Installed nacelle aerodynamics at cruise and windmilling conditions

IF 1.2 4区 工程技术 Q3 ENGINEERING, AEROSPACE Aircraft Engineering and Aerospace Technology Pub Date : 2024-07-11 DOI:10.1108/aeat-03-2023-0070
Francisco Sánchez-Moreno, David MacManus, Fernando Tejero, Josep Hueso-Rebassa, Christopher Sheaf
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Abstract

Purpose

The decrease in specific thrust achieved by Ultra-High Bypass Ratio (UHBPR) aero-engines allows for a reduction in specific fuel consumption. However, the typical associated larger fan size might increase the nacelle drag, weight and the detrimental interference effects with the airframe. Consequently, the benefits from the new UHBPR aero-engine cycle may be eroded. This paper aims to evaluate the potential improvement in the aerodynamic performance of compact nacelles for installed aero-engine configuration.

Design/methodology/approach

Drooped and scarfed non-axisymmetric compact and conventional nacelle designs were down selected from a multi-point CFD-based optimisation. These were computationally assessed at a set of installation positions on a contemporary wide-body, twin-engine transonic aircraft. Both cruise and off-design conditions were evaluated. A thrust and drag accounting method was applied to evaluate different aircraft, powerplant and nacelle performance metrics.

Findings

The aircraft with the compact nacelle configuration installed at a typical installation position provided a reduction in aircraft cruise fuel consumption of 0.44% relative to the conventional architecture. However, at the same installation position, the compact design exhibits a large flow separation at windmilling conditions that is translated into an overall aircraft drag penalty of approximately 5.6% of the standard cruise net thrust. Additionally, the interference effects of a compact nacelle are more sensitive to deviations in mass flow capture ratio (MFCR) from the nominal windmilling diversion condition.

Originality/value

This work provides a comprehensive analysis of not only the performance but also the aerodynamics at an aircraft level of compact nacelles compared to conventional configurations for a range of installations positions at cruise. Additionally, the engine-airframe integration aerodynamics is assessed at an off-design windmilling condition which constitutes a key novelty of this paper.

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巡航和风力条件下安装的短舱空气动力装置
目的超高旁路比(UHBPR)航空发动机实现了比推力的下降,从而降低了比耗油量。但是,风扇尺寸通常较大,可能会增加短舱阻力、重量和对机身的有害干扰。因此,新型 UHBPR 航空发动机循环的优势可能会被削弱。本文旨在评估已安装航空发动机配置的紧凑型短舱在气动性能方面的潜在改进。在当代宽体双引擎跨音速飞机上的一组安装位置对这些设计进行了计算评估。对巡航和非设计条件都进行了评估。结果在典型安装位置安装紧凑型短舱配置的飞机与传统结构相比,巡航油耗降低了 0.44%。然而,在相同的安装位置,紧凑型设计在风力条件下表现出较大的流动分离,转化为飞机整体阻力损失,约为标准巡航净推力的 5.6%。此外,紧凑型短舱的干扰效应对质量流量捕获比 (MFCR) 与名义风动分流条件的偏差更为敏感。此外,本文还对非设计风力条件下的发动机-机身一体化空气动力学进行了评估,这也是本文的一大创新之处。
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来源期刊
Aircraft Engineering and Aerospace Technology
Aircraft Engineering and Aerospace Technology 工程技术-工程:宇航
CiteScore
3.20
自引率
13.30%
发文量
168
审稿时长
8 months
期刊介绍: Aircraft Engineering and Aerospace Technology provides a broad coverage of the materials and techniques employed in the aircraft and aerospace industry. Its international perspectives allow readers to keep up to date with current thinking and developments in critical areas such as coping with increasingly overcrowded airways, the development of new materials, recent breakthroughs in navigation technology - and more.
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