Dynamic modeling and vibration characteristics analysis of the aero-engine dual-rotor system with Fan blade out

Yu, Pingchao; Zhang, Dayi; Ma, Yuanyuan; Hong, Jun

doi:10.1016/j.ymssp.2017.12.012

Cited by 127 publications

(41 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…(1) The dynamic model of a high-speed flexible cantilever rotor is established, and it can be used to effectively calculate the dynamic response of the rotor under the impact load. The characteristics of the transient and steady-response stages are analyzed, and the reaction forces of support bearings are calculated (2) The finite element dynamic model of the dual-rotor system is established, and the dynamic response of…”

Section: Resultsmentioning

confidence: 99%

See 1 more Smart Citation

Response of Aeroengine with Fusing Design Suffering FBO

Chen

Liu

et al. 2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

The loss of fan blades in an aeroengine, or fan-blade out (FBO), is a type of accident that causes a sudden imbalance and large impact load, which leads to complex vibration of a system. To conduct a dynamic analysis of an aeroengine rotor system is an important requirement for relevant departments. The purpose of this paper is to study the dynamic response of a complex dual-rotor system suffering FBO events and the protective effect of the fusing structure on the system. The dynamic model of an aeroengine dual-rotor system is established, and the response of the rotor system is obtained by calculation and analysis. The rear support bearing of the fan has a high reaction force, which may lead to bearing failure. The mechanism of a fusing structure is analyzed, and the results show that the sudden imbalance will produce impact loads on the rotor, resulting in a sharp increase in the vibration amplitude and reaction force, and then, attenuation to steady state. The fusing structure can reduce the amplitude of steady-state rotor vibration and reaction force on the support bearings. However, the transient response of the rotor will increase because of the sudden change in support stiffness.

show abstract

Section: Resultsmentioning

confidence: 99%

“…Compared with the general mechanical system, its safety and reliability have higher requirements [1]. Due to many factors, such as impact by birds, hail, and other foreign objects, the fan blades may be lost, causing serious accidents of the engine [2]. This engineering problem [3][4][5] is called fan-blade out (FBO) by many researchers.…”

Section: Introductionmentioning

confidence: 99%

Response of Aeroengine with Fusing Design Suffering FBO

Chen

Liu

et al. 2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…Modern aircraft engine tends to require high thrust-weightratio and superior flight safety performance [1], [2]. As a critical hot-section component of aircraft engine, the turbine rotor is often subjected to significant mechanical stresses under long-term harsh high-temperature, high-pressure and highspeed conditions [3], [4].…”

Section: Introductionmentioning

confidence: 99%

Multi-Surrogate Collaboration Approach for Creep-Fatigue Reliability Assessment of Turbine Rotor

Song

Bai

2020

IEEE Access

View full text Add to dashboard Cite

The creep-fatigue resistance of turbine rotor seriously affects the reliability performance and service lifetime of aircraft engine. Creep-fatigue reliability assessment is an effective measure to quantify the uncertain creep-fatigue damage and evaluate the creep-fatigue reliable life for turbine rotor. To improve the modeling accuracy and simulation efficiency of creep-fatigue reliability assessment, a multi-surrogate collaboration approach (MSCA) is proposed by absorbing the strengths of the proposed dynamic neural network surrogate (DNNS) into distributed collaborative strategy. The creep-fatigue reliability assessment of a typical turbine rotor is regarded as one case to estimate the presented MSCA with respect to the fluctuations of multi-physical variables and the variabilities of multi-model parameters. The assessment results reveal that the creep-fatigue reliable life of turbine rotor under reliability degree of 0.998 7 is 629 cycles, and the fatigue strength coefficient and holding creep time play a leading role on creep-fatigue reliable life since their effect probabilities of 27 % and 19 %, respectively. Comparison of various methods (direct Monte Carlo simulation, response surface, neural network surrogate, DNNS) shows that the presented MSCA holds high efficiency and accuracy in creep-fatigue reliability assessment of turbine rotor. INDEX TERMS Creep-fatigue life, reliability assessment, turbine rotor, surrogate model, neural network.

show abstract

“…For the aero-engine, several factors which include the structural deformation of the rotor system caused by the change of flight state, blade wear and impact, will lead to real-time changes in the unbalance state of the rotor system. The mass unbalance will cause engine vibration exceeding the standard and is easy to cause accidents including rotor rubbing, bearing damage and blade fracture [3][4][5]. Therefore, scholars at home and abroad have been committed to the research on the unbalance vibration of high-end equipment.…”

Section: Introductionmentioning

confidence: 99%

A Review on Self-Recovery Regulation (SR) Technique for Unbalance Vibration of High-End Equipment

Pan

Huo

et al. 2020

Chin. J. Mech. Eng.

View full text Add to dashboard Cite

The high-end equipment represented by high-end machine tools and aero-engines is the core component of the national intelligent manufacturing plan, and the mass unbalance is the main reason for its excessive vibration, that seriously impacts the operation efficiency and running life of the equipment. In order to change the traditional way that the fault of equipment can only be repaired by human, the self-recovery mechanism of human and animal are given to the equipment in this paper, which forms the self-recovery regulation (SR) system for unbalance vibration of high-end equipment. The system can online generate the self-recovery force to restrain the unbalance vibration of the equipment in operation, which is an important direction for the development of the equipment to the advanced intelligent stage. Based on the basic principles of SR technique, the typical engineering application cases of this technique in the field of aeroengine and high-end machine tools are introduced, and four related studies promoting the development of this technique are summarized and analyzed in turn. It includes feature extraction, imbalance location, regulation method and balancing actuator. Self-recovery Regulation (SR) Technique is an important way to realize intelligent manufacturing and intelligent maintenance. Relevant research can lay a technical foundation for the development of high-end equipment with self-health function.

show abstract

Dynamic modeling and vibration characteristics analysis of the aero-engine dual-rotor system with Fan blade out

Cited by 127 publications

References 22 publications

Response of Aeroengine with Fusing Design Suffering FBO

Response of Aeroengine with Fusing Design Suffering FBO

Multi-Surrogate Collaboration Approach for Creep-Fatigue Reliability Assessment of Turbine Rotor

A Review on Self-Recovery Regulation (SR) Technique for Unbalance Vibration of High-End Equipment

Contact Info

Product

Resources

About