The growth of cracks in Ti–6Al–4V plate under combined high and low cycle fatigue

Powell, B. E.; Hawkyard, M.; Grabowski, L.

doi:10.1016/s0142-1123(97)00016-9

Cited by 24 publications

(9 citation statements)

References 12 publications

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“…This highlights the importance of using FSI simulations to obtain realistic HCF loading cycles on a rotating blade operating in the presence of upstream stators, and then accounting for the LCF load case that occurs simultaneously. The overall decrease in fatigue life is rep resentative of the HCF/LCF interaction that was observed by pre vious researchers [3,5,8,11,37] through their specimen testing, which is shown numerically in the present study for a rotating fan blade.…”

Section: Fatigue Interactionsupporting

confidence: 80%

“…The implications of the FSI results on the fatigue life are that when the mean stresses are similar for the two cases, the R-ratio has a greater effect than the mean stress, since the IGV-rotor was pre dicted to have a lower life than the IR case. The crack growth analysis was extended to analyze the HCF/LCF interaction, where previous researchers [1,3,4,11,37] implied that the interaction of the HCF and LCF loads can result in a reduction in fatigue life due to accelerated crack growth. The major findings from this study have shown that this is indeed the case when the HCF loads from the IGV-rotor interaction are combined with an LCF spec trum of the simplified flight cycle in the fatigue software nCode DesignLife.…”

Section: Discussionmentioning

confidence: 99%

“…The novel aspect of the present study is that the HCF/LCF interaction effect was simulated numerically by applying it to the case of a rotating, titanium fan blade, which is more representative of a real engine than the metal specimens studied previously [2][3][4]8]. This also provides the justification for future experimen tal studies to be performed on engine blades that could be sub jected to HCF and LCF loading and measurement of crack growth rates.…”

Section: Blade Aeroelasticitymentioning

confidence: 98%

“…Past research efforts have attempted to understand the behavior of specimens under combined HCF/LCF loading and observed that the structure does not respond to the combined loading as it would under individual HCF and LCF cycles [2][3][4], suggesting an interaction between the HCF and LCF cycles. This interaction and the mechanisms that contribute to it are not well understood, espe cially for complex cases such as rotating components in engines.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Aeromechanical Modeling of Rotating Fan Blades to Investigate High-Cycle and Low-Cycle Fatigue Interaction

Dhopade

Neely

2015

Journal of Engineering for Gas Turbines and Power

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Gas turbine engine components are subject to both low-cycle fatigue (LCF) and highcycle fatigue (HCF) loads. To improve engine reliability, durability and maintenance, it is necessary to understand the interaction of LCF and HCF in these components, which can adversely affect the overall life of the engine while they are occurring simultaneously during a flight cycle. A fully coupled aeromechanical fluid-structure interaction (FSI) analysis in conjunction with a fracture mechanics analysis was numerically performed to predict the effect of representative fluctuating loads on the fatigue life ofbliskfan blades. This was achieved by comparing an isolated rotor (IR) to a rotor in the presence of upstream inlet guide vanes (IGVs). A fracture mechanics analysis was used to combine the HCF loading spectrum with an LCF loading spectrum from a simplified engine flight cycle in order to determine the extent of the fatigue life reduction due to the interaction of the HCF and LCF loads occurring simultaneously. The results demonstrate the reduced fatigue life of the blades predicted by a combined loading of HCF and LCF cycles from a crack growth analysis, as compared to the effect of the individual cycles. In addition, the HCF aerodynamic forcing from the IGVs excited a higher natural frequency of vibration o f the rotor blade, which was shown to have a detrimental effect on the fatigue life. The findings suggest that FSI, blade-row interaction and HCF I LCF interaction are important considerations when predicting blade life at the design stage of the engine. The lack of available experimental data to validate this problem emphasizes the utility of a numerical approach to first examine the physics of the problem and second to help establish the need for these complex experiments.

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Section: Fatigue Interactionsupporting

confidence: 80%

Section: Discussionmentioning

confidence: 99%

Section: Blade Aeroelasticitymentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Aeromechanical Modeling of Rotating Fan Blades to Investigate High-Cycle and Low-Cycle Fatigue Interaction

Dhopade

Neely

2015

Journal of Engineering for Gas Turbines and Power

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“…The FE analysis was carried out to determine stress state in the joint along with J-integral to accurately account the complex state of mixed fracture mode loading. The growth of cracks in Ti-6Al-4V plate under combined high and low cycle fatigue was presented by Powell et al [12]. The description of fatigue crack growth under modes II, III, and II ?…”

Section: Introductionmentioning

confidence: 99%

An Investigation and 3D Crack Propagation Analysis of High Speed Flexible Coupling of Fighter Aircraft

Nagesh

Basha

Thakur

2015

J Fail. Anal. and Preven.

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The high speed flexible coupling (HSFC) transmits power from the aircraft engine gear box to the accessory gear box operating at high speed ranging from 10,000 to 18,000 rpm. The HSFC utilizes a series of thin annular, titanium alloy flexible plates, to accommodate larger parallel and axial misalignment that arises on the drive line. During ground testing, failure of flexible plate was observed. As a part of the failure analysis the extensive metallographic studies were done. This study showed that, failure was caused by the presence of Electron beam weld spatter on flexible plate, which was a crucial factor to the fatigue crack initiation phase. In order to complement the cause of failure, a 3D crack propagation simulation by FEA was done to predict the critical flaw size. This combined failure cause analysis approach has served as an efficient tool for optimized product development.

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Prediction of Fatigue Lives of MAR‐M247 LC Based on the Crack Closure Concept

2012

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Low cycle fatigue (LCF), high cycle fatigue (HCF), and combined LCF and HCF tests are carried out on MAR‐M247 LC at 650 °C in air environment. Under combined LCF and HCF loading, block striations form on the fracture surface which are used to complete an effective crack growth curve by using the linear summation model. Crack growth lives starting from equivalent initial flaw sizes are calculated by the crack closure code FASTRAN and compared with experimental fatigue lives. Under HCF loading, predicted and experimental fatigue lives agree well for lifetimes above 105 cycles. Lower lifetimes are overestimated indicating that the linear summation model is not valid for MAR‐M247 LC in this loading range. Interactions between the non‐crystallographic HCF crack growth and striated crack growth that is caused by the LCF loading are probably responsible for this behavior.

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The growth of cracks in Ti–6Al–4V plate under combined high and low cycle fatigue

Cited by 24 publications

References 12 publications

Aeromechanical Modeling of Rotating Fan Blades to Investigate High-Cycle and Low-Cycle Fatigue Interaction

Aeromechanical Modeling of Rotating Fan Blades to Investigate High-Cycle and Low-Cycle Fatigue Interaction

An Investigation and 3D Crack Propagation Analysis of High Speed Flexible Coupling of Fighter Aircraft

Prediction of Fatigue Lives of MAR‐M247 LC Based on the Crack Closure Concept

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