waves. This energy is also used to specify initial conditions for the simulations of air and methane/air processes. Additionally, interferometry is used to resolve the density field within the plasma kernel. For the methane/air simulation two chemical models are used, a global reaction model supplemented by an ignition model and a two-step mechanism. The sensitivity of the simulations to the initial geometry of the laser spark is also investigated. The blast wave and interferometry results show that in the reacting methane/air mixture the resulting shock wave is strengthened by early heat release. It is also shown that the shock wave trajectory is not strongly affected by the initial spark geometry, but it has an impact on the velocity field and on the distribution of thermodynamic properties.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116955945","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Investigation and Assessment of the Performance of Various Recuperative Cycles Based on the Intercooled Recuperation Concept","authors":"C. Salpingidou, Z. Vlahostergios, D. Misirlis, M. Flouros, F. Donus, K. Yakinthos","doi":"10.1115/GT2018-76778","DOIUrl":"https://doi.org/10.1115/GT2018-76778","url":null,"abstract":"This work is focused on investigations of Intercooled Recuperation configurations for aero engines. The investigated configurations were the Conventional Recuperation, where the recuperator was placed downstream the low-pressure turbine (LPT), the Alternative Recuperation, where the recuperator was mounted between the intermediate pressure turbine (IPT) and LPT, and the Staged Heat Recovery concept, in which two recuperators were mounted, one between IPT and LPT and the other downstream the LPT. These concepts were further assessed with the use of an additional combustor between IPT and LPT. All recuperator concepts that have been developed within the framework of various research projects by Aristotle University of Thessaloniki and MTU Aero engines AG were utilized, named as the NEWAC, CORN and STARTREC concepts. Additionally, a new recuperator design was introduced using a secondary fluid as heat transfer medium. The configurations thermodynamic assessment was focused on specific fuel consumption reduction, while the configurations effect on NOx emissions was also investigated. The results showed that the most promising recuperator concept, with respect to low TSFC values compared with a reference GTF engine of 2050 year technology level, is the recuperator with the secondary fluid heat transfer medium.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"119 2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129269490","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Reaction Model Development for Synthetic Jet Fuels: Surrogate Fuels As a Flexible Tool to Predict Their Performance","authors":"T. Kathrotia, S. Richter, C. Naumann, N. Slavinskaya, T. Methling, M. Braun-Unkhoff, Uwe Riedel","doi":"10.1115/GT2018-76997","DOIUrl":"https://doi.org/10.1115/GT2018-76997","url":null,"abstract":"In the last years, the development of synthetic aviation jet fuels has attracted much interest, to provide alternatives to crude-oil based kerosene. Synthetic jet fuels can be produced from a variety of feedstocks and processes. To limit possible harmful effects on the environment when burning a jet fuel, discussions are attributed to the effects of the specific composition of a synthetic fuel on its performance and its emission pattern. A numerical tool, if available, would also be helpful within the specification process any aviation jet fuel must pass.\u0000 The present work contributes to the studies and efforts how to design a synthetic jet fuel to match predefined properties, e.g. the energy content or a less harmful emission characteristics compared to Jet A-1. The approach of a generic fuel will be followed in order to design a synthetic jet fuel with pre-defined chemical properties: A chemical kinetic reaction mechanism will be elaborated capable predicting the fundamental combustion properties of the generic fuel for each possible mixing ratio of the components included.\u0000 In this work, a generic mixture serving as an innovative synthetic jet fuel was studied, with n-dodecane, cyclohexane, and iso-octane chosen as single fuel components; no aromatics were added to reduce the concentration of soot precursors. Then, their fundamental combustion properties, i.e. laminar burning velocity and ignition delay time, were measured in a burner test rig and applying the shock tube technique, respectively. These experimental data were used for the validation of the reaction mechanisms developed for each single fuel component, which were then combined to the reaction mechanism for the generic fuel under consideration. To allow a comparison of the combustion behavior of the synthetic jet fuel directly, with the same reaction mechanism, to Jet A-1, toluene was added as a model component for aromatics. A reduced surrogate reaction model was produced, too.\u0000 All the reaction mechanisms elaborated are shown to reasonably predict the fundamental combustion properties within the parameter range considered. The compact reduced surrogate model can serve as a virtual jet fuel within numerical simulations. Thus, ultimately, an estimation of the suitability of an innovative synthetic jet fuel as a blending component to crude-oil kerosene is enabled. As a result, CFD simulations can be run efficiently tackling the combustion of a synthetic fuel in a jet engine under practical conditions and by taking into account the interaction between turbulence and chemistry.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129907865","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Rotor Over-Speed Analysis of a Hybrid Solar Gas Turbine","authors":"Darsini Kathirgamanathan, L. Axelsson","doi":"10.1115/GT2018-76370","DOIUrl":"https://doi.org/10.1115/GT2018-76370","url":null,"abstract":"As the demand for environmentally friendly power production is increasing, the Hybrid Solar Gas Turbine (HSGT) power plant has the potential to provide a reliable electricity production with low carbon foot print by combining the solar heat and the fossil fuel. Compared to the conventional gas turbine system, the HSGT system has an additional heat source and larger volume due to the solar receiver and the ducting system required for guiding the air to and from the solar receiver. The additional heat source and larger volume increase the thermal capacitance which adds complexity to the operational behavior of the gas turbine.