进气畸变条件下非轴对称风扇设计及扩稳机理研究

doi:10.7527/S1000-6893.2024.29725

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进气畸变条件下非轴对称风扇设计及扩稳机理研究

余军杨¹,傅文广¹,孙鹏¹,张韬²,王春雪²,赵伟²

1. 中国民航大学
2. 北京动力机械研究所

收稿日期:2023-10-16 修回日期:2024-01-10 出版日期:2024-01-11 发布日期:2024-01-11
通讯作者: 孙鹏
基金资助:
天津市教委科研计划项目;国家自然科学基金民航联合基金重点项目

Research on the design and stabilization mechanism of non-axisymmetric fans under inlet distortion conditions

Received:2023-10-16 Revised:2024-01-10 Online:2024-01-11 Published:2024-01-11

摘要/Abstract

摘要： 动力系统的进气畸变问题导致风扇性能下降、引发气动不稳定，从而对飞行器的安全构成潜在威胁，在军、民航空领域已受到广泛关注。为确保进气畸变条件下推进系统的可靠运行和飞行安全，本研究基于数值方法对某小涵道比涡扇发动机开展抗畸变风扇设计及扩稳研究。针对其畸变影响特征，采用非轴对称静子(NAS)布局来消除其不利影响，研究表明：NAS能够有效改善进气畸变条件下的风扇性能。相较于原型，在同流量工况下，绝热效率和总压比可分别相对增加1.37%和1.26%，稳定裕度可相对增加8.31%，实现了该NAS风扇的性能提升及扩稳目的；NAS设计直接作用于畸变区，有效改善了畸变区内的静叶冲角，抑制了静叶通道涡系结构的发展和迁移，较大程度减小静叶的扩压因子，从而有效消除了静叶的角区分离，使得静叶冲角周向分布相对均匀，有效改善风扇静叶内部流场，整体提高风扇的气动性能。此外，NAS设计还具有改善风扇后部内涵流场的潜力，使内涵出口的不均匀流场朝着周向均匀化方向发展，并且在有效减弱动态总压畸变强度、改善流场均匀性的同时，还兼具改善总温畸变的能力。

关键词: 进气畸变, 涡扇发动机, 非轴对称静子, 气动性能, 稳定裕度

Abstract: The issue of inlet distortion in propulsion systems leads to a decrease in fan performance and induces aerodynam-ic instability, posing a potential threat to aircraft safety. This concern has gained widespread attention in both mili-tary and civil aviation fields. To ensure the reliable operation of propulsion systems under inlet distortion conditions and maintain flight safety, this study conducted research on anti-distortion fan design and stability enhancement for a small bypass ratio turbofan engine using numerical methods. Taking into account the characteristics of distortion effects, this paper employed a Non-Axisymmetric Stator (NAS) arrangement to mitigate these adverse effects. The research suggests that NAS can effectively enhance fan performance under inlet distortion conditions. When com-pared to the prototype operating at the same mass flow rate, there are relative increases of 1.37% and 1.26% in adiabatic efficiency and total pressure ratio, respectively. Additionally, there is a relative increase of 8.31% in the stability margin. These enhancements have successfully met the objectives of improving performance and ex-panding stability for the NAS fan. The NAS design directly impacts the distortion zone, effectively improving the stator incidence angle within the distorted region. It suppresses the development and migration of vortex structures in the stator passage, resulting in a significant reduction in the stator diffusion factor. Consequently, it effectively eliminates corner separation in the stator passages, leading to a more uniform circumferential distribution of stator incidence angles. This, in turn, improves the internal flow field within the fan stator and enhances the overall aero-dynamic performance of the fan. Furthermore, NAS design has the potential to improve the flow field of the inner-bypass region behind the fan, encouraging the development of a more circumferentially uniform flow field at the inner-bypass outlet. Additionally, while effectively reducing the intensity of dynamic total pressure distortion and improving flow field uniformity, NAS design also possesses the capability to mitigate total temperature distortion.

Key words: Inlet distortion, Turbofan engine, Non-axisymmetric stator, Aerodynamic performance, Stability margin

中图分类号:

V231.3

余军杨傅文广孙鹏张韬王春雪赵伟. 进气畸变条件下非轴对称风扇设计及扩稳机理研究[J]. 航空学报, doi: 10.7527/S1000-6893.2024.29725.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

进气畸变条件下非轴对称风扇设计及扩稳机理研究

Research on the design and stabilization mechanism of non-axisymmetric fans under inlet distortion conditions

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