Maximisation of installed net resulting force through multi-level optimisation of an ultra-high bypass ratio engine nacelle

Magrini, Andrea; Buosi, Denis; Benini, Ernesto

doi:10.1016/j.ast.2021.107169

Cited by 17 publications

(2 citation statements)

References 29 publications

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“…A more advanced analysis is proposed in [73], in which CFD simulations with steady RANS solvers are used to thoroughly investigate the effects of UHBR turbofan installation. Starting from the results previously obtained by the same authors in [74], numerical simulations are used to assess and characterise the complex aerodynamic flow around the nacelle of a UHBR turbofan (with a value of BPR > 14) mounted underwing to the longrange NASA common research model [75] and to evaluate the impact of engine positioning on the mutual interaction with the wing in cruise condition (where the Mach number is 0.85 and the aircraft altitude is 10,667 m). The work accurately demonstrates that the proper engine positioning with respect to the wing is of primary relevance to interference effects and aerodynamic performance.…”

Section: Assesment Of Uhbr Installation Effectsmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies.

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Section: Assesment Of Uhbr Installation Effectsmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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“…Grid resolution for the Wing Body Nacelle Pylon (WBNP) configuration of the NASA CRM was first specified in accordance with workshop guidelines [25,26] and assessed for the current geometry with a powered-on nacelle. A detailed description of the numerical model validation is reported in [16,27]. Here, a summary of the mesh sensitivity analysis at the ADP is reported for completeness in Table 1.…”

Section: Cfd Modellingmentioning

confidence: 99%

CFD-Based Analysis of Installed Fuel Consumption and Aerodynamics of Transonic Transport Aircraft during Cruise Flight

et al. 2023

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Gas turbine fuel burn for an aircraft engine can be obtained analytically using thermodynamic cycle analysis. For large-diameter ultra-high bypass ratio turbofans, the impact of nacelle drag and propulsion system integration must be accounted for in order to obtain realistic estimates of the installed specific fuel consumption. However, simplified models cannot fully represent the complexity of installation effects. In this paper, we present a method that combines thermodynamic cycle analysis with detailed Computational Fluid Dynamics (CFD) modelling of the installation aerodynamics to obtain the fuel consumption at a given mission point. The flow field and propulsive forces arising in a transport aircraft powered by an ultra-high bypass ratio turbofan at cruise are first examined to characterise the operating conditions and measure the sensitivity to variations of the incidence at transonic flight. The proposed methodology, in which dynamic balance of the vehicle is achieved at each integration point, is then applied along a cruise segment to calculate the cumulative fuel burn and the change in the specific fuel consumption.

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Damage morphology and force-deflection curves for impact loading of thick multilayer organic protective coating systems

Momber,

Irmer,

Kelm

et al. 2023

J Coat Technol Res

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Maximisation of installed net resulting force through multi-level optimisation of an ultra-high bypass ratio engine nacelle

Cited by 17 publications

References 29 publications

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

CFD-Based Analysis of Installed Fuel Consumption and Aerodynamics of Transonic Transport Aircraft during Cruise Flight

Damage morphology and force-deflection curves for impact loading of thick multilayer organic protective coating systems

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