Improvement of Variation Propagation Control in Mechanical Assembly Using Adjustment Assembly Technique

This paper aims to provide an assembly method to improve mechanical assembly quality. In order to improve the variation propagation control in rotationally symmetric cylindrical components assembly, the eccentric and tilt errors of a single rotor stage were taken into account using a connective assembly model and the eccentric deviation in a mechanical assembly was minimized by properly selecting component orientations. Compared to the minimum cumulative error, the maximum cumulative error was reduced by 71 percent, and the average cumulative error was reduced by 57 percent in the assembly of three components. This article provides an assembly method through variation propagation control in rotationally symmetric cylindrical components assembly. The method could be extended to rotationally symmetric cylindrical components assembly, for example in the assembly of aero-engine components.

Download Full-text

Improvement of location and orientation tolerances propagation control in cylindrical components assembly using stack-build assembly technique

Assembly Automation ◽

10.1108/aa-03-2015-023 ◽

2015 ◽

Vol 35 (4) ◽

pp. 358-366 ◽

Cited By ~ 9

Author(s):

Lei Wang ◽

Chuanzhi Sun ◽

Jiubin Tan ◽

Bo Zhao ◽

Gu Wan

Keyword(s):

Tolerance Allocation ◽

Separate Analysis ◽

Assembly Model ◽

Content Type ◽

Final Assembly ◽

Assembly Method ◽

Assembly Technique ◽

Measuring Machine ◽

Engine Rotor

Purpose – This paper aims to provide an assembly method to improve cylindrical components assembly quality. The proposed method not only could be applied to tolerance allocation, but also could guide the assembly of cylindrical components. Design/methodology/approach – The paper claims to provide a stack-build assembly method using a connective assembly model to take the location and orientation tolerances of a rotor stage into account. Through the separate analysis of the location and orientation tolerances propagation process in the assembly, the quality of the final assembly of the rotationally symmetric cylindrical components assembly could be improved by properly selecting component orientations to minimize the eccentric deviation in the assembly. Findings – The effectiveness of the proposed stack-build assembly technique in improving the tolerance propagation in the assembly of cylindrical components was verified through experiments run with a measuring machine. A real aero-engine rotor was assembly using the proposed method; compared to the direct-build assembly technique, which had the component orientations without consideration, the stack-build assembly technique could be used to reduce the eccentric deviation in cylindrical components assembly by nearly 50 per cent. Originality/value – Different with the old methods, the new method defined the tolerances in detail, such as perpendicularity and angle of the lowest point, and could guide the assembly by the features of surfaces on different components. Through measuring the special tolerances of surfaces on the components, the best assembly angle for each component could be obtained.

Download Full-text

Investigation of the Water Guided Laser Micro-Jet Machining of Aero Engine Components

Volume 1: Processes ◽

10.1115/msec2017-2723 ◽

2017 ◽

Author(s):

Zhigang Wang

Keyword(s):

Energy Density ◽

Material Removal ◽

Removal Rate ◽

Cutting Speed ◽

Potential Method ◽

Laser Machining ◽

Aero Engine ◽

Engine Components ◽

The Relationship ◽

Dual Laser

The water guided laser micro-jet (LMJ) is a new potential method to machine aero engine parts with much less heat affected area and faster cutting speed than dry laser machining. The focus of this paper is to investigate the energy density and material removal for a dual-laser LMJ system. Then, the effects of dominated parameters on the energy density of LMJ are analyzed. Finally, a mathematical model is developed to describe the relationship between dominant laser parameters with the energy density of LMJ and material removal rate followed by machining case studies of aero engine components.

Download Full-text

Drilling of aero-engine components: Experiences from the shop floor

The Industrial Laser Handbook ◽

10.1007/978-1-4612-2882-0_12 ◽

1992 ◽

pp. 113-118 ◽

Cited By ~ 2

Author(s):

Martien H. H. van Dijk

Keyword(s):

Shop Floor ◽

Aero Engine ◽

Engine Components

Download Full-text

A research of assembly technique-oriented three-dimensional assembly model file structure tree information restructuring method

Information Technology and Computer Application Engineering ◽

10.1201/b15936-172 ◽

2013 ◽

pp. 747-750

Keyword(s):

Three Dimensional ◽

Assembly Model ◽

File Structure ◽

Structure Tree ◽

Model File ◽

Assembly Technique

Download Full-text

On cold dwell facet fatigue in titanium alloy aero-engine components

International Journal of Fatigue ◽

10.1016/j.ijfatigue.2016.11.034 ◽

2017 ◽

Vol 97 ◽

pp. 177-189 ◽

Cited By ~ 29

Author(s):

M.A. Cuddihy ◽

A. Stapleton ◽

S. Williams ◽

F.P.E. Dunne

Keyword(s):

Titanium Alloy ◽

Aero Engine ◽

Engine Components

Download Full-text

Detecting Symmetries in Mechanical Assembly Model

Journal of Mechanical Engineering ◽

10.3901/jme.2017.09.116 ◽

2017 ◽

Vol 53 (9) ◽

pp. 116

Author(s):

Shungang HUA

Keyword(s):

Assembly Model ◽

Mechanical Assembly

Download Full-text

Key Points in Engineering Application of 3D Laser Repair of Aero Engine Components

Applied laser ◽

10.3788/al20123203.184 ◽

2012 ◽

Vol 32 (3) ◽

pp. 184-187

Author(s):

杨薇 Yang Wei

Keyword(s):

Engineering Application ◽

Key Points ◽

Aero Engine ◽

Engine Components

Download Full-text

Non-Linear Aeromechanical Behaviour of Axial Core Compressor Stator Vanes

Volume 5: Turbo Expo 2007 ◽

10.1115/gt2007-27580 ◽

2007 ◽

Author(s):

Caetano Peng

Keyword(s):

Integrated Design ◽

Engine Performance ◽

Forced Response ◽

Design Tools ◽

Virtual Testing ◽

Aero Engine ◽

Stator Vane ◽

Recent Developments ◽

Aero Engines ◽

Engine Components

This paper highlights some engine non-linearities that can affect both performance and robustness of aero engines. It pays particular attention to non-linearities generated at the stator vane contact end joints. These non-linearities resulting from friction contact joints affect the vane modeshapes, damping and forced response. This work proposes upper and lower bound solutions based on vane end restraints non-linearities to predict conservative forced response of stator vanes. Some non-linearities such as those caused by mistuning can be beneficial to the component and system. There are also non-linearities that can be detrimental to engine performance, robustness and reliability. Moreover, it proposes and discusses the concept of temporal HCF or CCF lifing method. Recent developments in FE, CFD, mistuning, forced response and probabilistic codes can help to create more integrated design tools that incorporate time-dependent non-linearities in the lifing of aero engine components. Computations performed here demonstrated some level of component virtual testing. These analyses are important component virtual testing that will be gradually extended to whole aero engine virtual testing.

Download Full-text