Fuel burn evaluation of a turbo-electric propulsive fuselage aircraft

Giannakakis, Panagiotis; Tantot, Nicolas; Frantz, Caroline; Belleville, Mathieu

doi:10.2514/6.2019-4181

Cited by 11 publications

(19 citation statements)

References 11 publications

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“…More specifically, Equation 7is introduced in the first part of Equation (8), in order to express the total dissipation as a function of the profile dissipation and λ. Introducing Equation (6) into the left part of Equation (8) and assuming that the wave and vortex dissipation remain unchanged between the BLI and conventional configurations, Equation (10) is obtained.…”

Section: Power Saving Estimation Methodsmentioning

confidence: 99%

“…The method described in the previous sections has been compared against the detailed preliminary design study published by the authors (6) , in order to ascertain that it can produce reliable results for the design space exploration. The benchmark study included a full multipoint design and performance evaluation of the propulsion system, a CFD calculation of the flow ingested by the BLI fan and a mechanical design, integration and weight estimation of the propulsive system (6) . As such, it represents the most accurate estimation possible at a conceptual design stage and it can serve as a reliable benchmark for the validation of the analytical method presented herein.…”

Section: Methods Validation and Limitationsmentioning

confidence: 99%

“…The comparison takes place on the cruise point given in Table 1 together with the rest of the assumptions. According to the results of Giannakakis et al (6) , the BLI fan produces 33% Table 2 Validation against the detailed study of Giannakakis et al (6) Predicted Reference ( of total thrust at cruise (30% at top-of-climb) and this is the value taken for the q parameter in Table 1. The turbofan BPR and average jet velocity V jet,TF correspond to an Ultra High Bypass Ratio (UHBR) architecture.…”

Section: Methods Validation and Limitationsmentioning

confidence: 99%

“…The exchange rates used for the calculation correspond to a typical short-to medium-range aircraft and are the same as the ones used by Giannakakis et al (6) . The results of the verification are shown in Table 2, where one can readily see that the TSFC reduction predicted by the analytical method is sufficiently close to the higher fidelity estimation of Giannakakis et al (6) . Furthermore, the reduction in the underwing engines fan diameter is also predicted fairly accurately, leading to a good estimation of the propulsive system mass change.…”

Section: Methods Validation and Limitationsmentioning

confidence: 99%

“…A few interesting methods, which would be compatible with the preliminary design approach developed in this work, are proposed by Guha et al (16) and Greitzer et al (17) , and can be calibrated to better represent the designer's target. For this work, the mass of the underwing turbofans and of the BLI fan have been calculated as linear functions (M = a • D fan + b) of their respective fan diameters, based on the detailed mechanical integration studies by Giannakakis et al (6) . With respect to the underwing turbofans, the correlation approximately gives the variation in the weight of the low-pressure components and nacelle, as the core components weight stays fairly constant.…”

Section: • • • (41)mentioning

confidence: 99%

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Turbo-electric propulsive fuselage aircraft BLI benefits: A design space exploration using an analytical method

2020

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Turbo-electric propulsive fuselage aircraft featuring Boundary-Layer Ingestion (BLI) are considered promising candidates to achieve the emissions reduction targets set for aviation. This paper presents an analytical method capable of estimating the BLI benefit at aircraft level, enabling a quick exploration of the propulsive fuselage design space. The design space exploration showed that the assumptions regarding the underwing turbofans and BLI fan mass estimation can have an important impact on the final fuel burn estimation. The same applies to the total efficiency assumed for the electric transmission, the range of the aircraft mission, and the propulsive efficiency of the engines used as benchmark. The regional jet and short- to medium-range aircraft classes seem to be the most promising as the ingested drag and power saving are among the largest, with long-range aircraft being just behind. The future introduction of advanced technologies, which target the reduction of vortex and wave dissipation at aircraft level, could increase the potential benefit of propulsive fuselage BLI. On the other hand, the potential benefit would be decreased if more efficient and lighter ultra high bypass ratio engines were used as benchmark.

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Section: Power Saving Estimation Methodsmentioning

confidence: 99%

Section: Methods Validation and Limitationsmentioning

confidence: 99%

Section: Methods Validation and Limitationsmentioning

confidence: 99%

Section: Methods Validation and Limitationsmentioning

confidence: 99%

Section: • • • (41)mentioning

confidence: 99%

See 3 more Smart Citations

Turbo-electric propulsive fuselage aircraft BLI benefits: A design space exploration using an analytical method

2020

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Numerical investigation of the effects of fuselage upsweep in a propulsive fuselage concept

2021

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In recent years, aircraft concepts employing wake-filling devices to reduce mission fuel burn have gained increasing attention. The study presented here aims at a detailed physical understanding of the effects of integrating a propulsive fuselage device on a commercial aircraft. Compared to an isolated, axisymmetric fuselage-propulsor configuration, a propulsive fuselage device experiences an increased circumferential inlet distortion due to three-dimensional geometric features of the aircraft. This study uses three-dimensional CFD simulations to investigate the effect of fuselage upsweep on the aero-propulsive performance of an aircraft configuration featuring a boundary layer ingestion device. It is shown that fuselage upsweep has a negative impact on the performance of a propulsive fuselage device as compared to an axisymmetric configuration. Increasing the upsweep angle by $$\Delta \alpha _{{{\text{SW}},{\text{PFC}}}} = 3.5^\circ$$ Δ α SW , PFC = 3 . 5 ∘ leads to an increase in required fuselage fan shaft power by 19%. Furthermore, it is demonstrated that the negative effects of fuselage upsweep on the propulsor’s performance can be effectively mitigated by a circumferential variation in the propulsor nacelle thickness.

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Fundamental considerations in the design and performance assessment of propulsive fuselage aircraft concepts

Moirou,

Mutangara,

Sanders

2024

Aeronaut. j.

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Propulsive fuselage aircraft complement the two under-wing turbofans of current aircraft with an embedded propulsion system within the airframe to ingest the energy-rich fuselage boundary layer. The key design features of this embedding are examined and related to an aero-propulsive performance assessment undertaken in the absolute reference frame which is believed to best evaluate these effects with intuitive physics-based interpretations. First, this study completes previous investigations on the potential for energy recovery for different fuselage slenderness ratios to characterise the aerodynamics sensitivity to morphed fuselage-tail design changes and potential performance before integrating fully circumferential propulsors. Its installation design space is then explored with macro design parameters (position, size and operating conditions) where an optimum suggests up to 11% fuel savings during cruise and up to 16% when introducing compact nacelles and re-scaling of the under-wing turbofans. Overall, this work provides valuable insights for designers and aerodynamicists on the potential performance of their concepts to meet the environmental targets of future aircraft.

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Fuel burn evaluation of a turbo-electric propulsive fuselage aircraft

Cited by 11 publications

References 11 publications

Turbo-electric propulsive fuselage aircraft BLI benefits: A design space exploration using an analytical method

Turbo-electric propulsive fuselage aircraft BLI benefits: A design space exploration using an analytical method

Numerical investigation of the effects of fuselage upsweep in a propulsive fuselage concept

Fundamental considerations in the design and performance assessment of propulsive fuselage aircraft concepts

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