The Experts below are selected from a list of 315 Experts worldwide ranked by ideXlab platform
Fakhre Ali - One of the best experts on this subject based on the ideXlab platform.
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multi objective optimization of a regenerative Rotorcraft powerplant trade off between overall engine weight and fuel economy
Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference twin-engine light Rotorcraft, modeled after the Bo105 helicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Second, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload-range capability and airworthiness (one-engine-inoperative) of the Rotorcraft.
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Multi-objective Optimization of Conceptual Rotorcraft Powerplants: Trade-off Between Rotorcraft Fuel Efficiency and Environmental Impact
Journal of Engineering for Gas Turbines and Power, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto D'ippolitoAbstract:This paper aims to present an integrated Rotorcraft conceptual design and analysis framework, deployed for the multidisciplinary design and optimization of regenerative powerplant configurations in terms of Rotorcraft operational and environmental performance. The proposed framework comprises a wide-range of individual modeling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance, and weight estimation as well as a novel physics-based, stirred reactor model for the rapid estimation of gas turbine gaseous emissions. A multi-objective particle swarm optimizer (mPSO) is coupled with the aforementioned integrated Rotorcraft multidisciplinary design framework. The combined approach is applied to conduct multidisciplinary design and optimization of a reference twin engine light civil Rotorcraft modeled after the Airbus-Helicopters Bo105 helicopter, operating on representative mission scenario. Through the implementation of a multi-objective optimization study, Pareto front models have been acquired, quantifying the optimum interrelationship between the mission fuel consumption and gaseous emissions for the representative Rotorcraft and a variety of engine configurations. The acquired optimum engine configurations are subsequently deployed for the design of conceptual Rotorcraft regenerative engines, targeting improved mission fuel economy, enhanced payload range capability, as well as improvements in the Rotorcraft overall environmental impact. The proposed methodology essentially constitutes an enabler in terms of focusing the multidisciplinary design and optimization of Rotorcraft powerplants within realistic, three-dimensional operations and toward the realization of their associated design trade-offs at mission level.
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design space exploration and optimization of conceptual Rotorcraft powerplants
Volume 3: Coal Biomass and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:This paper demonstrates the application of an integrated Rotorcraft multidisciplinary design and optimisation framework, deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for Rotorcraft. The proposed approach comprises a wide-range of individual modelling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance and weight estimation as well as a novel physics-based stirred reactor model, for the rapid estimation of various gas turbine gaseous emissions. A Single-Objective Particle Swarm Optimizer is coupled with the aforementioned Rotorcraft multidisciplinary design framework. The overall methodology is deployed for the design space exploration and optimisation of a reference multipurpose twin-engine light civil Rotorcraft, modelled after the Bo105 helicopter, employing two Rolls Royce Allison 250-C20B turboshaft engines. Through the implementation of single-objective optimization, notionally based optimum regenerative engine design configurations are acquired in terms of engine weight, mission fuel burn and mission gaseous emissions inventory, at constant technology level. The acquired optimum engine configurations are subsequently deployed for the design of conceptual regenerative Rotorcraft configurations, targeting improved mission fuel economy, enhanced payload range capability as well as improvements in the Rotorcraft overall environmental footprint, while maintaining the required airworthiness requirements. The proposed approach essentially constitutes an enabler in terms of focusing the multidisciplinary design of conceptual Rotorcraft powerplants to realistic, three-dimensional operations and towards the realization of their associated engine design trade-offs at mission level.Copyright © 2015 by ASME
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Design Space Exploration and Optimisation of an Advanced Propulsion System for Rotorcraft Applications
2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Greek SymbolsAbstract:Abstract A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference DOEtwin-engine light Rotorcraft, modelled after the Bo105 DPhelicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Secondly, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that, the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload -range capability and airworthiness (One-Engine-Inoperative) of the Rotorcraft.
Roberto D'ippolito - One of the best experts on this subject based on the ideXlab platform.
