Numerical study of dynamic characteristics of Rotor 37 induced by back pressure and rotation speed variation

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-09-26 DOI:10.1016/j.ast.2025.110987

Fan Liu , Hong-Kai Ren , Fu-Zhen Chen , Hong Yan

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引用次数: 0

Abstract

The dynamic characteristics of fan component have an important impact on the transient performance and stable working margin during aero-engine acceleration and deceleration processes. The effects of the amplitude and frequency of back pressure variation on the dynamic characteristics of Rotor 37 are investigated in the designed rotation speed and during acceleration and deceleration processes. The shock wave evolution in cascade flow field is analyzed based on the three dimensional unsteady simulations of a single passage model. The results show that the dynamic operating points do not move along the constant rotation speed line when the outlet boundary is specified with a variable back pressure. The dynamic characteristics exhibit a hysteresis loop, and the corresponding position of shock wave in the cascade flow also shows a hysteresis variation. This hysteresis loop expands with the increase of back pressure amplitude, and deforms with the back pressure frequency. Based on the back pressure pulsation frequency and the characteristic time of disturbance propagation, a dimensionless pulsation frequency (

S_{f}

) is defined to reveal the influence of frequency on the rotor flow and the phase of variations. The dynamic characteristics of the rotor are closer to the steady results with

S_{f} \approx 0

. The hysteresis of the dynamic characteristics becomes significant with the range of

0 < S_{f} < 1

. As for

S_{f} > 1

, the influence range of back pressure variation on the rotor flow is decreased significantly and eventually limited to the region near the outlet. Moreover, the effects of constant and variable back pressure on the transient performance of Rotor 37 are compared during acceleration and deceleration processes between 90 % to 100 % designed rotation speed. The rotor efficiency hysteresis and fluctuation are elucidated to be associated with the leakage vortex breakage based on the total pressure loss distribution of the tip flow.

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背压和转速变化对转子37动态特性影响的数值研究

在航空发动机加减速过程中，风扇部件的动态特性对发动机的瞬态性能和稳定工作裕度有重要影响。研究了在设计转速和加减速过程中背压变化幅度和频率对转子37动态特性的影响。基于单通道模型的三维非定常模拟，分析了叶栅流场中激波的演化过程。结果表明：当出口边界为可变背压时，动态工作点不沿定转速线移动；其动力特性呈现迟滞回线，激波在叶栅流动中的对应位置也呈现迟滞变化。该滞回线随背压幅值的增加而膨胀，随背压频率的增加而变形。根据背压脉动频率和扰动传播的特征时间，定义了无量纲脉动频率（Sf），以揭示频率对转子流量的影响及其变化的相位。当Sf≈0时，转子的动态特性更接近稳态结果。动态特性的迟滞在0<；Sf<；1范围内变得明显。对于Sf>；1，背压变化对转子流量的影响范围明显减小，最终限制在出口附近区域。在90% ~ 100%设计转速范围内，比较了恒定背压和变背压对转子37加减速过程瞬态性能的影响。从叶尖总压损失分布出发，分析了转子效率的滞后和波动与泄漏涡破裂的关系。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.