Dynamic Model and Theoretical Investigation for the Fan-Blade Out Event in the Flexible Rotor System of Aero-Engine

2018 ◽  
pp. 18-33
Author(s):  
Yanhong Ma ◽  
Yongfeng Wang ◽  
Jie Hong
Keyword(s):  
Dynamic Model ◽  
Theoretical Investigation ◽  
Rotor System ◽  
Flexible Rotor ◽  
Aero Engine ◽  
Fan Blade

Modelling of Misaligned Rotor Systems in Aero-Engines

2012 ◽  
Author(s):  
Jun Li ◽  
Jie Hong ◽  
Yanhong Ma ◽  
Dayi Zhang
Keyword(s):  
Dynamic Model ◽  
Rotor System ◽  
Flexible Rotor ◽  
Lagrange Equations ◽  
Rotor Systems ◽  
Nonlinear Properties ◽  
Aero Engine ◽  
Series Of Experiments ◽  
Aero Engines ◽  
Good Agreement

Based on the analysis of structural and dynamic characteristics, a dynamic model of flexible rotor system under misalignment and unbalance excitation in aero-engine was developed through Lagrange equations. The model describes the mechanism and influencing factors of nonlinear properties of misaligned rotors. Then some numerical simulations were performed in order to get the vibration response in time and frequency domain. The results suggest that the rotor system and its coupling may behave in a complex and nonlinear way with the excitation of misalignment and unbalance. The response of the system contains 1× and 2× harmonics, and the spectrum signature closely relate to the misalignment magnitude and the distribution of unbalance mass. A series of experiments were also designed to verify the dynamic model. Their characteristics of response are in good agreement.

Robust Control of the Elastodynamic Vibrations of a Flexible Rotor System With Discontinuous Friction

2011 ◽  
Vol 133 (3) ◽  
Author(s):  
Mansour Karkoub
Keyword(s):  
Dynamic Model ◽  
Design Process ◽  
Nonlinear Models ◽  
Control Design ◽  
Rotor System ◽  
Control Technique ◽  
Flexible Rotor ◽  
Highly Nonlinear ◽  
Modeling Errors ◽  
The Difference

The work presented here deals with the control of a flexible rotor system using the μ-synthesis control technique. This technique allows for the inclusion of modeling errors in the control design process in terms of uncertainty weights. The dynamic model of the rotor system, which includes discontinuous friction, is highly nonlinear and has to be linearized around an operating point in order to use μ-synthesis. The difference between the linear and nonlinear models is characterized in terms of uncertainty weights and included in the control design process. The designed controller is robust to uncertainty in the dynamic model, spillover, actuator uncertainty, and noise. The theoretical findings of the μ-synthesis control design are validated through simulations and the results are presented and discussed here.

Modal characteristics and unbalance responses of fan rotor system with flexible support structures in aero-engine

2016 ◽  
Vol 231 (9) ◽  
pp. 1686-1705 ◽  
Author(s):  
Meiling Wang ◽  
Qingkai Han ◽  
Baogang Wen ◽  
Hao Zhang ◽  
Tianmin Guan
Keyword(s):  
Response Spectrum ◽  
Flexible Structures ◽  
Analytical Formula ◽  
Rotor System ◽  
Support Structures ◽  
Flexible Rotor ◽  
Test Rig ◽  
Modal Characteristics ◽  
Flexible Support ◽  
Aero Engine