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Multi-objective Optimization of Conceptual Rotorcraft Powerplants: Trade-off Between Rotorcraft Fuel Efficiency and Environmental Impact
Journal of Engineering for Gas Turbines and Power, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto D'ippolitoAbstract:This paper aims to present an integrated Rotorcraft conceptual design and analysis framework, deployed for the multidisciplinary design and optimization of regenerative powerplant configurations in terms of Rotorcraft operational and environmental performance. The proposed framework comprises a wide-range of individual modeling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance, and weight estimation as well as a novel physics-based, stirred reactor model for the rapid estimation of gas turbine gaseous emissions. A multi-objective particle swarm optimizer (mPSO) is coupled with the aforementioned integrated Rotorcraft multidisciplinary design framework. The combined approach is applied to conduct multidisciplinary design and optimization of a reference twin engine light civil Rotorcraft modeled after the Airbus-Helicopters Bo105 helicopter, operating on representative mission scenario. Through the implementation of a multi-objective optimization study, Pareto front models have been acquired, quantifying the optimum interrelationship between the mission fuel consumption and gaseous emissions for the representative Rotorcraft and a variety of engine configurations. The acquired optimum engine configurations are subsequently deployed for the design of conceptual Rotorcraft regenerative engines, targeting improved mission fuel economy, enhanced payload range capability, as well as improvements in the Rotorcraft overall environmental impact. The proposed methodology essentially constitutes an enabler in terms of focusing the multidisciplinary design and optimization of Rotorcraft powerplants within realistic, three-dimensional operations and toward the realization of their associated design trade-offs at mission level.
Vassilios Pachidis - One of the best experts on this subject based on the ideXlab platform.
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multi objective optimization of a regenerative Rotorcraft powerplant trade off between overall engine weight and fuel economy
Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference twin-engine light Rotorcraft, modeled after the Bo105 helicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Second, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload-range capability and airworthiness (one-engine-inoperative) of the Rotorcraft.
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Multi-objective Optimization of Conceptual Rotorcraft Powerplants: Trade-off Between Rotorcraft Fuel Efficiency and Environmental Impact
Journal of Engineering for Gas Turbines and Power, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto D'ippolitoAbstract:This paper aims to present an integrated Rotorcraft conceptual design and analysis framework, deployed for the multidisciplinary design and optimization of regenerative powerplant configurations in terms of Rotorcraft operational and environmental performance. The proposed framework comprises a wide-range of individual modeling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance, and weight estimation as well as a novel physics-based, stirred reactor model for the rapid estimation of gas turbine gaseous emissions. A multi-objective particle swarm optimizer (mPSO) is coupled with the aforementioned integrated Rotorcraft multidisciplinary design framework. The combined approach is applied to conduct multidisciplinary design and optimization of a reference twin engine light civil Rotorcraft modeled after the Airbus-Helicopters Bo105 helicopter, operating on representative mission scenario. Through the implementation of a multi-objective optimization study, Pareto front models have been acquired, quantifying the optimum interrelationship between the mission fuel consumption and gaseous emissions for the representative Rotorcraft and a variety of engine configurations. The acquired optimum engine configurations are subsequently deployed for the design of conceptual Rotorcraft regenerative engines, targeting improved mission fuel economy, enhanced payload range capability, as well as improvements in the Rotorcraft overall environmental impact. The proposed methodology essentially constitutes an enabler in terms of focusing the multidisciplinary design and optimization of Rotorcraft powerplants within realistic, three-dimensional operations and toward the realization of their associated design trade-offs at mission level.
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design space exploration and optimization of conceptual Rotorcraft powerplants
Volume 3: Coal Biomass and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:This paper demonstrates the application of an integrated Rotorcraft multidisciplinary design and optimisation framework, deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for Rotorcraft. The proposed approach comprises a wide-range of individual modelling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance and weight estimation as well as a novel physics-based stirred reactor model, for the rapid estimation of various gas turbine gaseous emissions. A Single-Objective Particle Swarm Optimizer is coupled with the aforementioned Rotorcraft multidisciplinary design framework. The overall methodology is deployed for the design space exploration and optimisation of a reference multipurpose twin-engine light civil Rotorcraft, modelled after the Bo105 helicopter, employing two Rolls Royce Allison 250-C20B turboshaft engines. Through the implementation of single-objective optimization, notionally based optimum regenerative engine design configurations are acquired in terms of engine weight, mission fuel burn and mission gaseous emissions inventory, at constant technology level. The acquired optimum engine configurations are subsequently deployed for the design of conceptual regenerative Rotorcraft configurations, targeting improved mission fuel economy, enhanced payload range capability as well as improvements in the Rotorcraft overall environmental footprint, while maintaining the required airworthiness requirements. The proposed approach essentially constitutes an enabler in terms of focusing the multidisciplinary design of conceptual Rotorcraft powerplants to realistic, three-dimensional operations and towards the realization of their associated engine design trade-offs at mission level.Copyright © 2015 by ASME
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Design Space Exploration and Optimisation of an Advanced Propulsion System for Rotorcraft Applications
2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Greek SymbolsAbstract:Abstract A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference DOEtwin-engine light Rotorcraft, modelled after the Bo105 DPhelicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Secondly, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that, the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload -range capability and airworthiness (One-Engine-Inoperative) of the Rotorcraft.
