Tolerance Design of Multistage Aero-Engine Casing Assembly by Vibration Characteristic Evaluation

2021 ◽  
Vol 34 (5) ◽  
pp. 04021064
Author(s):  
Hehe Kang ◽  
Zhi-Min Li ◽  
Tao Liu ◽  
Pizhong Qiao
Keyword(s):  
Tolerance Design ◽  
Vibration Characteristic ◽  
Aero Engine

Vibration Characteristics Analysis of an Aero-Engine Turbine Blade

2012 ◽  
Vol 487 ◽  
pp. 894-897
Author(s):  
Wei Qiang Zhao ◽  
Yong Xian Liu ◽  
Mo Wu Lu ◽  
Qing Jun Guo
Keyword(s):  
Optimal Design ◽  
Turbine Blade ◽  
Dynamic Characteristics ◽  
Natural Frequencies ◽  
Vibration Characteristics ◽  
Mode Shapes ◽  
Vibration Characteristic ◽  
Analysis Method ◽  
Aero Engine ◽  
Characteristics Analysis

This paper introduces the FEA method for a certain type of aero-engine turbine blade and makes a vibration characteristics analysis to this aero-engine turbine blade based on this method. The vibration characteristic of this aero-engine turbine blade is studied and the natural modal of the turbine blade is calculated based on UG software. The first six natural frequencies and mode shapes are given. According to the analysis results the dynamic characteristics of the blade are discussed. The analysis method and results in this paper can be used for further study on optimal design and vibration safety verification for the blade.

A method to control the amount of unbalance propagation in precise cylindrical components assembly

2019 ◽  
Vol 233 (13) ◽  
pp. 2458-2468 ◽  
Author(s):  
Chuanzhi Sun ◽  
Ming Hu ◽  
Yongmeng Liu ◽  
Maowei Zhang ◽  
Zewei Liu ◽  
...  
Keyword(s):  
Measurement Error ◽  
Tolerance Design ◽  
Machining Error ◽  
The Real ◽  
Assembly Strategy ◽  
Assembly Accuracy ◽  
Aero Engine ◽  
Assembly Guidance ◽  
Assembly Error ◽  
Optimal Assembly

The article provides a novel method to control the amount of unbalance propagation in precise cylindrical components assembly, which takes the machining error, the measurement error, and the assembly error into account. The coefficient and the correction factor matrices of mass eccentric deviations are defined to analyze the amount of unbalance propagation by building the connective assembly model. The influence of the machining error, the measurement error, and the assembly error on the mass center is analyzed in the assembly. The cumulative mass eccentric deviation can be reduced stage by stage in the assembly, and the amount of unbalance of final assembly can be minimized by controlling the assembly angle of each component. The effectiveness of the proposed method is verified by the assembly of the real aero-engine using the optimal assembly strategy. Compared to the worst assembly strategy, the values of the amount of unbalance using the optimal assembly strategy are reduced by 20%, 76%, and 79% for two, three, and four components assembly, respectively. Besides, the reasonable tolerance design area for each component is obtained with the proposed method for the real aero-engine assembly with four components. The proposed method can improve the assembly accuracy of cylindrical components and can be used for assembly guidance and tolerance design, especially for the assembly of multistage precise cylindrical components.

Recent Repair Technology for Aero-Engine Blades

2015 ◽  
Vol 9 (2) ◽  
pp. 132-141 ◽  
Author(s):  
Wang Tao ◽  
Ding Huapeng ◽  
Tang Jie ◽  
Wang Hao
Keyword(s):  
Repair Technology ◽  
Aero Engine

Further Computational Investigations Into Aero-Engine Bearing Chamber Off-Take Flows

2010 ◽  
Author(s):  
Adam Robinson ◽  
Carol Eastwick ◽  
Herve´ Morvan
Keyword(s):  
Experimental Work ◽  
Symmetry Plane ◽  
Two Phase ◽  
Pipe System ◽  
Aero Engine ◽  
Gravity Driven ◽  
Computational Fluid Dynamics Cfd ◽  
Modelling Assumptions ◽  
Static Head ◽  
Engine Bearing

