The Experts below are selected from a list of 3039 Experts worldwide ranked by ideXlab platform
Kyprianidis Konstantinos - One of the best experts on this subject based on the ideXlab platform.
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Multi-Point Design of Parallel Hybrid Aero Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2020Co-Authors: Sielemann Michael, Co\uefc Cl\ue9ment, Zhao Xin, Diamantidou, Dimitra Eirini, Kyprianidis KonstantinosAbstract:A Parallel Hybrid Configuration is a feasible means to reduce fuel consumption of gas turbines propelling aircraft. It introduces an electric drive on one of the spools of the gas turbine, typically the low pressure spool. The electric drive is supplied by a battery, which can also be charged when excess power is available (for instance during conditions requiring handling bleed in conventional designs). It also requires a thermal management system to dissipate heat away from electric components. While the scientific literature describes Parallel Hybrid studies and anticipated benefits assuming various future entry into service dates, there is limited information on the design of the gas turbine component of such a system. For conventional gas turbines, multi-point design schemes are used. This paper describes, in a consistent fashion and based on a formalized notation, how such multi-point design schemes are applied to Parallel Hybrid aero engines. It interprets published approaches, fills gaps in methodology descriptions with meaningful assumptions and summarizes design intent. It also discusses cycle designs generated by different methodologies based on the same cycle model. Results show that closure equations prescribing boost power can be preferable over closure equations prescribing temperature ratios for uniqueness and engineering intuitiveness while the latter can be beneficial in a second step for design space exploration
Sielemann Michael - One of the best experts on this subject based on the ideXlab platform.
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Multi-Point Design of Parallel Hybrid Aero Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2020Co-Authors: Sielemann Michael, Co\uefc Cl\ue9ment, Zhao Xin, Diamantidou, Dimitra Eirini, Kyprianidis KonstantinosAbstract:A Parallel Hybrid Configuration is a feasible means to reduce fuel consumption of gas turbines propelling aircraft. It introduces an electric drive on one of the spools of the gas turbine, typically the low pressure spool. The electric drive is supplied by a battery, which can also be charged when excess power is available (for instance during conditions requiring handling bleed in conventional designs). It also requires a thermal management system to dissipate heat away from electric components. While the scientific literature describes Parallel Hybrid studies and anticipated benefits assuming various future entry into service dates, there is limited information on the design of the gas turbine component of such a system. For conventional gas turbines, multi-point design schemes are used. This paper describes, in a consistent fashion and based on a formalized notation, how such multi-point design schemes are applied to Parallel Hybrid aero engines. It interprets published approaches, fills gaps in methodology descriptions with meaningful assumptions and summarizes design intent. It also discusses cycle designs generated by different methodologies based on the same cycle model. Results show that closure equations prescribing boost power can be preferable over closure equations prescribing temperature ratios for uniqueness and engineering intuitiveness while the latter can be beneficial in a second step for design space exploration
Zhao Xin - One of the best experts on this subject based on the ideXlab platform.
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Multi-Point Design of Parallel Hybrid Aero Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2020Co-Authors: Sielemann Michael, Co\uefc Cl\ue9ment, Zhao Xin, Diamantidou, Dimitra Eirini, Kyprianidis KonstantinosAbstract:A Parallel Hybrid Configuration is a feasible means to reduce fuel consumption of gas turbines propelling aircraft. It introduces an electric drive on one of the spools of the gas turbine, typically the low pressure spool. The electric drive is supplied by a battery, which can also be charged when excess power is available (for instance during conditions requiring handling bleed in conventional designs). It also requires a thermal management system to dissipate heat away from electric components. While the scientific literature describes Parallel Hybrid studies and anticipated benefits assuming various future entry into service dates, there is limited information on the design of the gas turbine component of such a system. For conventional gas turbines, multi-point design schemes are used. This paper describes, in a consistent fashion and based on a formalized notation, how such multi-point design schemes are applied to Parallel Hybrid aero engines. It interprets published approaches, fills gaps in methodology descriptions with meaningful assumptions and summarizes design intent. It also discusses cycle designs generated by different methodologies based on the same cycle model. Results show that closure equations prescribing boost power can be preferable over closure equations prescribing temperature ratios for uniqueness and engineering intuitiveness while the latter can be beneficial in a second step for design space exploration
Diamantidou, Dimitra Eirini - One of the best experts on this subject based on the ideXlab platform.
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Multi-Point Design of Parallel Hybrid Aero Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2020Co-Authors: Sielemann Michael, Co\uefc Cl\ue9ment, Zhao Xin, Diamantidou, Dimitra Eirini, Kyprianidis KonstantinosAbstract:A Parallel Hybrid Configuration is a feasible means to reduce fuel consumption of gas turbines propelling aircraft. It introduces an electric drive on one of the spools of the gas turbine, typically the low pressure spool. The electric drive is supplied by a battery, which can also be charged when excess power is available (for instance during conditions requiring handling bleed in conventional designs). It also requires a thermal management system to dissipate heat away from electric components. While the scientific literature describes Parallel Hybrid studies and anticipated benefits assuming various future entry into service dates, there is limited information on the design of the gas turbine component of such a system. For conventional gas turbines, multi-point design schemes are used. This paper describes, in a consistent fashion and based on a formalized notation, how such multi-point design schemes are applied to Parallel Hybrid aero engines. It interprets published approaches, fills gaps in methodology descriptions with meaningful assumptions and summarizes design intent. It also discusses cycle designs generated by different methodologies based on the same cycle model. Results show that closure equations prescribing boost power can be preferable over closure equations prescribing temperature ratios for uniqueness and engineering intuitiveness while the latter can be beneficial in a second step for design space exploration
Co\uefc Cl\ue9ment - One of the best experts on this subject based on the ideXlab platform.
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Multi-Point Design of Parallel Hybrid Aero Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2020Co-Authors: Sielemann Michael, Co\uefc Cl\ue9ment, Zhao Xin, Diamantidou, Dimitra Eirini, Kyprianidis KonstantinosAbstract:A Parallel Hybrid Configuration is a feasible means to reduce fuel consumption of gas turbines propelling aircraft. It introduces an electric drive on one of the spools of the gas turbine, typically the low pressure spool. The electric drive is supplied by a battery, which can also be charged when excess power is available (for instance during conditions requiring handling bleed in conventional designs). It also requires a thermal management system to dissipate heat away from electric components. While the scientific literature describes Parallel Hybrid studies and anticipated benefits assuming various future entry into service dates, there is limited information on the design of the gas turbine component of such a system. For conventional gas turbines, multi-point design schemes are used. This paper describes, in a consistent fashion and based on a formalized notation, how such multi-point design schemes are applied to Parallel Hybrid aero engines. It interprets published approaches, fills gaps in methodology descriptions with meaningful assumptions and summarizes design intent. It also discusses cycle designs generated by different methodologies based on the same cycle model. Results show that closure equations prescribing boost power can be preferable over closure equations prescribing temperature ratios for uniqueness and engineering intuitiveness while the latter can be beneficial in a second step for design space exploration
