Hybridization and Mission Analysis of a regional turboprop

Orefice, Francesco; Nicolosi, Fabrizio; Corcione, Salvatore; Vecchia, Pierluigi Della

doi:10.2514/6.2021-2421

Cited by 6 publications

(9 citation statements)

References 10 publications

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“…Various concepts for novel propulsion systems in regional applications have been explored in literature [3][4][5]. Orefice et al [6] modeled an 8-propeller hybrid-electric aircraft with batteries and gas turbine engines, based on ATR42 mission requirements and geometric characteristics. They considered two propulsive lines, a primary one, consisting of the gas turbines and main propellers that can be assisted by an electic power on-take to the propeller shaft, and a second propulsive line consisting of an electric power train sourced by batteries and leading to the secondary propellers.…”

Section: B State Of the Art 1 Novel Propulsion Systems For Regional A...mentioning

confidence: 99%

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Pontika

Zaghari

Zhou

et al. 2023

AIAA SCITECH 2023 Forum

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This paper presents the development and application of an integrated, higher-fidelity framework developed within CHARM (the Cranfield Hybrid electric Aircraft Model) for the design, performance analysis and overall evaluation of novel electrified propulsion systems. The developed framework is used to model and analyze the performance characteristics of a Fuel Cell (FC) regional aircraft system in comparison with a conventional regional aircraft and a hydrogen gas turbine regional aircraft retrofit. The FC propulsion system and the hydrogen gas turbine are retrofitted to the same conventional aircraft platform. Physics-based aircraft performance calculations, propeller maps, gas turbine component maps, off-design cycle analysis, electric component maps, calculations for the electric power management and distribution, and a Proton-Exchange Membrane FC (PEMFC) configuration sized to cover the power requirements of a regional aircraft, are integrated within this framework to capture the performance and interaction of components, sub-systems and aircraft during any flight mission and conditions. The aircraft performance, the propulsion system performance characteristics and the emissions of the three technologies are calculated and discussed to understand the challenges and opportunities of using hydrogen-electric propulsion (FC). The effect of capturing the variable mission parameters and flight phases on the performance of the electric power system and FC is presented and compared against a lower fidelity modeling approach for the electric powertrain. The sensitivity of the FC propulsion system and its attributes to varying mission requirements (island-hopping, range, cruise altitude, ambient conditions), as well as the change in the consumed fuel, are demonstrated. This framework can be used to inform the decision-making for the design of electric components and thermal management systems (TMS), and the importance of capturing the trade-off between mass, efficiency and operational constraints in the design process is highlighted. Also, the off-design performance of the electric power system designs and FC is modeled to decide if the design is within acceptable limits under various conditions, and capture the effect of mission requirements and flight conditions on the energy consumption of the overall aircraft system. Finally, a parametric analysis addresses the effect of power density improvement with future technology on the energy per passenger and feasibility of the FC regional aircraft.

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Section: B State Of the Art 1 Novel Propulsion Systems For Regional A...mentioning

confidence: 99%

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Pontika

Zaghari

Zhou

et al. 2023

AIAA SCITECH 2023 Forum

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“…At the aircraft level, the main objective of the project was to reduce typical mission fuel burn, similar to [7]. Pre-studies were conducted to refine the design space accordingly.…”

Section: Hybrid-electric Powertrain System Behaviormentioning

confidence: 99%

“…Thus, HEP is deemed most suited for market segments with short design and operational ranges, such as regional air transportation (e.g., [2,3,5,6]). Following the successful flight of early CS-23 prototypes, regional turboprop application is a likely first step to a global electrification of commercial aviation through CS-25-type aircraft [7].…”

Section: Introductionmentioning

confidence: 99%

“…For design mission ranges typical to regional aircraft, HEP is, thus, a promising technology. Several studies are focusing on investigating the potential of regional HEP aircraft configurations, such as the projects PEGASUS (Parallel Electric-Gas Architecture with Synergistic Utilization Scheme) [8], IRON (Innovative turbopROp configuratioN) [7], HECARRUS (Hybrid ElectriC smAll commuteR aiRcraft conceptUal deSign) [9], FutPrInt50 (Future Propulsion and Integration: towards a hybrid-electric 50-seat regional aircraft) [10] and the studies presented in [6,[11][12][13][14][15]. Most investigated configurations are based on the ATR (Avions de Transport Régional) 42 or ATR 72 aircraft, employing different combinations of technologies in addition to a hybrid-electric power train.…”

Section: Introductionmentioning

confidence: 99%

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Study of a Regional Turboprop Aircraft with Electrically Assisted Turboshaft

et al. 2023

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Hybrid-Electric Propulsion (HEP) could be part of the solution to decrease emissions associated with regional commercial aviation. This study presents results for the aircraft level fuel reduction potential of a regional turboprop concept with an HEP architecture and Entry-Into-Service (EIS) in 2035+. The configuration specifically tackles the elaborated challenges of introducing an additional electrical energy source to the configuration by employing a twofold electrical assistance to a turboshaft engine in combination with an innovative thermal management concept. Relevant components and disciplines were modeled and incorporated into an integrated aircraft design environment. The behavior and interaction of the HEP architecture with the aircraft was thoroughly investigated. A best-performing configuration was derived and compared with a conventional reference configuration following a State-of-the-Art (SoA) reference aircraft approach. For a typical mission with 200 nmi range, a block fuel reduction of 9.6% was found. However, the assumed battery performance characteristics limited the reduction potential and led to a fuel burn increase for the 600 nmi design mission. Furthermore, sourcing the non-propulsive subsystems directly from the on-board battery was detrimental. The innovative Thermal Management System (TMS) located in the propeller slipstream showed a synergistic effect with the investigated configuration.

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“…As a result, hybrid propulsion is considered most suitable for short range market segments such as regional aviation [2,3,4,5,6]. Following the successful flight of early CS-23 prototypes, regional turboprop applications are a likely first step towards the global electrification of commercial aviation [7].…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design and Control Schedule Optimization for Parallel Hybrid Propulsion System of Regional Turboprop Aircraft

Mikhailov,

Vasilieva,

Mikhailova

et al. 2023

E3S Web Conf.

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Current environmental policies for the aviation industry motivate the use of cleaner propulsion systems to reduce its CO2 and noise footprint in the coming years. In this context, hybrid propulsion systems have emerged as a potential solution as they have demonstrated a good trade-off between performance and low pollutant emissions. In the present work, the conceptual design and control schedule optimisation of a parallel hybrid propulsion system for the De Havilland Dash 8 regional turboprop aircraft is carried out. A parametric study of the turboprop engine with different degrees of hybridisation at design point and off-design performance analysis of the parallel hybrid propulsion system with different control schedules for an aircraft typical mission has been carried out. Overall aircraft performance parameters are used to evaluate hybrid propulsion systems with different degrees of hybridisation and control schedules. From the results, it was found that a control schedule with 10-15% hybridisation during the cruise phase is the most promising when considering the aircraft mission blocked fuel and fuel efficiency.

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Hybridization and Mission Analysis of a regional turboprop

Cited by 6 publications

References 10 publications

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Study of a Regional Turboprop Aircraft with Electrically Assisted Turboshaft

Conceptual Design and Control Schedule Optimization for Parallel Hybrid Propulsion System of Regional Turboprop Aircraft

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