\u0000 This paper presents an investigation of the transient behavior of a hybrid solar gas turbine. The OP16 gas turbine, rated at 1.85MWe, is integrated into a solar thermal power plant as part of an ongoing R&D project. To analyze the shaft over-speed of the system, a model is created using the commercial cycle analysis software GSP. The model is validated against the measured data for a non-solar mode operation as it is similar to the conventional gas turbine operation on pure fossil fuel.\u0000 A rotor over-speed analysis of the OP16-HSGT system during load-shed shows that the rotor over-speed exceeds the acceptable limit due to the thermal capacitance and volumetric effects. An increase in shaft inertia, or re-direction of the air flow from hybrid-solar mode to non-solar mode by using control valves, or the use of blow-off valve to vent out the solar heat can be taken as safety measures to reduce rotor over-speed. It was found that the control valve should act within 0.3s to maintain acceptable rotor over-speed. As a control valve with such characteristics is scarcely available, a concept where the OP16-HSGT system uses a blow-off valve in addition to the control valve was developed. The blow-off valve reduces the rotor over-speed from 111% to 103% by venting out the thermal capacitance from the OP16-HSGT system and by that one can achieve safe operation during a load-shed or an emergency shutdown.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129910302","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Mission Analysis and Operational Optimization of Adaptive Cycle Micro-Turbofan Engine in Surveillance and Firefighting Scenarios","authors":"M. Palman, B. Leizeronok, B. Cukurel","doi":"10.1115/gt2018-75323","DOIUrl":"https://doi.org/10.1115/gt2018-75323","url":null,"abstract":"The current work focuses on mission based evaluation of a novel engine architecture arising from the conversion of a micro turbojet to a micro turbofan via introduction of a variable speed fan and bypass nozzle. The solution significantly improves maximum thrust by 260%, reduces fuel consumption by as much as 60% through maintaining the core independently running at its optimum, and enables a wider operational range, all the meanwhile preserving a simple single spool configuration. Particularly, the introduction of a variable speed fan, enables real-time optimization for both high speed cruise and low speed loitering. In order to characterize the performance of the adaptive cycle engine with increased number of controls (engine speed, gear ratio, bypass opening), a component map based thermodynamic study is used to contrast it against other similar propulsion systems with incrementally reduced input variables. In following, a shortest path based optimization is conducted over the locally minimum fuel consumption operating points, based on a set of gradient driven connectivity constraints for changes in gear ratio and bypass nozzle area. The resultant state transition graphs provide global optimum for fuel consumption at a thrust range in a given altitude and Mach flight envelope. Then, the engine model is coupled to a flight mechanics solver supplied with a conceptual design for a representative multipurpose UAV. Lastly, the associated mission benefits are demonstrated in surveillance and firefighting scenarios.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123205896","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Experimental Investigation of Droplets Splashing With Varying Pressures and Impact Angles to Predict Behaviour During Wet Compression","authors":"J. Bröder, C. Günther, F. Joos","doi":"10.1115/GT2018-76544","DOIUrl":"https://doi.org/10.1115/GT2018-76544","url":null,"abstract":"Wet compression is a powerful means to increase gas turbine power output and to perform fast load changes. These characteristics make this process suitable to compensate the unsteady supply of electric energy from renewable sources or to increase overall power output in times of high demand without the necessity to invest in higher peak capacity.\u0000 In case of high fogging water sprays are injected inside the intake duct of the gas turbine compressor resulting in droplets entering the first stages of the compressor. Inside, droplets above a specific size cannot follow the airflow properly, which makes it likely for them to collide with compressor surfaces and disintegrate. Characteristics of the ejected secondary droplets influence evaporation and condensation processes and thereby the thermodynamics of the compression process.\u0000 To investigate the characteristics of ejected secondary droplets, collisions between droplets and surfaces were recorded with a high-speed camera using the shadowgraphy method. From these recordings, quantity, diameter and velocity of secondary droplets were obtained. To resemble conditions at the first stages of a compressor under high fogging conditions, the experiments were conducted at elevated pressures up to 500 kPa and with varying impact angles from 0° to 30°. The Weber number normal to the surface was held constant at 550 and 700. The paper discusses the measured influence of splashing at simulated compressor conditions.