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Comparative Assessment between Variable Area Fan Nozzle Concepts at Inner and Outer By-Pass Duct Surfaces

机译:内外旁通管道表面可变面积风扇喷嘴概念的比较评估

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The next generation of civil turbofan engines target the by-pass ratios of up to 20:1, which are far beyond the current levels of 10:1 to 12:1. These jet engines require a significant step forward in low-pressure system technologies. The European Union supports within the 7th Framework the research activities for these new low-pressure systems through the program ENOVAL [1]. Such a new low-pressure technology can be achieved through an innovative fan design with a low fan pressure ratio and a radically increased fan diameter compared to the current conventional turbofan engines. The aerodynamic stability of such large fans is quite likely very sensitive against backpressure variations in the by-pass duct. For this reason, the back-pressure regulation of such a large fan, especially during the take-off operation, can be achieved through the introduction of a Variable Area Fan Nozzle (VAFN). On the given geometry, two potential design spaces were studied and the conceptual designs of two VAFN concepts were created. This paper presents a comparative study between both the concepts following the requirements of different attributes. These involve the performance assessment, structural design study, and a preliminary assessment of the design features for integration into the nacelle or in the core fairing structure. For the comparison, the clean nozzle, without any modulation of the BPD aero lines, was taken as the reference case. The VAFN assessments were carried out on two VAFN positions, over- and under-area, considering the maximum take-off and maximum climb flight conditions respectively. For the selected concepts, CFD trade studies were executed in order to compare the nozzle performance, in which three main governing design parameters i.e. discharge-, thrust performance coefficient, and drag, were examined. This research has received funding from the European Union's 7th Framework Program under grant agreement number 604999.
机译:下一代民用涡轮箱发动机针对高达20:1的副通过比率,远远超过目前的10:1至12:1。这些喷气发动机需要在低压系统技术方面前进。欧洲联盟在第7架框架内支持这些新的低压系统的研究活动[1]。这种新的低压技术可以通过具有低风扇压力比的创新风扇设计来实现,并且与当前传统的涡轮扫发动机相比,具有低风扇压力比和扇形直径的扇形直径。这种大型风扇的空气动力学稳定性很可能对旁路管道中的背压变化非常敏感。因此,通过引入可变区域风扇喷嘴(VAFN),可以实现这种大型风扇的背压调节,特别是在起飞操作期间。在给定的几何形状上,研究了两个潜在的设计空间,并创建了两个VAFN概念的概念设计。本文介绍了不同属性要求之后的概念之间的比较研究。这些涉及性能评估,结构设计研究以及对设计特征的初步评估,以将其整合到机舱或核心整流结构中。为了比较,清洁喷嘴,没有BPD航空线的任何调制,作为参考情况。 vafn评估是在两个VAFN位置,过度和下面进行的,考虑到分别最大的起飞和最大攀爬飞行条件。对于所选概念,执行CFD贸易研究以比较喷嘴性能,其中检查了三个主要管理设计参数等。进行了排放,推力性能系数和阻力。该研究已收到欧盟第七次框架计划的资金于拨款协议编号604999。

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