Parallel Hybrid-Electric Powertrain Sizing on Regional Turboprop Aircraft with Consideration for Certification Performance Requirements

Quillet, Dominik; Boulanger, Vincent; Rancourt, David; Freer, Richard; Poumellec, Bertrand

doi:10.2514/6.2021-2443

Cited by 11 publications

(7 citation statements)

References 7 publications

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“…The conceptual level framework combines overall sizing and operation effects on aircraft performance for the two hybrid designs considered. The chosen modelling approach is based upon low fidelity models used to compute time marching inverse simulation with a steady-state energy approach on a point mass aircraft (Quillet et al , 2021). From prescribed kinematics, the power chain is computed upstream to monitor the total energy consumption at sources.…”

Section: Mission Analysis Frameworkmentioning

confidence: 99%

Impact of OEI requirement on parallel hybrid electric turboprop regional aircraft optimization

Quillet

Boulanger²,

Rancourt³

et al. 2022

AEAT

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Purpose Parallel hybrid electric (HE) propulsion retrofit is a promising alternative to reduce fuel burn of aircraft operating on short regional flights. However, if the batteries are depleted at the end of the mission, the hybrid powertrain designs with downsized gas turbines (GTs) and additional electric motors might not meet the one-engine inoperative (OEI) missed approach climb performance required by the certification. Alternatively, hybrid designs using the original full-size GT can perform one engine climb without electric assistance. This paper aims to evaluate the impact of overshoot climb requirements on powertrain design and performance comparing the two design approaches. Design/methodology/approach An aircraft-level parametric mission analysis model is used to evaluate aircraft performance combined with an optimization framework including multiple constraints. An indirect approach using metamodels is used to optimize powertrain sizing and operation strategy. Findings Considering OEI climb requirements, no benefits were found using a design with downsized GTs. Equivalent fuel burns were found for hybrid designs that keep the original size GTs, but do not require electric energy for the OEI overshoot at the end of the mission. Then, it is recommended to size the GT to maintain the emergency climb capabilities with no electric assistance to ensure power availability regardless of remaining battery energy. Originality/value This work introduces a new perspective on parallel HE sizing with consideration for the dependency of power capability at aircraft level on the electric energy availability in case of critical mission scenarios such as overshoot climb at the end of the mission.

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Section: Mission Analysis Frameworkmentioning

confidence: 99%

Impact of OEI requirement on parallel hybrid electric turboprop regional aircraft optimization

Quillet

Boulanger²,

Rancourt³

et al. 2022

AEAT

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“…This section shows an example of a PMSM design problem for an aircraft application [6]. The main challenge is to maximize motor power density and efficiency.…”

Section: Design Examplementioning

confidence: 99%

“…The search for the best configurations remains an important issue to identify the most efficient solutions. It must be based on optimization methods with multiple objectives and dimensioning tools to assess the behaviour of the entire propulsion system during a typical mission [4][5][6]. In this case, it is necessary to take into account various physical phenomena and to make compromises on the granularity of certain models to carry out the design analyses in a reasonable time.…”

Section: Introductionmentioning

confidence: 99%

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Comparison between Space Mapping and Direct FEA Optimizations for the Design of Halbach Array PM Motor

et al. 2022

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Effective methods for the design of high-performance electrical machines must use optimization techniques and precise and fast physical models. Convergence, precision and speed of execution are important issues, in addition to the ability to explore the entire domain of solutions. The finite element method (FEM) presents a high accuracy in the results but with high computational costs. Analytical models, on the other hand, solve the problem quickly but compromise the accuracy of the results. This work shows a comparison between an optimization made with an analytical electromagnetic model and a direct optimization with finite element field calculation for the optimal design of a Halbach array permanent magnet synchronous motor (PMSM). In the case of the analytical model, it is necessary to use an iterative method of correcting the model to obtain a valid solution. This method is known as Space Mapping (SM) and the analytical model can be improved with a reduced number of iterations with the FEM. The results show a rapid convergence towards an optimal solution for the SM, with more than 78% reduction in computational cost compared to a Direct FEM optimization. Both solutions have only a difference of 3% on the power density, which indicates that FEM does not improve the results obtained by SM. This represents a great advantage that allows for the consideration of a large amount of designs to analyze the domain of solutions in more detail. This study also shows that SM is a powerful method to optimize the power density or torque density of electrical machines.

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“…However, due to the energy density of state of the art batteries, purely battery electric power trains are limited to smaller and low range applications, such as two-seater airplanes, unmanned aerial vehicles or urban air vehicles and no near-time option for larger passenger capacity or long range flight [3]. Parallel hybrids of gas turbines and batteries have been identified as a potentially suitable alternative for the regional segment, enabling decreased fuel consumption and therefore a reduction of CO 2 emissions [4]. If this gas turbine is operated with sustainable aviation fuel (SAF), global CO 2 emissions can be theoretically reduced to zero.…”

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confidence: 99%

Modelling of a battery supported fuel cell electric power train topology for a regional aircraft

Staggat

Ludowicy

Bahrs

et al. 2023

J. Phys.: Conf. Ser.

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Electrification of aircraft propulsion may offer a way towards carbon dioxide (CO2) neutral air travel. Here, the electric aircraft demonstrators already flying mostly rely on the use of batteries as energy source. While battery electric concepts may be suitable solutions for short range applications, such as urban air vehicles, the energy density of state of the art batteries is not yet sufficient to power regional aircraft with a typical range of 1000 nautical miles and 70 passengers. One possible topology option of a propulsion concept suitable for a regional aircraft is a hybrid composed of a fuel cell system (FCS) and a battery. On the one hand, this concept uses hydrogen (H2) as the primary energy carrier, resulting in a significant reduction of the required battery stack mass in comparison to a battery only aircraft. On the other hand, a battery support of flight phases with high power demand, such as take-off or climb, allows a smaller dimensioning of the fuel cell system and the corresponding thermal management system (TMS) and therefore additional overall system mass benefits in comparison to a fuel cell only aircraft. The present paper analyses the weight reduction potential of a battery stack supported fuel cell system electric power train architecture for a typical regional aircraft with regard to the hybridization factor (HF) and battery specific energy (BSE). The modelling includes the sizing of the fuel cell system and the battery stack, other mechanical and electric components, such as gearboxes, electric motors and power electronics and the corresponding TMS. The according electrified aircraft is resized, keeping wing loading and power-to-weight ratio constant. The best combination of HF and BSE yielding the lowest MTOM with 27 100 kg is still about 19.9 % heavier than the conventionally powered reference aircraft with 22 800 kg. The study shows that future aircraft of similar weight and hence size require very advanced battery technology with regard to the BSE compared to available state of the art solutions.

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Parallel Hybrid-Electric Powertrain Sizing on Regional Turboprop Aircraft with Consideration for Certification Performance Requirements

Cited by 11 publications

References 7 publications

Impact of OEI requirement on parallel hybrid electric turboprop regional aircraft optimization

Impact of OEI requirement on parallel hybrid electric turboprop regional aircraft optimization

Comparison between Space Mapping and Direct FEA Optimizations for the Design of Halbach Array PM Motor

Modelling of a battery supported fuel cell electric power train topology for a regional aircraft

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