Abstract:Deployed on a commercial airplane, proton exchange membrane fuel cells may offer emissions reductions, thermal efficiency gains, and enable locating the power near the point of use. This work seeks to understand whether on-board fuel cell systems are technically feasible, and, if so, if they offer a performance advantage for the airplane as a whole.Through hardware analysis and thermodynamic and electrical simulation, we found that while adding a fuel cell system using today's technology for the PEM fuel cell … Show more
“…Even though current PEM FC technology cannot be used to completely replace the APU on large civil airliners, partial substitution of existing electrical generation equipment for fuel cell technology should be considered on a case-by-case basis [14].…”
Section: Combined Model Resultsmentioning
confidence: 99%
“…Several studies have previously considered the integration of fuel cell systems into aircraft [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. Different aspects of the integration process have been considered.…”
Section: Introductionmentioning
confidence: 99%
“…Different aspects of the integration process have been considered. These included the theoretical integration of a FC system to partially cover the electrical load on the APU on a Boeing 787-8 [14]. In addition, working prototypes on a small remote piloted scale have been designed and flown [4][5][6][9][10][11].…”
mentioning
confidence: 99%
“…A possible alternative would be to use SOFC technology as it is capable of being fuelled by light hydrocarbons which could potentially be stored in a similar manner to current jet fuel. The use of SOFCs in aircraft has been a topic of extensive research [4,[69][70] with key conclusions meriting the efficiency of SOFC technology and the potential to use the highquality waste heat.Even though current PEM FC technology cannot be used to completely replace the APU on large civil airliners, partial substitution of existing electrical generation equipment for fuel cell technology should be considered on a case-by-case basis [14].Page 8 of 1106/22/2017
…”
mentioning
confidence: 99%
“…The significantly higher operating temperature of a SOFC (700-1,000°C) compared with 60-100°C for a PEM FC [3] allows it to reform light fossil fuels such as methane into hydrogen. However, if PEM fuel cells are used, then their relatively low operating temperature could potentially reduce the thermal signature of the electrical generation and/or propulsive system of the aircraft.Several studies have previously considered the integration of fuel cell systems into aircraft [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. Different aspects of the integration process have been considered.…”
Electrification of aircraft is on track to be a future key design principal due to the increasing pressure on the aviation industry to significantly reduce harmful emissions by 2050 and the increased use of electrical equipment. This has led to an increased focus on the research and development of alternative power sources for aircraft, including fuel cells. These alternative power sources could either be used to provide propulsive power or as an Auxiliary Power Unit (APU). Previous studies have considered isolated design cases where a fuel cell system was tailored for their specific application. To accommodate for the large variation between aircraft, this study covers the design of an empirical model, which will be used to size a fuel cell system for any given aircraft based on basic design parameters. The model was constructed utilising aircraft categorisation, fuel cell sizing and balance of plant sub-models. Fifteen aircraft categories were defined based on the primary function and propulsion method of the aircraft. For each category, propulsive power and electrical generation requirements were calculated. Based on the results from categorisation and the flight envelope of the aircraft, fuel cell and balance of plant systems are defined. The total system mass and volume are given as outputs, along with polarisation and power curves for the fuel cell. This study finds that the model can accurately predict the electrical generation capability and propulsive requirements across the defined aircraft categories. In addition, the model can appropriately define key, high-level fuel cell parameters based on current Polymer Electrolyte Membrane (PEM) technology. Total fuel cell system mass and volume are calculated and shown to be reasonable for small aircraft. For larger aircraft with a Maximum Take-Off Weight (MTOW) greater than 50,000kg, current PEM technology is not able to match the gravimetric power density of existing APUs.
IntroductionElectrification of aircraft is on track to be a key design principal in the future due to the increasing pressure on the whole aviation industry to significantly reduce harmful emissions by 2050 [1]. This has led to an increased focus on the research and development of alternative power sources for aircraft, including fuel cells. These alternative power sources could either be used to provide propulsive power or as an Auxiliary Power Unit (APU).Hydrogen fuel cells produce electricity through an exothermic electrochemical reaction between hydrogen and oxygen. This highly efficient reaction only produces heat and water as by-products [2]. Two Fuel Cell (FC) technologies currently being researched for use in aerospace applications are Solid Oxide Fuel Cells (SOFC) and Polymer Electrolyte Membrane (PEM) fuel cells. A key difference between these two technologies is their operating temperature. The significantly higher operating temperature of a SOFC (700-1,000°C) compared with 60-100°C for a PEM FC [3] allows it to reform light fossil fuels such as methane into hydrogen. Ho...
