Multi-Point Design of Parallel Hybrid Aero Engines

Sielemann, Michael; Coïc, Clément; Zhao, Xin; Diamantidou, Dimitra Eirini; Kyprianidis, Konstantinos

doi:10.2514/6.2020-3556

Cited by 4 publications

(3 citation statements)

References 21 publications

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“…Several modules for the modeling of electric components were developed in NPSS (Perullo et al, 2014) and PROOSIS (Athanasakos et al, 2020). The same applies to a number of multi domain simulation programs (Sielemann et al, 2020;Kang et al, 2021). Commonly, it is up to the user to integrate different modules into the propulsion system in a sensible way.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Pohl

Kohler

Kellermann

et al. 2022

J. Glob. Power Propuls. Soc.

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This paper presents a novel tool for the modeling of partial turboelectric propulsion systems together with a corresponding case study for a commercial single-aisle aircraft. In order to reduce the environmental impact of air traffic, radically new aircraft and propulsion concepts with a high market penetration are needed. Partial turboelectric propulsion systems seem to offer a promising option to achieve this. For the development of these propulsion systems, a preliminary design tool with a homogeneous and sufficiently high fidelity, both for turbomachinery and electric components, is needed. To address this, the authors of this publication have developed a tool based on the GasTurb software. The models developed, in particular for the electric components which together form the electric powertrain, are described here. In the case study, which demonstrates the coupling of the developed tool with an aircraft design environment, a conventional turboprop baseline aircraft is compared to a derived aircraft which features a partial turboelectric propulsion system with wingtip propellers. The latter are intended to reduce the induced drag, enabling a reduction of the aircraft's total shaft power demand compared to the conventional baseline aircraft. The comparison between the partial turboelectric aircraft and the baseline aircraft indicates that fuel reduction increases with power split. However, primarily increasing electric powertrain masses and a stagnating drag reduction result in lower additional fuel reductions for higher power splits. Despite these conclusions, the predicted induced drag reductions need further refinement as they were found to be optimistic. In summary, this publication presents a methodology and a set of physics-based component models for the preliminary design of partial turboelectric propulsion systems, so that the electric components can be investigated and optimized at the same high level of detail as the gas turbine.

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Section: Introductionmentioning

confidence: 99%

Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems

Pohl

Kohler

Kellermann

et al. 2022

J. Glob. Power Propuls. Soc.

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“…The study also concluded that including the ram-air drag penalty for the electric powertrain cooling system outweighs this benefit. The studies from Sahoo et al [19] and Sielemann et al [20] presented different approaches to cycle design with limited information on its impact at the aircraft mission level. Roumeliotis et al [21] presented the impact of power on-takes on LPC, fan, and HPC operability.…”

mentioning

confidence: 99%

“…There has been work done on parallel hybrid engine cycle design for a fixed power management strategy as described [18], [19], and [20]. In Lents' study [18], no change is made to the design point FPR and OPR with increasing BPR, and neither the mass flows are conserved at top of climb.…”

mentioning

confidence: 99%

Design Methodology and Mission Assessment of Parallel Hybrid Electric Propulsion Systems

Ghelani

Roumeliotis

Saias

et al. 2022

Journal of Engineering for Gas Turbines and Power

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An integrated engine cycle design methodology and mission assessment for parallel hybrid electric propulsion architectures are presented in this paper. The aircraft case study considered is inspired by Fokker 100, boosted by an electric motor on the low-pressure shaft of the gas turbine. The fuel burn benefits arising from boosting the low-pressure shaft are discussed for two different baseline engine technologies. A three-point engine cycle design method is developed to redesign the engine cycle according to the degree of hybridization. The integrated cycle design and power management optimization method is employed to identify potential fuel burn benefits from hybridization for multiple mission ranges. The sensitivity of these mission results has also been analyzed for different assumptions on the electric powertrain. With 1 MW motor power and a battery pack of 2307 kg, a 3% fuel burn benefit can be obtained by retrofitting the gas turbine for 400 nm range. Optimizing the power management strategy improves this fuel burn benefit by 0.2-0.3%. Redesigning the gas turbine and optimizing the power management strategy, provides a 4.2% fuel benefit on 400 nm. The results suggest that a high hybridization by power, low hybridization by energy, and ranges below 700 nm are the only cases where the redesigned hybrid electric aircraft has benefits in fuel burn and energy consumption relative to the baseline aircraft. Finally, it is found that the percentage of fuel burn benefits from the hybrid electric configuration increases with the improvement in engine technology.

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