Dynamic characteristics analysis of an aeroengine rotor system subjected to aerodynamic excitation

Shao, Jun; Wu, Jigang; Zhang, Yuan

doi:10.1088/1361-6501/acefec

Cited by 3 publications

(2 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Among these components, blades are one of the most critical and numerous parts in aircraft engines. These blades operate in harsh conditions characterized by high temperatures, high pressures, and heavy loads over an extended 3 These authors contributed to the work equally and should be regarded as co-first authors. * Authors to whom any correspondence should be addressed.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Measuring the profile of aircraft engine blades using spectral confocal sensors

Chen,

Xue,

Sun

et al. 2024

Meas. Sci. Technol.

View full text Add to dashboard Cite

The geometric parameters of aircraft engine blades need to be precisely measured to ensure the quality of the blades for the normal operation of aircraft engines. This study aims to address the challenges of existing measurement systems in balancing efficiency, accuracy, and completeness. Additionally, it aims to enhance the accuracy and robustness of the algorithm for extracting blade profile characteristic parameters. In this paper, a spectral confocal sensor is employed to establish a blade profile measurement system. The design includes a probe sampling strategy, and a standard ball is used to calibrate the sensor probe's light emission direction and the precise rotation center of the turntable. The paper proposes the use of methods such as partition search algorithm, binary search, and curvature segmentation to process point cloud data of blade body and tenon. We have conducted experimental measurements on the blades of an aircraft engine. The acquired three-dimensional point cloud data of multiple sets of blade cross-sections and dovetail sections were processed. After calculation, the maximum measurement errors for chord length, maximum blade thickness, tenon width, bottom height, top angle, and bottom angle are -0.0036mm, -0.00721mm, -0.0102mm, -0.00928mm, 0.0086 °, and -0.0058 °, respectively. This process validates the effectiveness of the proposed method and has high measurement accuracy. Compared with the CMM method, this method is more accurate in measuring small pits and large curvature micro surfaces, with higher measurement integrity and higher measurement efficiency.

show abstract

Section: Introductionmentioning

confidence: 99%

“…Serving as key elements for airflow guidance and energy conversion, the quality of blades directly impacts the performance of the engine. Therefore, in large-scale manufacturing, achieving high precision and efficiency in blade measurements is of paramount importance [2,3].…”

Section: Introductionmentioning

confidence: 99%

Measuring the profile of aircraft engine blades using spectral confocal sensors

Chen,

Xue,

Sun

et al. 2024

Meas. Sci. Technol.

View full text Add to dashboard Cite

show abstract

Dynamic characteristic analysis of a twin-spool rotor–casing system with looseness and intershaft rubbing coupling faults

Shao,

Wu,

Yang

et al. 2024

J Mech Sci Technol

View full text Add to dashboard Cite

Backward whirling behaviors of a twin-spool rotor system with coupling inter-shaft and rotor-stator rubbings

Shao,

Wu,

Zhang

2024

Proceedings of the Institution of Mechanical Engineers, Part C:

Self Cite

View full text Add to dashboard Cite

The aim of this paper is to investigate the backward whirling behaviors of an aero-engine twin-spool rotor system with coupling rubbings. Firstly, considering the effects of the inter-shaft and rotor-stator rubbings, the dynamic model for a twin-spool rotor system without inter-shaft bearing is developed by means of finite element method. Subsequently, using three-dimensional full spectrum and rotor orbits, the backward whirling behaviors of twin-spool rotor system are illustrated, and the effects of rotational direction and speed ratio on the whirling direction of the rotor are discussed as well. The results reveal that backward inter-shaft and rotor-stator frictions are the physical reasons of backward whirl in the rubbing rotor. For the twin-spool rotor system with inter-shaft rubbing, when the speed ratio is positive, the high-pressure rotor can strengthen the rotation of the low-pressure rotor through the inter-shaft rubbing point, and the low-pressure rotor maintains in forward whirl. In contrast, when the speed ratio is negative, the larger inter-shaft friction may induce backward whirl for the low-pressure rotor. Regardless of whether the speed ratio is positive or negative, the rotor-stator rubbing always contributes to promote the backward whirl of the rotor. As the speed ratio goes up, the initial speed of the backward whirl drops and the opposite is also true. These findings contribute to understanding the mechanism of backward whirling behaviors for the rubbing twin-spool rotor system.

show abstract

Dynamic characteristics analysis of an aeroengine rotor system subjected to aerodynamic excitation

Cited by 3 publications

References 28 publications

Measuring the profile of aircraft engine blades using spectral confocal sensors

Measuring the profile of aircraft engine blades using spectral confocal sensors

Dynamic characteristic analysis of a twin-spool rotor–casing system with looseness and intershaft rubbing coupling faults

Backward whirling behaviors of a twin-spool rotor system with coupling inter-shaft and rotor-stator rubbings

Contact Info

Product

Resources

About