Konstantinos Tzanidakis - One of the best experts on this subject based on the ideXlab platform.
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multi objective optimization of a regenerative Rotorcraft powerplant trade off between overall engine weight and fuel economy
Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference twin-engine light Rotorcraft, modeled after the Bo105 helicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Second, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload-range capability and airworthiness (one-engine-inoperative) of the Rotorcraft.
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Multi-objective Optimization of Conceptual Rotorcraft Powerplants: Trade-off Between Rotorcraft Fuel Efficiency and Environmental Impact
Journal of Engineering for Gas Turbines and Power, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto D'ippolitoAbstract:This paper aims to present an integrated Rotorcraft conceptual design and analysis framework, deployed for the multidisciplinary design and optimization of regenerative powerplant configurations in terms of Rotorcraft operational and environmental performance. The proposed framework comprises a wide-range of individual modeling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance, and weight estimation as well as a novel physics-based, stirred reactor model for the rapid estimation of gas turbine gaseous emissions. A multi-objective particle swarm optimizer (mPSO) is coupled with the aforementioned integrated Rotorcraft multidisciplinary design framework. The combined approach is applied to conduct multidisciplinary design and optimization of a reference twin engine light civil Rotorcraft modeled after the Airbus-Helicopters Bo105 helicopter, operating on representative mission scenario. Through the implementation of a multi-objective optimization study, Pareto front models have been acquired, quantifying the optimum interrelationship between the mission fuel consumption and gaseous emissions for the representative Rotorcraft and a variety of engine configurations. The acquired optimum engine configurations are subsequently deployed for the design of conceptual Rotorcraft regenerative engines, targeting improved mission fuel economy, enhanced payload range capability, as well as improvements in the Rotorcraft overall environmental impact. The proposed methodology essentially constitutes an enabler in terms of focusing the multidisciplinary design and optimization of Rotorcraft powerplants within realistic, three-dimensional operations and toward the realization of their associated design trade-offs at mission level.
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design space exploration and optimization of conceptual Rotorcraft powerplants
Volume 3: Coal Biomass and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:This paper demonstrates the application of an integrated Rotorcraft multidisciplinary design and optimisation framework, deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for Rotorcraft. The proposed approach comprises a wide-range of individual modelling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance and weight estimation as well as a novel physics-based stirred reactor model, for the rapid estimation of various gas turbine gaseous emissions. A Single-Objective Particle Swarm Optimizer is coupled with the aforementioned Rotorcraft multidisciplinary design framework. The overall methodology is deployed for the design space exploration and optimisation of a reference multipurpose twin-engine light civil Rotorcraft, modelled after the Bo105 helicopter, employing two Rolls Royce Allison 250-C20B turboshaft engines. Through the implementation of single-objective optimization, notionally based optimum regenerative engine design configurations are acquired in terms of engine weight, mission fuel burn and mission gaseous emissions inventory, at constant technology level. The acquired optimum engine configurations are subsequently deployed for the design of conceptual regenerative Rotorcraft configurations, targeting improved mission fuel economy, enhanced payload range capability as well as improvements in the Rotorcraft overall environmental footprint, while maintaining the required airworthiness requirements. The proposed approach essentially constitutes an enabler in terms of focusing the multidisciplinary design of conceptual Rotorcraft powerplants to realistic, three-dimensional operations and towards the realization of their associated engine design trade-offs at mission level.Copyright © 2015 by ASME
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Design Space Exploration and Optimisation of an Advanced Propulsion System for Rotorcraft Applications
2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Greek SymbolsAbstract:Abstract A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference DOEtwin-engine light Rotorcraft, modelled after the Bo105 DPhelicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Secondly, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that, the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload -range capability and airworthiness (One-Engine-Inoperative) of the Rotorcraft.
Ioannis Goulos - One of the best experts on this subject based on the ideXlab platform.
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multi objective optimization of a regenerative Rotorcraft powerplant trade off between overall engine weight and fuel economy
Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference twin-engine light Rotorcraft, modeled after the Bo105 helicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Second, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload-range capability and airworthiness (one-engine-inoperative) of the Rotorcraft.
