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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Fan Flow Field in an Installed Variable Pitch Fan Operating in Reverse Thrust for a Range of Aircraft Landing Speeds
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Fan Flow Field in an Installed Variable Pitch Fan Operating in Reverse Thrust for a Range of Aircraft Landing Speeds

机译：在一定范围的飞机着陆速度下，反向倾斜运行的可变螺距风扇中的风扇流场

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The installed flow field for a variable pitch fan (VPF) operating in reverse thrust for the complete aircraft landing run is described in this paper. To do this, a VPF design to generate reverse thrust by reversing airflow direction is developed for a representative 40,000 lbf modern high bypass ratio engine. Thereafter, to represent the actual flow conditions that the VPF would face, an engine model that includes the nacelle, core inlet splitter, outlet guide vanes, bypass nozzle, core exhaust duct, aft-body plug, and core nozzle is designed. The engine model with the VPF is attached to a representative airframe in landing configuration to include the effects of installation. A rolling ground plane that mimics the runway during the landing run is also included to complete the model definition. Three-dimensional (3D) Reynolds-averaged Navier-Stokes (RANS) solutions are carried out for two different VPF stagger angle settings and rotational speeds to obtain the fan flow field. The dynamic installed VPF flow field is characterized by the interaction of the freestream and the reverse stream flows. The two streams meet in a shear layer in the fan passages and get deflected radially outward before turning back onto themselves. The flow field changes with stagger setting, fan rotational speed, and the aircraft landing speed because of the consequent changes in the momentum of the two streams. The description of the installed VPF flow field as generated in this study is necessary to (a) qualify VPF designs that are typically designed by considering only the uninstalled static flow field and (b) choose the VPF operating setting for different stages of the aircraft landing run.
机译：本文描述了在整个飞机着陆运行中以反推力运行的可变螺距风扇（VPF）的安装流场。为此，针对具有代表性的40,000 lbf的现代高旁路比发动机，开发了一种VPF设计，该设计通过反转气流方向来产生反向推力。此后，为了表示VPF将会面对的实际流动条件，设计了一种发动机模型，该发动机模型包括机舱，岩心入口分流器，出口导流叶片，旁路喷嘴，岩心排气管，后身塞子和岩心喷嘴。带有VPF的发动机模型在着陆配置中连接到代表性的机身，以包括安装效果。还包括在着陆运行期间模拟跑道的滚动地面，以完成模型定义。针对两个不同的VPF交错角度设置和转速执行了三维（3D）雷诺平均Navier-Stokes（RANS）解决方案，以获得风扇流场。动态安装的VPF流场的特征在于自由流和反向流的相互作用。两条气流在风扇通道中的剪切层中汇合，并在径向转向之前向外偏转。流场随交错设置，风扇转速和飞机着陆速度而变化，这是由于两条流的动量随之变化。对本研究中生成的已安装VPF流场的描述对于（a）验证通常通过仅考虑未安装的静态流场而设计的VPF设计和（b）为飞机降落的不同阶段选择VPF操作设置是必要的跑。

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