Fatigue analysis of compressor blade with simulated foreign object damage

Witek, Lucjan; Bednarz, Arkadiusz; Stachowicz, Feliks

doi:10.1016/j.engfailanal.2015.09.002

Cited by 24 publications

(26 citation statements)

References 19 publications

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“…The blade used in the experimental test the notch like in works [6,7]. In every case the foot of the blade is equal to 3 mm displacement is equal to A = 1.8 mm.…”

Section: Resultsmentioning

confidence: 99%

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Temperature distribution as a method of measuring crack length in fatigue tests of compressor blade

2016

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ZESZYTY NAUKOWE POLITECHNIKI RZESZOWSKIEJ 293, Mechanika 88RUTMech, t. XXXIII, z. 88 (1/16), styczeń-marzec 2016, s. In this paper the experimental results of fatigue analysis of the compressor blade were presented. Temperature distribution as a method of measuring crack length was considered. The blade with the V-notch (which simulates the foreign object damage) was entered into transverse vibration under resonance condition. During investigations both the amplitude of the blade tip displacement and also the crack length were monitored. At the same the pictures of time temperature distribution were taken. In the first part of the work the amplitude-frequency diagrams were obtained for different sizes of cracks. In the investigation, both a number of load cycles to crack initiation and dynamics of the crack growth in the compressor blade subjected to vibrations were determined. An additional original result of the work is the comparison of optically measured crack length and the dimension of the crack length taken from the picture. An important application will be the benefits of the method of measuring the length of the slot with a temperature distribution image. The results presented in this paper have theoretical and practical significance.

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“…The blade used in the experimental test the notch like in works [6,7]. In every case the foot of the blade is equal to 3 mm displacement is equal to A = 1.8 mm.…”

Section: Resultsmentioning

confidence: 99%

“…The results of the tests were compared with the FEM analysis. An overview of attempts to study the fatigue of the compressor blades on the inductor vibration was presented in [6,7]. Methodology of works [6,7] is the basis of the analysis in this paper.…”

Section: Introductionmentioning

confidence: 99%

Temperature distribution as a method of measuring crack length in fatigue tests of compressor blade

2016

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“…∆ -2 x the stress amplitude, MPa, K′ -cyclic strength coefficient, MPa, n′ -cyclic strain hardening exponent. In this work, the first stage compressor blade of the aircraft engine, made of EI-961 alloy [14,15], were investigated. Fatigue material data of EI-961 steel (0.1-0.16% C, max 0.6% Si, max 0.6% Mn, 1.5-1.8% Ni, max 0.03% S, max 0.03% P, 10.5-12% Cr, 0.35-0.5 Mo, 1.6-2% W, 0.18-0.3% V) has been estimated based on the following mechanical properties: -modulus of elasticity E = 200 GPa, -Poisson ratio γ = 0.3, -ultimate tensile strength = 1200 MPa, -failure stain ε f = 0.12.…”

Section: Cyclic Hardening Models and Materials Data To ε-N Analysismentioning

confidence: 99%

“…This analysis was conducted for the linear-elastic model (based only on Young modulus and Poisson ratio). The amplitude of the displacement during the resonance was equal to EL = 1.8 mm (the same as in mentioned earlier papers [14,15]).…”

Section: Numerical Fatigue Analysismentioning

confidence: 99%

Influence of the Cyclic Hardening Model on the Results of the Numerical Analysis of Fatigue Life on Example of the Compressor Blade

Bednarz

2019

Journal of KONES

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The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.

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“…The joint between the turbine blade and the disc usually represents the most critical area from the point of view of the static and fatigue strength. The loads associated with these regions are mainly the centrifugal forces and the thermal stresses [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Thermo-mechanical stress analysis of the turbine of helicopter engine

Witek¹,

Stachowicz²

2016

ZN PRz Mechanika

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In this paper the results of the numerical stress analysis of the power turbine of helicopter engine were presented. In order to solve the problem, the nonlinear finite element method was used. The numerical models of both the blade and the disc segment were made using the MSC-Patran program. In the analysis the thermal load resulting from non-uniform temperature field was defined. The centrifugal force resulting from the rotation of the engine rotor was also considered. The cyclic symmetry boundary condition of the disc segment was used to decrease the size of the numerical task. The model of the turbine material was defined as linear-elastic. The modulus of elasticity and the thermal expansion coefficient of the disc and the blade material were considered as temperature dependent. As a result of performed computations, the stress distributions for the turbine subjected to both the thermal and the mechanical loads were determined.

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Fatigue analysis of compressor blade with simulated foreign object damage

Cited by 24 publications

References 19 publications

Temperature distribution as a method of measuring crack length in fatigue tests of compressor blade

Temperature distribution as a method of measuring crack length in fatigue tests of compressor blade

Influence of the Cyclic Hardening Model on the Results of the Numerical Analysis of Fatigue Life on Example of the Compressor Blade

Thermo-mechanical stress analysis of the turbine of helicopter engine

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