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Multi-objective Optimization of Conceptual Rotorcraft Powerplants: Trade-off Between Rotorcraft Fuel Efficiency and Environmental Impact
Journal of Engineering for Gas Turbines and Power, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto D'ippolitoAbstract:This paper aims to present an integrated Rotorcraft conceptual design and analysis framework, deployed for the multidisciplinary design and optimization of regenerative powerplant configurations in terms of Rotorcraft operational and environmental performance. The proposed framework comprises a wide-range of individual modeling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance, and weight estimation as well as a novel physics-based, stirred reactor model for the rapid estimation of gas turbine gaseous emissions. A multi-objective particle swarm optimizer (mPSO) is coupled with the aforementioned integrated Rotorcraft multidisciplinary design framework. The combined approach is applied to conduct multidisciplinary design and optimization of a reference twin engine light civil Rotorcraft modeled after the Airbus-Helicopters Bo105 helicopter, operating on representative mission scenario. Through the implementation of a multi-objective optimization study, Pareto front models have been acquired, quantifying the optimum interrelationship between the mission fuel consumption and gaseous emissions for the representative Rotorcraft and a variety of engine configurations. The acquired optimum engine configurations are subsequently deployed for the design of conceptual Rotorcraft regenerative engines, targeting improved mission fuel economy, enhanced payload range capability, as well as improvements in the Rotorcraft overall environmental impact. The proposed methodology essentially constitutes an enabler in terms of focusing the multidisciplinary design and optimization of Rotorcraft powerplants within realistic, three-dimensional operations and toward the realization of their associated design trade-offs at mission level.
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design space exploration and optimization of conceptual Rotorcraft powerplants
Volume 3: Coal Biomass and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration, 2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Roberto DippolitoAbstract:This paper demonstrates the application of an integrated Rotorcraft multidisciplinary design and optimisation framework, deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for Rotorcraft. The proposed approach comprises a wide-range of individual modelling theories applicable to Rotorcraft flight dynamics, gas turbine engine performance and weight estimation as well as a novel physics-based stirred reactor model, for the rapid estimation of various gas turbine gaseous emissions. A Single-Objective Particle Swarm Optimizer is coupled with the aforementioned Rotorcraft multidisciplinary design framework. The overall methodology is deployed for the design space exploration and optimisation of a reference multipurpose twin-engine light civil Rotorcraft, modelled after the Bo105 helicopter, employing two Rolls Royce Allison 250-C20B turboshaft engines. Through the implementation of single-objective optimization, notionally based optimum regenerative engine design configurations are acquired in terms of engine weight, mission fuel burn and mission gaseous emissions inventory, at constant technology level. The acquired optimum engine configurations are subsequently deployed for the design of conceptual regenerative Rotorcraft configurations, targeting improved mission fuel economy, enhanced payload range capability as well as improvements in the Rotorcraft overall environmental footprint, while maintaining the required airworthiness requirements. The proposed approach essentially constitutes an enabler in terms of focusing the multidisciplinary design of conceptual Rotorcraft powerplants to realistic, three-dimensional operations and towards the realization of their associated engine design trade-offs at mission level.Copyright © 2015 by ASME
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Design Space Exploration and Optimisation of an Advanced Propulsion System for Rotorcraft Applications
2015Co-Authors: Fakhre Ali, Konstantinos Tzanidakis, Ioannis Goulos, Vassilios Pachidis, Greek SymbolsAbstract:Abstract A computationally efficient and cost effective simulation framework has been implemented to perform design space exploration and multi-objective optimization for a conceptual regenerative Rotorcraft powerplant configuration at mission level. The proposed framework is developed by coupling a comprehensive Rotorcraft mission analysis code with a design space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a reference DOEtwin-engine light Rotorcraft, modelled after the Bo105 DPhelicopter, manufactured by Airbus Helicopters. Initially, a sensitivity analysis of the regenerative engine is carried out to quantify the relationship between the engine thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Secondly, through the execution of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between the fuel economy offered by a regenerative engine and its associated weight penalty. The optimum sets of cycle design parameters obtained from the structured Pareto front suggest that the employed heat effectiveness is the key design parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by the acquired Pareto front, it is shown that, the fuel economy offered by the simple cycle Rotorcraft engine can be substantially improved with the implementation of regeneration technology, without degrading the payload -range capability and airworthiness (One-Engine-Inoperative) of the Rotorcraft.
