Exergy Approach to Decision-Based Design of Integrated Aircraft Thermal Systems

Figliola, Richard; Tipton, Robert; Li, H.

doi:10.2514/2.3056

Cited by 44 publications

(9 citation statements)

References 5 publications

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“…Additionally, researchers can compare the performance of different subsystems with exergy analysis. Tipton et al [93] applied an exergy analysis to an IPTMS where the optimisation objectives were exergetic efficiency and total take-off weight. The entropy generated by the IPTMS subsystems is estimated and the total entropy generation of the overall system is found.…”

Section: Iptms Analysis Methodsmentioning

confidence: 99%

Integrated Power and Thermal Management Systems for Civil Aircraft: Review, Challenges, and Future Opportunities

Ouyang,

Nikolaidis,

Jafari

2024

Applied Sciences

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Projects related to green aviation designed to achieve fuel savings and emission reductions are increasingly being established in response to growing concerns over climate change. Within the aviation industry, there is a growing trend towards the electrification of aircraft, with more-electric aircraft (MEA) and all-electric aircraft (AEA) being proposed. However, increasing electrification causes challenges with conventional thermal management system (TMS) and power management system (PMS) designs in aircraft. As a result, the integrated power and thermal management system (IPTMS) has been developed for energy-optimised aircraft projects. This review paper aims to review recent IPTMS progress and explore potential design solutions for civil aircraft. Firstly, the paper reviews the IPTMS in electrified propulsion aircraft (EPA), presenting the architectures and challenges of the propulsion systems, the TMS cooling strategies, and the power management optimisation. Then, several research topics in IPTMS are reviewed in detail: architecture design, power management optimisation, modelling, and analysis method development. Through the review of state-of-the-art IPTMS research, the challenges and future opportunities and requirements of IPTMS design are discussed. Based on the discussions, two potential solutions for IPTMS to address the challenges of civil EPA are proposed, including the combination of architecture design and power management optimisation and the combination of modelling and analysis methods.

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Section: Iptms Analysis Methodsmentioning

confidence: 99%

Integrated Power and Thermal Management Systems for Civil Aircraft: Review, Challenges, and Future Opportunities

Ouyang,

Nikolaidis,

Jafari

2024

Applied Sciences

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“…In the case of non-negligible tank wall heat transfer,Q W from equation (5) can be introduced into the energy equation (9) as…”

Section: Iiib Non-negligible Tank Wall Heat Transfermentioning

confidence: 99%

“…Many fuel thermal management system analysis tools and approaches have been developed and demonstrated. [9][10][11][12] Fuel heating in modern aircraft is now understood to be one member of a class of related dynamic phenomenon, which also includes electrical power dynamics associated with actuators and other transient electrical loads. For this reason, research is now increasingly being conducted in time-accurate dynamical simulations of fuel temperature throughout entire aircraft missions.…”

Section: Introductionmentioning

confidence: 99%

Tank Heating Model for Aircraft Fuel Thermal Systems with Recirculation

German

2012

Journal of Propulsion and Power

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Fuel thermal management has become an important consideration in the design and operation of modern high performance aircraft. In many cases, fuel is a primary heat sink for thermal loads associated with the cooling of the airframe as well as propulsion, electronic, actuator, and payload systems. It is now common for thermal systems to recirculate warm fuel to the tanks, resulting in a rise in temperature in the mission fuel mass. In this paper, a model is presented that integrates heat transfer during mission segments to determine the thermal endurance of an aircraft in terms of fuel tank temperature. The model is intended for early-phase trade studies to determine whether a proposed vehicle will be restricted in operational performance by tank temperature limits.

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“…There are a number of studies available in the open literature for exergy and exergoeconomic analyses as a tool, such as spark ignition internal combustion engines (Zhecheng, Brun, and Badin 1991;Rakopoulos 1993;Kopac and Kokturk 2005;Abu-Nada et al 2007;Sezer and Bilgin 2008a,b;Ameri et al 2010), the aerospace industry (Bejan and Siems 2001;Etelen and Rose 2001;Roth and Mavris 2001;Figliola, Tipton, and Li 2003;Moorhouse 2003;Rosen and Etelen 2004;Leo and Pérez-Grande 2005;Pellegrini, Gandolfi, and Silva 2007;Turgut, Karakoc, and Hepbasli 2007;Periannan, von Spakovsky, and Moorhouse 2008;Turgut, Karakoc, and Hepbasli 2009a;Turgut et al 2009b;Tona et al 2010), and other systems such as power plants, wind turbine, cement plants, heat pumps, etc. (Kim et al 1998;Bilgen 2000;Kwon, Kwak, and Oh 2001;Cziesla, Tsatsaronis, Gao 2006;Zaleta et al 2007;Oktay and Dincer 2009;Ozgener, Ozgener, and Dincer 2009;Sogut, Oktay, and Hepbasli 2009;Ahmadi and Dincer 2010;Sogut, Oktay, and Karakoc 2010a;Sogut et al 2010b;Coskun, Oktay, and Dincer 2011;Gungor, Erbay, and Hepbasli 2011).…”

Section: Introductionmentioning

confidence: 99%

Exergoeconomic Environmental Optimization of Piston-Prop Aircraft Engines

Altuntaş

Karakoç

Hepbaşlı

2014

International Journal of Green Energy

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In this study, exergy, exergoeconomic, exergoenvironmental analyses, and exergoeconomic environmental optimization are applied to a four-cylinder, spark ignition, naturally aspirated and air-cooled piston-prop aircraft engine in the cruise phase of flight for the first time to the best of the authors`knowledge. Here, three piston-prop aircraft engine parameters (altitude, air-fuel ratio (AF), and rated power setting (PS)) are selected for optimization purposes. All exergy, exergoeconomic, and exergoenvironmental values are calculated first. These values are then optimized to find the best results of all analyses. The best altitude, AF ratio, and PS values are finally found while the maximum exergy efficiency, the minimum product specific environmental impact, and the minimum average unit fuel exergy cost are obtained. The best results of optimization indicated that the maximum exergy efficiency varied between 19.54% and 19.80%, the minimum unit fuel exergy cost ranged from 126.30 $/GJ to 127.23 $/GJ, and the minimum specific environmental impact of production was in the range of 8.70-9.59 mPts/MJ. Based on the results obtained, for ensuring the optimum conditions, the low AF ratios and the low-altitude flight at high rated power settings have to be selected.

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Exergy Approach to Decision-Based Design of Integrated Aircraft Thermal Systems

Cited by 44 publications

References 5 publications

Integrated Power and Thermal Management Systems for Civil Aircraft: Review, Challenges, and Future Opportunities

Integrated Power and Thermal Management Systems for Civil Aircraft: Review, Challenges, and Future Opportunities

Tank Heating Model for Aircraft Fuel Thermal Systems with Recirculation

Exergoeconomic Environmental Optimization of Piston-Prop Aircraft Engines

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