Oleksandr Kolkov, Andrii Duliepov, Yevhenii Hlobin, Denys Dovhaliuk, Kateryna Balalaieva
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摘要

支板后的气动尾迹导致压气机进口气流不均匀。涡轮轴发动机压气机进气处的不均匀会导致压气机运行不稳定,从而降低发动机的经济性和效率。目前的工作是评估在一台TV3-117涡轴发动机的进气道支板中注入额外质量的空气对压气机进气道速度不均匀性的影响。利用Ansys Workbench Student免费版软件环境,采用数学建模的方法对任务进行求解。在解决问题时,涉及到几个模块:Geometry(创建几何),Mesh(生成计算网格),CFX(选择边界和初始条件,计算和计算的可视化)。本文以一台TV3-117涡轮轴发动机的输入机架叶片边缘为研究对象。分析结果表明,通过注入额外的空气质量,可以减少压气机进口速度的不均匀性。当注入质量流量为主质量流量的2.2…2.8%时,进口速度为100…160 m/s时,压气机进口的速度不均匀度从10…12%到4%。这样,压气机前方的速度场就会趋于均匀,对压气机的性能产生积极的影响。对速度场的可视化分析表明,当注入额外的空气质量时,气动尾迹发生了质的变化并显著减小,尾迹距离为10 mm处的速度与流芯的速度相差3%,而在没有边界层控制的情况下,尾迹的速度与流芯的速度相差10 ~ 12%。为了控制输入机架叶片中的附面层,不需要提供额外的空气,因为已经提供给加热输入机架的空气可以用于此。控制近附面层的进气道支叶的设计将是相当复杂的,但利用现代3D打印机可以实现所开发的控制后缘附面层的进气道支叶设计。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Вплив інжекції повітря у вхідні стійки турбовального двигуна
The aerodynamic wakes behind the struts cause uneven flow at the compressor inlet. An irregularity at the compressor inlet of a turboshaft engine causes unstable operation of the compressor, which can deteriorate the engine economy and a decrease its efficiency. The current work evaluates the effect of injection of an additional mass of air into the inlet struts of a TV3-117 turboshaft engine on the velocity non-uniformity at the compressor inlet. The solution of the task was carried out by the method of mathematical modeling using the free version of the Ansys Workbench Student software environment. When solving the problem, several modules were involved: Geometry (creation of geometry), Mesh (generation of the computational mesh), CFX (selection of boundary and initial conditions, calculation and visualization of the calculation). The blade rim of the input racks of a TV3-117 turboshaft engine was chosen as the object of study in this work. Analysis of the results obtained shows that by using the injection of additional air mass, it is possible to reduce the unevenness of the speed at the compressor inlet. When injected with a mass flow rate of 2.2...2.8% of the main mass flow rate at inlet speeds of 100...160 m/s, the speed unevenness at the compressor inlet decreases from 10...12% to 3...4%. Thus, the velocity field in front of the compressor will be nearly uniform, which will positively affect its performance. An analysis of the visualizations of the velocity fields shows that when additional air mass is injected, the aerodynamic wake changes qualitatively and decreases significantly, the speed in the wake at a distance of 10 mm differs from the speed in the flow core by 3%, in contrast to the case without boundary layer control, where the speed in the wake it differs in speed in the core of the flow by 10...12%. To control the boundary layer in the blades of the input racks, it will not be necessary to supply additional air because air that is already supplied to heat the input racks can be used for this. The design of the inlet leg blade with control of the near-boundary layer will be quite complicated, but it is possible to implement the developed inlet leg blade design for controlling the boundary layer in the trailing edge using modern 3D printers.
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