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Aeroelastic effect of declining hub to tip ratios on the low-pressure compressor of future UHBR engines

减小冲程与叶尖比对未来 UHBR 发动机低压压气机的气动弹性效应

基本信息

批准号：
290312636
负责人：
Professor Dr.-Ing. Jens Friedrichs
金额：
--
依托单位：
Institut für Flugantriebe und Strömungsmaschinen (IFAS)
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2016
资助国家：
德国
起止时间：
2015-12-31 至 2020-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/290312636?language=en
关键词：
Aeroelastic effect declining hub tip

项目摘要

Aim of the project is the identification of key sensitivities, which will result in new or enhanced aerodynamic and aeroelastic interactions of future large bypass ratios of engines which are achieved through reduced hub-to-tip ratios. The approach is to assess the aeroelastic sensitivity of the first compressor stage with respect to the excitation by UHBR fan wakes in unprecedented quality based on an integrated investigation of various fan, duct- and IGV variations. From this research task, the following sub-goals are derived: a) Aerodynamic characterization and detailed study of three-dimensional flow structure of the inflow to the low-pressure compressor for UHBR fan stages with low hub-to-tip ratiofocussing on the hub near flow regime and secondary flow structures. b) Consideration of the rotor-cavity leakage flow. c) Consideration of the periodic unsteady interaction between fan rotor outlet, IGV and LPC-rotor.d) New Strategies to avoid increased forced-response and self-excitation of the blades in the front core engine due to typical secondary flow effects. d) e) Typical excitation sources are evaluated taking into account current trends in the development of aircraft engines, for example UHBR fans and geared turbofans and turboprops after their aeroelastic excitation and cataloged.

该项目的目的是确定关键的敏感性，这将导致未来发动机大旁路比的新的或增强的气动和气动弹性相互作用，这是通过降低轮毂与尖端的比率实现的。这种方法是基于对各种风扇、风道和IGV变化的综合调查，评估第一级压气机相对于UHBR风扇尾迹以前所未有的质量激励的气动弹性敏感性。根据这项研究任务，得出了以下子目标：a)低轮毂比UHBR风扇级低压压气机进气的三维流动结构的详细研究，主要集中在轮毂附近的流型和二次流结构。B)考虑转子-腔体泄漏流动。C)考虑了风扇转子出口、IGV和LPC转子之间的周期性非定常相互作用。d)避免由于典型的二次流效应而增加前芯发动机叶片的强迫响应和自激的新策略。D)e)对典型的激励源进行评估，同时考虑到飞机发动机发展的当前趋势，例如超高频段风扇和齿轮传动涡扇和涡轮螺旋桨在气动弹性激励和编目后。