民用航空发动机短舱推进一体化研究

F. Tejero, D. MacManus, I. Goulos, C. Sheaf
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引用次数: 0

摘要

据设想,未来的民用航空发动机将以超高涵道比运行,以降低比油耗。为了从新的发动机循环中获得预期的好处,这些新的动力装置可能会安装紧凑的短舱。对于这些新的结构,动力装置和机身之间的气动耦合可能会增加。因此,需要量化和进一步了解飞机集成对紧凑型航空发动机短舱的影响。这项研究提供了流动空气动力学变化的见解,以及动力装置、机身和组合飞机系统在一系列不同安装位置上最相关的性能指标的量化。与传统结构相比,安装在前方位置的紧凑型动力装置在空气动力学方面的净车辆力可提高约1.2%。这和航空发动机舱隔离时的改进是一样的。然而,对于紧密耦合的安装位置,由于飞机一体化对紧凑型短舱的影响较大,净车辆力的气动效益下降至0.44%。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Propulsion integration study of civil aero-engine nacelles
It is envisaged that future civil aero-engines will operate with ultra-high bypass ratios to reduce the specific fuel consumption. To achieve the expected benefits from the new engine cycles, these new powerplants may mount compact nacelles. For these new configurations the aerodynamic coupling between the powerplant and the airframe may increase. For this reason, it is required to quantify and further understand the effects of aircraft integration for compact aero-engine nacelles. This study provides an insight of the changes in flow aerodynamics as well as quantification of the most relevant performance metrics of the powerplant, airframe and the combined aircraft system across a range of different installation positions. Relative to a conventional architecture, there is an aerodynamic benefit in net vehicle force of about 1.2% for a compact powerplant when installed in forward positions. This is the same improvement that was identified when the aero-engine nacelles were in isolation. However, for close-coupled installation positions, the aerodynamic benefit in net vehicle force erodes to 0.44% due to the larger effects of aircraft integration on compact nacelles.
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