scholarly journals On the Fatigue and Fracture of Bladed and Integrally Bladed Rotors of Aircraft Engine Compressors

2021 ◽  
Author(s):  
Dikran Mangardich
Keyword(s):  
High Cycle Fatigue ◽  
Aircraft Engine ◽  
Fatigue Loading ◽  
Crack Trajectory ◽  
Fatigue And Fracture ◽  
Fan Blade ◽  
Element Technique ◽  
Compressor Disk ◽  
Model Crack ◽  
Engine Compressors

The fatigue and fracture for bladed and integrally bladed rotors (IBR) of aircraft engine compressors has been studied. For IBRs, a new distinct finite element technique was developed to model crack propagation under combined low cycle and high cycle fatigue loading. The crack trajectory, aspect ratio, and shape resulting from the method agreed very well with airfoils which fractured in service. The technique can be extended on other compressor disk applications. For bladed rotors limited by fretting fatigue, a unique fracture mechanics based methodology was developed for obtaining an evolved coefficient of friction (COF) resulting from fretting motion between the fan blade and hub. The predicted nucleation location, nucleation life, crack trajectory, shape and propagation life agreed well with the fractured components. The study confirms that the fretting-specific modified Smith-Watson-Topper (SWT) parameter more accurately predicts the nucleation location and life of the crack compared to the plain fatigue SWT parameter.

scholarly journals On the Fatigue and Fracture of Bladed and Integrally Bladed Rotors of Aircraft Engine Compressors

2021 ◽  
Author(s):  
Dikran Mangardich
Keyword(s):  
High Cycle Fatigue ◽  
Aircraft Engine ◽  
Fatigue Loading ◽  
Crack Trajectory ◽  
Fatigue And Fracture ◽  
Fan Blade ◽  
Element Technique ◽  
Compressor Disk ◽  
Model Crack ◽  
Engine Compressors

The fatigue and fracture for bladed and integrally bladed rotors (IBR) of aircraft engine compressors has been studied. For IBRs, a new distinct finite element technique was developed to model crack propagation under combined low cycle and high cycle fatigue loading. The crack trajectory, aspect ratio, and shape resulting from the method agreed very well with airfoils which fractured in service. The technique can be extended on other compressor disk applications. For bladed rotors limited by fretting fatigue, a unique fracture mechanics based methodology was developed for obtaining an evolved coefficient of friction (COF) resulting from fretting motion between the fan blade and hub. The predicted nucleation location, nucleation life, crack trajectory, shape and propagation life agreed well with the fractured components. The study confirms that the fretting-specific modified Smith-Watson-Topper (SWT) parameter more accurately predicts the nucleation location and life of the crack compared to the plain fatigue SWT parameter.

scholarly journals A Numerical Method Used for the Simulation of Self-Excited Vibrations that Arise in the Aircraft Engine Fan Blade Ring

2020 ◽  
Vol 0 (2) ◽  
pp. 12-18
Author(s):  
Viacheslav Vladimirovich Donchenko ◽  
Vitaly Isaevich Gnesin ◽  
Lyubov Vladimirovna Kolodyzhnaya ◽  
Igor Fedorovich Kravchenko ◽  
Oleksii Vladimirovich Petrov
Keyword(s):  
Numerical Method ◽  
Aircraft Engine ◽  
Blade Ring ◽  
Fan Blade

Structural Design and Analysis of Cylindrical Squirrel Cage to Meet Stiffness, Strength and High Cycle Fatigue Life for an Aero Engine

2017 ◽  
Author(s):  
Senthil Kumar Kandhaswamy Srinivasan ◽  
Nazar Periarowthar
Keyword(s):  
Fatigue Life ◽  
Structural Design ◽  
High Cycle Fatigue ◽  
Aircraft Engine ◽  
Squeeze Film ◽  
Cycle Fatigue ◽  
Squeeze Film Damper ◽  
Squirrel Cage ◽  
Fillet Radius ◽  
Goodman Diagram

Squeeze film dampers have traditionally been used in aircraft engine to overcome stability and vibration problems that are not adequately handled with conventional style bearings. One of the key design features in a squeeze film damper [1] configuration is the introduction of flexibility in the bearing support. The simplest means to provide the support flexibility in the squeeze film damper is through the use of squirrel cage [2]. This paper deals with structural design analysis of cylindrical squirrel cage of an aircraft engine. Design of the squirrel cage needs a balance between stiffness and strength requirements. To meet the strength, stiffness and fatigue life requirements, squirrel cage web dimensions and fillet radius are modified. The various configurations of the squirrel cage have been evaluated to arrive at the optimum design. Stress analysis of the bearing has been carried out for axial, radial unbalance loads. Stress distribution in the web region has been studied in detail. High cycle fatigue life margins are estimated using Goodman diagram. The squirrel cage web dimensions and fillet radius are modified to improve HCF life requirements. The operating stresses in the squirrel cage are reduced while meeting the stiffness and HCF life requirements of the component.

High cycle fatigue and fracture behaviors of CrMoV/NiCrMoV dissimilar rotor welded joint at 280 °C

2020 ◽  
Vol 786 ◽  
pp. 139473
Author(s):  
Wen-Ke Wang ◽  
Yan Liu ◽  
Yang Guo ◽  
Zhen-Zhen Xu ◽  
Jie Zhong ◽  
...  
Keyword(s):  
High Cycle Fatigue ◽  
Welded Joint ◽  
Cycle Fatigue ◽  
Fracture Behaviors ◽  
Fatigue And Fracture

High cycle fatigue and fracture behavior of Ti-5Al-5Mo-5V-3Cr alloy with BASCA and double aging treatments

2016 ◽  
Vol 658 ◽  
pp. 203-209 ◽  
Author(s):  
Leonardo Contri Campanelli ◽  
Paulo Sergio Carvalho Pereira da Silva ◽  
Claudemiro Bolfarini
Keyword(s):  
Fracture Behavior ◽  
High Cycle Fatigue ◽  
Cycle Fatigue ◽  
Double Aging ◽  
Fatigue And Fracture

PSBs and Non-Propagation of Small Surface and Interior Cracks in Polycrystalline Copper

2013 ◽  
Vol 592-593 ◽  
pp. 777-780 ◽  
Author(s):  
Stefanie E. Stanzl-Tschegg ◽  
Bernd M. Schönbauer
Keyword(s):  
High Cycle Fatigue ◽  
Fatigue Loading ◽  
Cycle Fatigue ◽  
Lower Stress ◽  
Small Surface ◽  
Loading Method ◽  
Very High Cycle Fatigue ◽  
Small Cracks ◽  
Number Of Cycles ◽  
Very High

PSB formation and its relevance for an eventual fatigue limit of polycrystalline electrolytic copper was studied in the very-high cycle fatigue regime with the ultrasound fatigue loading method. PSBs are formed at much lower stress/strain amplitudes than reported in earlier literature, if a high enough number of cycles is applied. Fatigue fracture takes place at approximately 50% higher amplitudes than needed for PSB formation, which is likewise in contrast to former literature results. Non-propagation of small cracks, originating from intrusions or PSB-induced non-propagating grain-boundary cracks are made responsible for this different material response.

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