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121159745","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Research on Optimal Matching Method of Variable Stator Vanes for Multi-Stage Compressor Based on Genetic Algorithm","authors":"Zhitao Wang, Fan Kuo, Ma Wenqi, Li Tielei, Shuying Li","doi":"10.1115/GT2018-76005","DOIUrl":"https://doi.org/10.1115/GT2018-76005","url":null,"abstract":"As one of the anti-surge technique, the adjusting scheme of VSV under off-design conditions has a significant impact on the performance of gas turbine. With the limitation of time and cost, it is difficult to study the adjusting scheme of VSV by experimental method under a wide operating range. With the development of the gas turbine simulation, integrated simulation technology is used to study the simulation of whole or part of gas turbine from different views and levels. It has become an effective way to optimize the performance of gas turbine. Based on the existing one-dimensional HARIKA algorithm and the zero dimensional gas turbine simulation model, a new compressor characteristic module and a scaling interface module are built up for studying the characteristics of the variable geometry compressor. The compressor one-dimensional characteristic calculation program is embedded into the zero dimensional gas turbine general model to replace the original compressor characteristic module. Taking the surge margin of LC and the efficiency of gas turbine as the optimization objectives, the optimal VSV matching angle of multi-stage compressor is obviously benefit from using the optimization algorithm based on genetic algorithm. In addition, this paper also analyzes the steady-state performance of the gas turbine. After optimization, the efficiency of the three-shaft gas turbine under different operating conditions was improved by 1.912% on average and the surge margin was increased by 2.78% meanwhile, the fuel consumption was reduced. Thus, the optimization of this paper has proved to be of great significance to improve the performance of gas turbine.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130763811","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Design and CFD Analysis of a 150kW 8-Stage ORC-ROT (Organic Rankine Cycle-Radial Outflow Turbine) and Performance Degradation due to Blade Tip Clearance of Labyrinth Seal","authors":"Y. Doğu, Ibrahim Günaydin, Zeynal Kılıçaslan, Tacettin İleri, S. Soğanci","doi":"10.1115/GT2018-75612","DOIUrl":"https://doi.org/10.1115/GT2018-75612","url":null,"abstract":"In this study, blade tip leakages were calculated for a Radial Outflow Turbine (ROT) designed for an Organic Rankine Cycle (ORC) at a 150kW power output. Since the turbine blade sizes are relatively very small for low-capacity systems, the leakages through the blade tip clearances considerably affect the turbine isentropic efficiency. Therefore, labyrinth seals were applied at the blade tips and the ROT’s performance degradation due to blade tip leakages was investigated.\u0000 In order to determine the preliminary ROT sizes, an in-house developed 1-D code was utilized. The blade profiles were optimized with CFD analyses to reach high power output and isentropic efficiency. The designed ROT has 8 stages. Toluene is used as the cycle fluid at inlet conditions of 24bar of total pressure, 310°C and outlet conditions of 0.25bar of static pressure. These conditions are chosen for exhaust conditions of a common biogas engine. Thus, the ORC is supposed to operate at a heat source temperature of 460°C and a heat sink temperature of 35°C. The turbine speed of 14000 rpm is determined.\u0000 The CFD model for the entire 3-D turbine geometry is built in the FlowVision software. The real gas equation is employed for the compressible flow. The SST turbulent flow model is employed. The CFD model uses transient state and rotating frame approaches.\u0000 Four blade tip configurations were analyzed. The CFD results reveal the followings. The turbine isentropic efficiency is calculated to be 87.62% for the unshrouded geometry with no clearance, which is an ideal case. For a manufacturable and manageable blade tip clearance of 0.2 mm, the turbine isentropic efficiency is calculated to be 71.03% for the unshrouded geometry. The shrouded geometry with the same clearance increases the efficiency to 74.03%. When a labyrinth seal is applied to the shrouded geometry, the efficiency reaches to 77.03%. The best practice in terms of turbine power output and efficiency is the shrouded geometry with labyrinth seal applications.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132978151","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Applying Dynamic Programming Algorithms to the Energy Management of Hybrid Electric Aircraft","authors":"T. Donateo, A. Ficarella, L. Spedicato","doi":"10.1115/GT2018-76500","DOIUrl":"https://doi.org/10.1115/GT2018-76500","url":null,"abstract":"To explore the application of dynamic programming (DP) to the energy management strategies of hybrid electric aircraft, a hybrid powertrain for a lightweight rotorcraft is introduced and its dynamic control model is designed. The model is conceived for the Agusta-Westland A109 helicopter, a twin-engine rotorcraft used in various roles, such as light transport, search-and-rescue and military roles. The turboshaft single spool engines are modeled with the use of performance maps that allow part load specific fuel consumption to be calculated as a function of actual power request and flight conditions. The state-of-the-art lithium polymer batteries are used for the hybridization and their behavior is evaluated by the Sheperd-Peukert model. The control problem is modeled through a graph structure where a node is obtained from the intersection between a time value, representing the starting of a phase of flight, and a splitting factor, representing the percentage of propulsive power required to the battery in such a phase. The edge connecting two nodes concerns with the state transition and the weight of the edge refers to the transition cost. The goal is to find an optimal splitting sequence to minimize the total cost over the whole mission, that is given with regard to speed and altitude. The Dijkstra algorithm, which allows the shortest energy path to be found between nodes in a graph, is used to look for the optimum. A local optimum is achieved when the cost is defined as the fuel consumption whereas the global optimum can be attained when the model is enhanced to include the effect of the battery usage into the cost.\u0000 The results are compared with the original non-hybrid case and the engine efficiency was suitable evaluated. The applicability to other mission data is suitably evaluated so as to deduce the concept of similarity of mission.","PeriodicalId":131179,"journal":{"name":"Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121178841","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}