This paper investigates the vibration patterns, i.e. rigid motions of shaft and elastic deformation of support structures, of fan rotor system in aero-engine, which differs from traditional flexible rotor systems, and together with its shaft transverse motions due to unbalanced mass. The fan rotor system commonly is composed of one rigid shaft and two flexible support structures (such as squirrel cages), which is effective to decrease the critical speeds avoiding serious shaft vibration due to unbalance. Scaled test rig for realistic fan rotor system is set up according to similarity principles, governing differential equations of which are deduced by means of Lagrangian approach with four degrees of freedom. In contrast to modeling a traditional flexible rotor system, the system stiffness is not determined by the shaft but the two flexible support structures. The rigid shaft only contributes to the inertial items of the governing equations. Parameter values of dynamic model are identified from measurements on the scaled test rig, the modal shapes and the modal energy distributions are calculated. These modal characteristics of the fan rotor system are quite different from those of a traditional flexible rotor system whose stiffness mainly contributed by its elastic shaft even the system values are consistent. The obtained modal characteristics are compared and confirmed by using the simulation results of a corresponding finite element model, in which shaft is built by rotating beam elements and its flexible structures are built by equivalent spring elements. Campbell diagrams of the fan rotor system are used to illustrate the gyroscopic effect with the increasing speeds. And then the unbalance responses are calculated through the deduced analytical formula rapidly and comparisons, including the response spectrum and orbits, the amplitude and phase frequency response curves, and operating deflection shapes, are carried out in the sub- and super-critical range.

Research on Dynamic Model of Rotors with Bearing Misalignment

2014 ◽  
Vol 539 ◽  
pp. 3-8 ◽  
Author(s):  
De Xin Ren ◽  
Jie Hong ◽  
Cun Wang
Keyword(s):  
Dynamic Model ◽  
Rotor System ◽  
Flexible Rotor ◽  
Bending Rigidity ◽  
Lagrange Method ◽  
Motion Equations ◽  
Excitation Force ◽  
Aero Engines ◽  
The Relationship ◽  
Mechanics Characteristics

Based on the structural and mechanics analysis of aero-engines rotor system, the dynamic model of the flexible rotor system with multi-supports are presented in order to solve the bearing misalignment problem of rotor system in aero-engines. The motion equations are derived through Lagrange method. The relationship between structural and mechanics characteristics parameters are built up. Finally, the dynamic influence of bearing misalignment on rotor system is divided into three kinds: additional rotor bending rigidity, additional bearing misalignment excitation force and additional imbalance. The equations suggest that additional imbalance excitation force activates the nonlinearity on rotor system and an additional 2× excitation force might appear.

Analytical Dynamic Model of Statically Indeterminate Rotor System and Misalignment

2017 ◽  
Author(s):  
Guang Zhao ◽  
Shengxiang Li ◽  
Yunqiu Zhang ◽  
Zhiliang Xiong ◽  
Qingkai Han
Keyword(s):  
Dynamic Model ◽  
Virtual Work ◽  
Rotor System ◽  
Aero Engine ◽  
Flexible Supports ◽  
Natural Characteristic ◽  
Global Stiffness Matrix ◽  
Rotor Structure ◽  
Experimental Reference ◽  
Analytical Dynamic

For the statically indeterminate rotor structure of low-pressure rotor system in aero-engine, mechanics features of bearing deformation and rotor structure were analyzed, combined with the principle of virtual work, and the global stiffness matrix of the rotor system was deduced. According to the Lagrange method, the analytical dynamic model of statically indeterminate rotor system with three flexible supports based on the flexibility analysis was built. An analytical dynamic model of intermediate supporting misalignment was established on the basis of the model. The natural characteristic and unbalance response of aligned and misaligned statically indeterminate rotor system were obtained through the analytical solution, and the experimental verification was conducted. These findings indicate that intermediate bearing misalignment of statically indeterminate rotor system can not only produce the 2X component, but also make the 1X component change. The experimental results are essentially in agreement with the calculated ones. The study laid the foundations for model basis and experimental reference of the statically indeterminate rotor system design, dynamic modeling and vibration control.

