Study on the fatigue life and damage accumulation of a compressor blade based on a modified nonlinear damage model

Fu, Xing; Zhang, J.; Lin, Jiewei

doi:10.1111/ffe.12753

Cited by 17 publications

(12 citation statements)

References 32 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1 shows photographs indicating the geometric parameters of the blades. Based on the engine's commissioning test data and the aircraft's operating cycle, six typical operating conditions were investigated [15]: take-off, maximum continuous, cruise, descending, flight idle, and ground idle. Table 1 shows the rotational speeds corresponding to these operating conditions.…”

Section: Basic Parameters Of Blade and Operating Parameters Of Compressormentioning

confidence: 99%

See 1 more Smart Citation

Vibration characteristics of axial compressor blade under complex loads

Liu¹,

Fu²,

Zhang³

et al. 2022

J. vibroeng.

View full text Add to dashboard Cite

In this study, 3D models of a compressor blade for an aero engine with three different levels of surface accuracy (with 4, 6 and 10 section profiles) were obtained via reverse engineering by fitting point-cloud data. Then, finite element and flow-field models of the blade were established and validated. The vibration characteristics of the blade under typical operating conditions were analyzed by considering the interaction between the aerodynamic load by airflow and the centrifugal load by blade rotating. The results showed that, under complex centrifugal and aerodynamic loads, the three blade models differed significantly in their high-order dynamic frequencies, and the modal frequencies that were dominated by a torsional mode of vibration were sensitive to the aerodynamic load. Hence, considering both the aerodynamic excitation and the centrifugal load increased the accuracy of the numerical computation of the blade vibration characteristics. Moreover, a comparison of the computational results from the three blade models showed that models B6 and B10 differed only insignificantly, and B6 decreased the complexity of the modeling process while satisfying the required computational accuracy. Thus, model B6 is the best option for engineering analysis and computation.

show abstract

Section: Basic Parameters Of Blade and Operating Parameters Of Compressormentioning

confidence: 99%

“…7). The compressor blade was made from a titanium alloy Ti-6Al-4V, whose major mechanical properties are [15]: density 𝜌 = 4440 kg/m 3 ; modulus of elasticity 𝐸 = 1.07×10 5 MPa; and Poisson's ratio 𝜇 = 0.3.…”

Section: Fe Modeling Of the Blade And Model Verificationmentioning

confidence: 99%

Vibration characteristics of axial compressor blade under complex loads

Liu¹,

Fu²,

Zhang³

et al. 2022

J. vibroeng.

View full text Add to dashboard Cite

show abstract

“…Generally, the working conditions of an aeroengine are divided into some stages, such as take-off, cruise, approach, and landing, with different rotation speeds, which lead to a change of the aerodynamic load and vibration characteristics. Hence, the engine flight cycle was divided into six typical operating conditions according to the aeroengine test-drive data [37], its rotation speeds are shown in Table 2. With the CFD calculation models, the internal flow field of the compressor was solved under six typical speeds.…”

Section: Aerodynamic Loads Analysismentioning

confidence: 99%

Numerical Study on Vibration Response and Fatigue Damage of Axial Compressor Blade Considering Aerodynamic Excitation

Lin

et al. 2021

Metals

Self Cite

View full text Add to dashboard Cite

Axial compressor blades with a deformed initial torsion angle caused by aerodynamic excitation resonated at the working speed and changed the rule of fatigue damage accumulation. The fatigue life of a blade has a prediction error, even causing serious flight accidents if the effect of torque causing damage deterioration of the blade fatigue life is neglected. Therefore, in this paper, a uniaxial non-linear fatigue damage model was modified using the equivalent stress with torsional shear stress, and the proposed fatigue model including the torsional moment was used to study the compressor blade fatigue life. Then, the blade numerical simulation model was established to calculate the vibration characteristics under complex loads of airflow excitation and a rotating centrifugal force. Finally, the blade fatigue life under actual working conditions was predicted using the modified fatigue model. The results show that the interaction between centrifugal and aerodynamic loads affects the natural frequency, as the frequencies in modes dominated by bending deformation decreased whereas those dominated by torsional deformation increased. Furthermore, the blade root of the suction surface showed stress concentration, but there is an obvious difference of stress distribution and amplitude between the normal stress and the equivalent stress including torsional shear stress. The additional consideration of the torsional shear stress decreased the predicted fatigue life by 4.5%. The damage accumulation rate changes with the loading cycle, and it accelerates fast for the last 25% of the cycle, when the blade fracture may occur at any time. Thus, the aerodynamic excitation increased the safety factor of blade fatigue life prediction.

show abstract

“…The blade is made of Ti-6Al-4V alloy with density of 4440 kg/m 3 , Young’s modulus of 107 GPa, ultimate tensile strength of 1005 MPa and Poisson’s ratio of 0.34, respectively [17]. In our previous work [45], the fatigue limits of the blade were obtained approximately 345 MPa under R = −1 and 605 MPa under R = 0.1, respectively.…”

Section: Life Prediction Of a Compressor Bladementioning

confidence: 99%

Study on Damage Accumulation and Life Prediction with Loads below Fatigue Limit Based on a Modified Nonlinear Model

Zhang

Lin

et al. 2018

Materials

View full text Add to dashboard Cite

Most fatigue theories neglect the loads below fatigue limit in damage accumulation, which leads to inconsistency between the predicted and the actual fatigue lives. In this study, a novel damage model is proposed to take into account the loads below fatigue limit from two aspects: the strengthening effect and the cumulative damage. The strengthening effect is introduced by an exponential function and the cumulative damage is calculated by fuzzy method with membership functions (MFs). The proposed model is verified against the experimental data under variable amplitude loading conditions. It is found the modified model with Cauchy MF significantly reduces the relative error of predicted life from 35.18% (linear model) and 16.09% (original Chaboche model) to 8.38% (proposed model). As a case study, the proposed damage model is implemented to evaluate the service life of a compressor blade under variable amplitude loading spectrum containing small loads below the fatigue limit.

show abstract

Study on the fatigue life and damage accumulation of a compressor blade based on a modified nonlinear damage model

Cited by 17 publications

References 32 publications

Vibration characteristics of axial compressor blade under complex loads

Vibration characteristics of axial compressor blade under complex loads

Numerical Study on Vibration Response and Fatigue Damage of Axial Compressor Blade Considering Aerodynamic Excitation

Study on Damage Accumulation and Life Prediction with Loads below Fatigue Limit Based on a Modified Nonlinear Model

Contact Info

Product

Resources

About