进气畸变条件下非轴对称风扇设计及扩稳机理

doi:10.7527/S1000-6893.2024.29725

Abstract

Abstract:

Inlet distortion in propulsion systems leads to decrease in fan performance and induces aerodynamic instability， posing a potential threat to aircraft safety and drawing extensive attention in both military and civil aviation fields. To ensure 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， we employed a Non-Axisymmetric Stator （NAS） arrangement to mitigate the adverse effects. The research suggests that the NAS can effectively enhance fan performance under inlet distortion conditions. Compared to the prototype operating at the same mass flow rate， relative increases of 1.37%， 1.26% and 8.31% can be observed in adiabatic efficiency， total pressure ratio， and stability margin， respectively， successfully meeting the objectives of improving performance and expanding 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 aerodynamic performance of the fan. Furthermore， the 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， the NAS design also possesses the capability to mitigate total temperature distortion.

Key words: inlet distortion, turbofan engine, non-axisymmetric stator, aerodynamic performance, stability margin

CLC Number:

V231.3

Junyang YU, Wenguang FU, Peng SUN, Tao ZHANG, Chunxue WANG, Wei ZHAO. Design and stabilization mechanism of non-axisymmetric fans under inlet distortion conditions[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(16): 129725.

Figures/Tables 31

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名称	稳定裕度/%	绝热效率	总压比
相对变化量/%	8.31	1.37	1.26
ORI风扇	19.33	0.796 8	1.632 2
NAS风扇	20.94	0.807 8	1.652 8

名称	紊流度/%	温度畸变指数
相对变化量/%	95	0.990 0
ORI风扇	0.059 7	0.015 7
NAS风扇	0.003 0	0.015 5

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Design and stabilization mechanism of non-axisymmetric fans under inlet distortion conditions

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