Design and Optimization of a Nacelle for a UHBR Turbofan engine using a Class Shape Transformation based parameterization

Benjamin, Legin; Heykena, Constance; Friedrichs, Jens; Marquez, Carlos

doi:10.33737/gpps20-tc-160

Cited by 5 publications

(5 citation statements)

References 9 publications

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“…These secondary effects, therefore, could theoretically (partially or totally) undermine the benefit obtainable in terms of specific fuel consumption by increasing the BPR, affecting the overall performance of the whole aircraft (i.e., block fuel consumption). For this reason, in order to effectively foster the development and actual implementation of the UHBR turbofan, in addition to evaluating technological implementations in advanced materials and more efficient components [52], in nacelle design [53,54] and its shape optimization [55,56], it is also crucial to take into account the effects of the turbofan installation [57], together with the mission performance of the complete aircraft [58].…”

Section: Advanced Turbofan 21 Overview Of Ultra-high Bypass Ratio Tur...mentioning

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: Advanced Turbofan 21 Overview Of Ultra-high Bypass Ratio Tur...mentioning

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 aircraft geometry and flight conditions are based on design studies carried out for the next design iteration of the BWB, as described in [7]. Nacelles designed following the methodology described in [8] were integrated onto the top rear of the aircraft fuselage. The DLR TAU-Code [9], a finite-volume-based Navier-Stokes solver is used for the CFD simulation, while the mesh is generated with CENTAUR.…”

Section: Derivation Of Distortion Patternmentioning

confidence: 99%

Aerostructural Investigation of Shape Adaptive Rotor Blading for the Reduction of Bli Induced Losses in the Distorted Flow Regimes of a Transonic Fan Rotor

Seidler,

Voigt,

Montano Rejas

et al. 2023

10th ECCOMAS Thematic Conference on Smart Structures and Materials

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Within the Cluster of Excellence for Sustainable and Energy-Efficient Aviation SE 2 A, a blended wing body aircraft is investigated to improve efficiency and carbon emissions of future air transport. By embedding the aircraft engines on the top rear fuselage, parts of the aircraft's wing boundary layer are ingested, which has the potential to further improve the engine's propulsion efficiency. Through the ingestion of low momentum fluid however, inflow distortion is induced and the fan rotor operates under increased flow incidence in the distorted flow regimes. To reduce the thereby arising efficiency and pressure ratio penalties in the aircraft engine, alternative design strategies for the fan stage are required. Within this investigation, an active shape morphing mechanism is introduced, which allows to temporarily adjust the fan blading when the fan rotor is exposed to distorted inflow conditions. By integrating piezoceramic actuators into the rotor blading, the blade staggering and turning can be adjusted with the goal to reduce flow incidence and deviation in the distorted flow regimes. For this investigation the NASA rotor 67 is chosen as a reference test case and its performance under boundary layer ingestion (BLI) conditions is evaluated. For the shape morphing assessment, FEA morphing simulations are tightly coupled with a geometry re-engineering methodology and stationary CFD simulations of the actuated fan rotor geometries under distorted inflow. For the chosen test case, the achievable deformations are however too small to compensate for the strong distortion effects of a blended wing body's boundary layer. Therefore, the blade reference design needs to be adapted in order to increase the achievable deformations. This includes the investigation of typical compressor design parameter variations, such as blade hub-to-tip ratio, chord length as well as lean and sweep and their impact on the deformability of a shape-adaptive fan stage.

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“…For consistency of use within the AVACON project, the nomenclature is not continuous at this point. In all cases, a UHBR engine with a bypass ratio of 16.3 is used, with geometry provided by a consortium partner [7]. While a previous paper by the author [8] described the Concept 2 configuration in detail, the present paper focuses on the Concept 3 configuration.…”

Section: Figure 1 Avacon Engine Mounting Conceptsmentioning

confidence: 99%

Integration of Wing-Mounted Over-Wing Engines on a Mid-Range Aircraft

Wegener

Lange

2022

AIAA SCITECH 2022 Forum

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Ultra-High Bypass Ratio (UHBR) engines are an important technology for improving the efficiency of future aircraft. However, their large diameter poses a major challenge for their use in conventional under-wing mounted engine configurations due to limited space. A configuration with engines mounted above the wing is not subject to these limitations and therefore offers the potential for improvements in overall aircraft efficiency and performance. Another advantage of this configuration is the acoustic shielding effect of the fan noise toward the ground by the wing. Configurations with this type of engine layout were investigated as part of the German LuFo V project AVACON (AdVanced Aircraft CONcepts). This paper describes the investigated variant of engine integration via a vertical pylon between nacelle lower side and main spar of the wing. To investigate the complex aerodynamic interactions between the engine and the wing, RANS CFD simulations were performed using the DLR code TAU. By optimizing twist and upper surface shape, the wing geometry was adapted to the flow conditions resulting from the engine integration to reduce detrimental aerodynamic installation effects. In general, the influence of the geometric shape of the wing and engine as well as their relative geometric position on the overall drag is more pronounced in such a configuration than in a underwing engine design. The use of advanced optimization methods is therefore crucial for a successful design.

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Design and Optimization of a Nacelle for a UHBR Turbofan engine using a Class Shape Transformation based parameterization

Cited by 5 publications

References 9 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

Aerostructural Investigation of Shape Adaptive Rotor Blading for the Reduction of Bli Induced Losses in the Distorted Flow Regimes of a Transonic Fan Rotor

Integration of Wing-Mounted Over-Wing Engines on a Mid-Range Aircraft

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