The preliminary design of a scaled Composite UHBR Fan for a wind tunnel test campaign
The preliminary design of a scaled Composite UHBR Fan for a wind tunnel test campaign
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用于风洞测试的比例复合 UHBR 风扇的初步设计
DOI：
10.1088/1757-899x/1226/1/012041
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发表时间：
2022
期刊：
影响因子：
--
通讯作者：
A. Vavouliotis
中科院分区：
文献类型：
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作者：
N. Paletta;J. Flüh;J. Lindemann;J. Seume;J. Goessling;J. Friedrichs;T. Eggers;S. Russo;N. Natale;D. Vlachos;D. Mazarakos;A. Baltopoulos;A. Vavouliotis
CA3ViAR项目的目标是设计一种具有民机超高涵道比（UHBR）风扇不稳定机制代表性的开放式试验用例风扇，并进行全面的实验研究，以测量各种工况下的气动、气动弹性和气动声学性能。实验测试将在德国Technische Universität喷气推进和涡轮机械研究所（IFAS）的推进测试设施（PTF）进行。该项目的最终目标是为整个研究界提供一个开放的测试案例，包括几何、数值和实验结果，为复合UHBR风扇设计建立新的参考。这将支持开发新的方法和工具，以开发更安全、更轻、更高效的复合风扇，用于更环保的UHBR发动机。本文介绍了用于风洞试验的低跨音速风机（LTF）的初步设计，其主要要求是在气动和/或气动弹性不稳定的条件下安全可控地运行。重点讨论了综合气动设计、驱动结构设计的策略、考虑进气道声反射的颤振分析、动力和应力分析以及气动声学测量优化。复合叶片和转子轮毂的初步机械设计，以及转子仪器和在复合叶片中嵌入传感器的相关研究也是本文的一部分，并通过制造试验和演示试验加以补充，从而全面了解到初步设计审查为止的所有项目活动。
The ambition of the CA3ViAR project is to design an open test case fan that experiences instability mechanisms, which are representative for ultra-high bypass ratio (UHBR) fans of civil aircrafts, and to perform a comprehensive experimental investigation to measure aerodynamic, aeroelastic and aeroacoustic performance in a wide range of operational conditions. Experimental tests will be performed in the Propulsion-Test-Facility (PTF) of the Institute of Jet Propulsion and Turbomachinery (IFAS) of Technische Universität Braunschweig, Germany. The final objective of the project is to provide an open test case for the entire research community, with geometries, numerical and experimental results to establish a new reference for composite UHBR fan design. This will support the development of new methods and tools for the development of safer, lighter and more efficient composite fans for greener UHBR engines. In this work the preliminary design of the low transonic fan (LTF) to be used as test article, whose main requirement is to be operated in a safe and controlled way in conditions of aerodynamic and/or aeroelastic instability during wind tunnel operations, is presented. More in particular, consolidated aerodynamic design, strategy adopted to drive the structural design, flutter analysis taking into account acoustic reflection at the intake, dynamic and stress analyses, as well as aeroacoustic measurement optimization are presented and discussed. The preliminary mechanical design of composite blades and the rotor hub, together with the rotor instrumentation and related studies to embed sensors in the composite blades, are also part of this article, and complemented by manufacturing trials and demonstration tests give the full picture of all the project activities up to the preliminary design review.