Multi-Objective Optimization of a Two-Disk Rotor System

2014 ◽  
Vol 705 ◽  
pp. 79-82
Author(s):  
Jing Jing Huang ◽  
Long Xi Zheng ◽  
Mei Qing
Keyword(s):  
Design Optimization ◽  
High Speed ◽  
Maximum Amplitude ◽  
Optimization Method ◽  
Rotor System ◽  
Practical Significance ◽  
Flexible Rotor ◽  
Multi Objective ◽  
Aero Engine ◽  
Minimum Amplitude

A two-disk rotor system under the aero-engine support structure of typical 1-0-1 was established and the dynamical characteristics were analyzed. The two-disk rotor model was integrated to the Isight. The multi-objective design optimization of the transient process was then carried out with Evolutionary Optimization Algorithm. The optimum positions of the two-disk rotor system were obtained at the specified constraints. In order to verify the validity of the design optimization, the transient test was carried out on a high-speed flexible rotor mockup. The maximum amplitude of disk 1 cross the first critical rotation speed fell 50% and the maximum amplitude of disk 2 decreased by 20%. Experimental results indicated that the optimization method could obtain the position of the flexible rotor with the minimum amplitude and improve the design efficiency and quality, which had practical significance in the design of aero-engine rotor system.

The Dynamic Load of Inter-Shaft Bearing and its Transmission Characteristic of Complex Rotor System

2018 ◽  
Author(s):  
Huan Yu ◽  
Bo Sun ◽  
YanHong Ma ◽  
Jie Hong
Keyword(s):  
Dynamic Model ◽  
Dynamic Load ◽  
Strain Energy ◽  
Vibration Mode ◽  
Resonance State ◽  
Rotor System ◽  
Rotor Vibration ◽  
Restoring Force ◽  
Flexural Mode ◽  
Aero Engine

Aiming at the dynamic design of dual rotor of aero-engine, the dynamic model of dual rotor system was established. And then based on the simulation results of the dynamic model established above, the unbalance distribution of dual rotor and the strain energy distribution of the flexural deformation were analyzed. The results showed that the dynamic load on inter-shaft bearing is determined by the rotor vibration mode and the rotor vibration response at the position of bearing. The flexural deformation can also affect the dynamic load on inter-shaft bearing. Under the influence of elastic restoring force generated by the flexural deformation of rotors, the dynamic load on the inter-shaft bearing under flexural mode is higher than that under the rigid mode. It was found that large dynamic load may act on inter-shaft bearing even though the rotor is not operating in the resonance state. And due to the internal damping of the rotor, the large dynamic load on the inter-shaft bearing can be obviously reduced when the load transmit to other bearings via the rotor with flexural deformation.

Aero-engine dynamic model based on an improved compact propulsion system dynamic model

2021 ◽  
pp. 095965182098408
Author(s):  
Qiangang Zheng ◽  
Yong Wang ◽  
Chongwen Jin ◽  
Haibo Zhang
Keyword(s):  
Dynamic Model ◽  
Propulsion System ◽  
System Dynamic ◽  
Inlet Temperature ◽  
System Dynamic Model ◽  
Component Level ◽  
Engine Model ◽  
Surge Margin ◽  
Aero Engine ◽  
Engine Dynamic

The modern advanced aero-engine control methods are onboard dynamic model–based algorithms. In this article, a novel aero-engine dynamic modeling method based on improved compact propulsion system dynamic model is proposed. The aero-engine model is divided into inlet, core engine, surge margin and nozzle models for establishing sub-model in the compact propulsion system dynamic model. The model of core engine is state variable model. The models of inlet, surge margin and nozzle are nonlinear models which are similar to the component level model. A new scheduling scheme for basepoint control vector, basepoint state vector and basepoint output vector which considers the change of engine total inlet temperature is proposed to improve engine model accuracy especially the steady. The online feedback correction of measurable parameters is adopted to improve the steady and dynamic accuracy of model. The modeling errors of improved compact propulsion system dynamic model remain unchanged when engine total inlet temperature of different conditions are the same or changes small. The model accuracy of compact propulsion system dynamic model, especially the measurable parameters, is improved by online feedback correction. Moreover, the real-time performance of compact propulsion system dynamic model and improved compact propulsion system dynamic model are much better than component level model.

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