Within an aero-engine bearing chamber oil is provided to components to lubricate and cool. This oil must be efficiently removed (scavenged) from the chamber to ensure it does not overheat and degrade. Bearing chambers typically contain a sump section with an exit pipe leading to a scavenge pump. In this paper a simplified geometry of a sump section, here simply made of a radial off-take port on a walled inclined plane, is analysed computationally. This paper follows on work presented within GT2008-50634. In the previous paper it was shown that simple gravity draining from a static head of liquid cold be modelled accurately, for what was akin to a deep sump situation fond in integrated gear boxes for example. The work within this paper will show that the draining of flow perpendicular to a moving film can be modelled. This situation is similar to the arrangements found in transmission bearing chambers. The case modelled is of a walled gravity driven film running down a plane with a circular off-take port, this replicates experimental work similar to that reported in GT2008-50632. The commercial computational fluid dynamics (CFD) code, Fluent 6 [1] has been employed for modelling, sing the Volume of Fluid (VOF) approach of Hirt and Nichols [2, 3] to capture the physics of both the film motion and the two phase flow in the scavenge pipe system. Surface tension [4] and a sharpening algorithm [5] are used to complement the representation of the free surface and associated effects. This initial CFD investigation is supported and validated with experimental work, which is only depicted briefly here as it is mainly sued to support the CFD methodology. The case has been modelled in full as well as with the use of a symmetry plane running down the centre of the plane parallel to the channel walls. This paper includes details of the meshing methodology, the boundary conditions sued, which will be shown to be of critical importance to accurate modelling, and the modelling assumptions. Finally, insight into the flow patterns observed for the cases modelled are summarised. The paper further reinforces that CFD is a promising approach to analysing bearing chamber scavenge flows although it can still be relatively costly.

Experimental and numerical investigations on novel models for mechanical behaviors of the elastic ring in aero-engine

2021 ◽  
pp. 095440622110130
Author(s):  
Zhong Luo ◽  
Lei Li ◽  
Yang Yang ◽  
Xiaojie Hou ◽  
Jiaxi Liu ◽  
...  
Keyword(s):  
3D Model ◽  
Maximum Stress ◽  
Simple Structure ◽  
Experimental Testing ◽  
Axial Direction ◽  
Elastic Ring ◽  
Load Range ◽  
Aero Engine ◽  
Stiffness Characteristics ◽  
First Time

The elastic ring is widely used in elastic support structures of aero-engine because of its simple structure and convenient manufacturing. In this paper, two elastic ring models, 3D and 2D models, are proposed, where the fillets between the bulges and ring are considered. The 2D model is more efficient for the calculation of stiffness characteristics. The 3D model can be used to obtain the maximum stress position in the axial direction. Then the experimental testing is carried out to verify the accuracy and effectiveness of the proposed models. Based on the proposed models, the stiffness nonlinearity and critical load of the elastic ring are found for the first time, which can be used to determine the normal working load range. Moreover, the elastic ring models with and without fillets are developed, and the effect of the fillets on stress is discussed. The results show that the stress is reduced by considering the fillets, which are not considered in the existing literature.

An improved dynamic load-strength interference model for the reliability analysis of aero-engine rotor blade system

2020 ◽  
pp. 095441002097289
Author(s):  
Bingfeng Zhao ◽  
Liyang Xie ◽  
Yu Zhang ◽  
Jungang Ren ◽  
Xin Bai ◽  
...  
Keyword(s):  
Reliability Analysis ◽  
Dynamic Load ◽  
Rotor Blade ◽  
Engineering Application ◽  
Weight Ratio ◽  
System Component ◽  
Aero Engine ◽  
Blade System ◽  
Improved Model ◽  
Engine Rotor

As the power source of an aircraft, aero-engine tends to meet many rigorous requirements for high thrust-weight ratio and reliability with the continuous improvement of aero-engine performance. In this paper, based on the order statistics and stochastic process theory, an improved dynamic load-strength interference (LSI) model was proposed for the reliability analysis of aero-engine rotor blade system, with strength degradation and catastrophic failure involved. In presented model, the “unconventional active” characteristic of rotor blade system, changeable functioning relationships and system-component configurations, was fully considered, which is necessary for both theoretical analysis and engineering application. In addition, to reduce the computation cost, a simplified form of the improved LSI model was also built for convenience of engineering application. To verify the effectiveness of the improved model, reliability of turbojet 7 engine rotor blade system was calculated by the improved LSI model based on the results of static finite element analysis. Compared with the traditional LSI model, the result showed that there were significant differences between the calculation results of the two models, in which the improved model was more appropriate to the practical condition.

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