Mission Analysis and Emissions for Conventional and Hybrid-Electric Commercial Transport Aircraft

Wroblewski, Gabrielle E.; Ansell, Phillip J.

doi:10.2514/1.c035070

Cited by 41 publications

(28 citation statements)

References 15 publications

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“…The results indicate that the two HEP concepts present no benefit with respect to a conventional powertrain. This is in line with the findings of previous studies, which show that either more optimistic e bat values [9,14,21,45] or reduced ranges [8,[16][17][18]24] are required for the HEP concepts to be competitive. Nonetheless, the results demonstrate the versatility of the method and provide valuable insight into possible areas of improvement.…”

Section: Conventionalsupporting

confidence: 92%

“…Despite the large amount of ongoing research related to hybrid-electric propulsion, little information is available regarding the clean-sheet design process of HEDP aircraft. In many cases, design studies analyze the hybrid-electric powertrain in detail starting from a predefined aircraft configuration [14][15][16], often maintaining the take-off weight constant [17][18][19]. Other studies have formulated more generalized conceptual sizing methods for HEP aircraft [19][20][21][22][23][24], but do not integrate the aero-propulsive interaction effects in the process.…”

Section: Introductionmentioning

confidence: 99%

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A Preliminary Sizing Method for Hybrid-Electric Aircraft Including Aero-Propulsive Interaction Effects

Vries

Brown

Vos

2018

2018 Aviation Technology, Integration, and Operations Conference

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The potential benefits of hybrid-electric propulsion (HEP) have led to an increased interest in this topic over the past decade. One promising advantage of HEP is the distribution of power along the airframe, which enables synergistic configurations with improved aerodynamic and propulsive efficiency. The purpose of this paper is to present a generic sizing method suitable for the first stages of the design process of hybrid-electric aircraft, taking into account the powertrain architecture and associated propulsion-airframe integration effects. To this end, the performance equations are modified to account for aero-propulsive interaction. A powerloading constraint-diagram is used for each component in the powertrain to provide a visual representation of the design space. The results of the power-loading diagrams are used in a HEP-compatible mission analysis and weight estimation to compute the wing area, powerplant size, and takeoff weight. The resulting method is applicable to a wide range of electric and hybrid-electric aircraft configurations and can be used to estimate the optimal power-control profiles. For demonstration purposes, the method is applied a HEP concept featuring leadingedge distributed-propulsion (DP). Three powertrain architectures are compared, showing how the aero-propulsive effects are inlcuded in the model. The results confirm the method is sensitive to top-level HEP and DP design parameters, and indicate an increase in wing loading and power loading enabled by DP.

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Section: Conventionalsupporting

confidence: 92%

Section: Introductionmentioning

confidence: 99%

A Preliminary Sizing Method for Hybrid-Electric Aircraft Including Aero-Propulsive Interaction Effects

Vries

Brown

Vos

2018

2018 Aviation Technology, Integration, and Operations Conference

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“…This last benefit is commonly referred to as distributed propulsion (DP) [5], which enables advanced propulsion-system layouts with increased aero-propulsive efficiency [6,7], reduced noise emissions through shielding [8], or enhanced high-lift [6,9] and control [10] capabilities. However, due to the battery weight penalty associated to many hybrid-electric powertrains, most design studies evaluate reduced ranges [2,3,11,12] or require battery technology levels which are inconceivable in the near future [13][14][15] in order to make these aircraft concepts viable.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Sizing of a Hybrid-Electric Passenger Aircraft Featuring Over-the-Wing Distributed-Propulsion

Vries

Hoogreef

Vos

2019

AIAA Scitech 2019 Forum

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This study compares a hybrid-electric aircraft featuring a propulsive empennage and overthe-wing, distributed-propulsion to a conventional regional turboprop. The impact of multiple design parameters, mission requirements, and technology assumptions on maximum takeoff mass and payload-range energy efficiency is evaluated, in order to illustrate the sensitivities of the design. A preliminary sizing method that incorporates aero-propulsive interaction effects is used to obtain rapid estimations. Results show that, for the baseline mission, the hybridelectric variant is 2.5% heavier and consumes 2.5% more energy than the reference aircraft. In this process, several key design guidelines and challenges for distributed-propulsion aircraft are identified. Firstly, when comparing a hybrid-electric configuration to a conventional one, each aircraft must be sized at its optimum cruise altitude for the same payload and range requirements. Secondly, the hypothetical advantages of distributed propulsion described in literature do not easily lead to a benefit at aircraft level, if the aero-propulsive interaction effects and associated dependencies are incorporated in the design process. Thirdly, the power-control parameters affect practically all characteristics of the aircraft, and the optimal control strategy is highly dependent on the aero-propulsive interaction. The results suggest that the proposed configuration can constitute a low-noise alternative for the regional transport market if the performance of the over-the-wing distributed-propulsion system is optimized.

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“…Sizing of the electrical power system is crucial for the realistic estimation of environmental and economic deltas for new concepts (Wroblewski et al, 2019). In this work, the first-order effects of electrification on aircraft weight are captured via utilizing technology factors for the individual components (Pornet et al, 2014;Bradley et al, 2015;Gnadt et al, 2019;Zhao et al, 2019a).…”

Section: Impact Of Electrical Power System Technologymentioning

confidence: 99%

Enabling the Potential of Hybrid Electric Propulsion Through Lean-Burn-Combustion Turbofans

Vouros¹,

Kavvalos²,

Sahoo³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Hybrid-electric propulsion has emerged as a promising technology to mitigate the adverse environmental impact of civil aviation. Boosting conventional gas turbines with electric power improves mission performance and operability. In this work the impact of electrification on pollutant emissions and direct operating cost of geared turbofan configurations is evaluated for an 150-passenger aircraft. A baseline two-and-a-half-shaft geared turbofan, representative of year 2035 entry-into-service technology, is employed. Parallel hybridization is implemented through coupling a battery-powered electric motor to the engine low-speed shaft. A multidisciplinary design space exploration framework is employed comprising modelling methods for multi-point engine design, aircraft sizing, performance and pollutant emissions, mission and economic analysis. A probabilistic approach is developed considering uncertainties in the evaluation of direct operating cost. Sensitivities to electrical power system technology levels, as well as fuel price and emissions taxation are quantified at different time-frames. The benefits of lean direct injection are explored along a realistic mission scenario, demonstrating 32% NOx savings compared to traditional rich-burn, quick-mix, lean-burn technologies. The impact of electrification on the enhancement of lean direct injection benefits is investigated. For hybrid-electric powerplants, the takeoff to cruise turbine entry temperature ratio is 2.5% lower than the baseline, extending the corresponding NOx reductions to the level of 46%. This work sheds light on the environmental and economic potential and limitations of a hybrid-electric propulsion concept towards a greener and sustainable civil aviation.

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Mission Analysis and Emissions for Conventional and Hybrid-Electric Commercial Transport Aircraft

Cited by 41 publications

References 15 publications

A Preliminary Sizing Method for Hybrid-Electric Aircraft Including Aero-Propulsive Interaction Effects

A Preliminary Sizing Method for Hybrid-Electric Aircraft Including Aero-Propulsive Interaction Effects

Preliminary Sizing of a Hybrid-Electric Passenger Aircraft Featuring Over-the-Wing Distributed-Propulsion

Enabling the Potential of Hybrid Electric Propulsion Through Lean-Burn-Combustion Turbofans

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