“…Even though current PEM FC technology cannot be used to completely replace the APU on large civil airliners, partial substitution of existing electrical generation equipment for fuel cell technology should be considered on a case-by-case basis [14].…”
Section: Combined Model Resultsmentioning
confidence: 99%
“…Several studies have previously considered the integration of fuel cell systems into aircraft [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. Different aspects of the integration process have been considered.…”
Section: Introductionmentioning
confidence: 99%
“…Different aspects of the integration process have been considered. These included the theoretical integration of a FC system to partially cover the electrical load on the APU on a Boeing 787-8 [14]. In addition, working prototypes on a small remote piloted scale have been designed and flown [4][5][6][9][10][11].…”
mentioning
confidence: 99%
“…A possible alternative would be to use SOFC technology as it is capable of being fuelled by light hydrocarbons which could potentially be stored in a similar manner to current jet fuel. The use of SOFCs in aircraft has been a topic of extensive research [4,[69][70] with key conclusions meriting the efficiency of SOFC technology and the potential to use the highquality waste heat.Even though current PEM FC technology cannot be used to completely replace the APU on large civil airliners, partial substitution of existing electrical generation equipment for fuel cell technology should be considered on a case-by-case basis [14].Page 8 of 1106/22/2017
…”
mentioning
confidence: 99%
“…The significantly higher operating temperature of a SOFC (700-1,000°C) compared with 60-100°C for a PEM FC [3] allows it to reform light fossil fuels such as methane into hydrogen. However, if PEM fuel cells are used, then their relatively low operating temperature could potentially reduce the thermal signature of the electrical generation and/or propulsive system of the aircraft.Several studies have previously considered the integration of fuel cell systems into aircraft [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. Different aspects of the integration process have been considered.…”
Electrification of aircraft is on track to be a future key design principal due to the increasing pressure on the aviation industry to significantly reduce harmful emissions by 2050 and the increased use of electrical equipment. This has led to an increased focus on the research and development of alternative power sources for aircraft, including fuel cells. These alternative power sources could either be used to provide propulsive power or as an Auxiliary Power Unit (APU). Previous studies have considered isolated design cases where a fuel cell system was tailored for their specific application. To accommodate for the large variation between aircraft, this study covers the design of an empirical model, which will be used to size a fuel cell system for any given aircraft based on basic design parameters. The model was constructed utilising aircraft categorisation, fuel cell sizing and balance of plant sub-models. Fifteen aircraft categories were defined based on the primary function and propulsion method of the aircraft. For each category, propulsive power and electrical generation requirements were calculated. Based on the results from categorisation and the flight envelope of the aircraft, fuel cell and balance of plant systems are defined. The total system mass and volume are given as outputs, along with polarisation and power curves for the fuel cell. This study finds that the model can accurately predict the electrical generation capability and propulsive requirements across the defined aircraft categories. In addition, the model can appropriately define key, high-level fuel cell parameters based on current Polymer Electrolyte Membrane (PEM) technology. Total fuel cell system mass and volume are calculated and shown to be reasonable for small aircraft. For larger aircraft with a Maximum Take-Off Weight (MTOW) greater than 50,000kg, current PEM technology is not able to match the gravimetric power density of existing APUs.
IntroductionElectrification of aircraft is on track to be a key design principal in the future due to the increasing pressure on the whole aviation industry to significantly reduce harmful emissions by 2050 [1]. This has led to an increased focus on the research and development of alternative power sources for aircraft, including fuel cells. These alternative power sources could either be used to provide propulsive power or as an Auxiliary Power Unit (APU).Hydrogen fuel cells produce electricity through an exothermic electrochemical reaction between hydrogen and oxygen. This highly efficient reaction only produces heat and water as by-products [2]. Two Fuel Cell (FC) technologies currently being researched for use in aerospace applications are Solid Oxide Fuel Cells (SOFC) and Polymer Electrolyte Membrane (PEM) fuel cells. A key difference between these two technologies is their operating temperature. The significantly higher operating temperature of a SOFC (700-1,000°C) compared with 60-100°C for a PEM FC [3] allows it to reform light fossil fuels such as methane into hydrogen. Ho...
Summary
This article proposes a component‐sizing problem for a hybrid unmanned aircraft alongside a coordinated energy consumption and flight scheduling. The goal is to simultaneously minimize the fuel consumption, the gaseous emission, and the overall costs of components (capital and operating costs) including fuel cell, battery, electric motor, and thermal engines. To this end, a non‐linear programming is proposed, and by an efficient decomposition method, it is solved under GAMS. The numerical results are compared with some evolutionary algorithms and showed that the proposed optimization framework exerts influence on the overall costs, energy efficiency, and computation time.
The use of fuel cell technology offers benefits to many applications beyond light‐duty vehicles, and many of these are currently commercially viable or have the potential to be in the near term. These include material‐handling equipment, construction equipment, handheld and portable power, telecom backup power, airport ground support equipment, aerospace power, and maritime power.
In all of these applications, fuel cells can provide immediate benefits in terms of decreased fossil‐fuel use, reduced criteria pollutants and greenhouse gases, and delivery of new capabilities. Just as important, they can also be leveraged to facilitate the eventual introduction of fuel cell light‐duty vehicles by providing experience in both fuel cells and hydrogen that helps to refine products, drive down cost, reconcile codes and standards issues, make hydrogen fuel more available, and introduce familiarity with the technology to the public. In the words of the
US DOE
's Fuel Cell Technologies Office Market Transformation subprogram, these near‐term applications “help overcome nontechnical challenges to the expansion of hydrogen and fuel cell technologies into the broader vehicular marketplace.”
The applications mentioned earlier are in varying states of commercial viability and development yet all are contributing to these goals. As experience and performance enhancements continue, the opportunity for new applications increases.
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