Experimental investigation on fatigue of blade specimen subjected to resonance and effect of a damping hard coating treatment

Chen, Yugang; Zhu, Qingyu; Zhai, Jingyu

doi:10.1007/s11771-021-4614-0

Cited by 14 publications

(6 citation statements)

References 24 publications

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“…No significant differences were observed in the damping ratios of the blade models at their respective modes. High damping ratios are always desired to dissipate vibration energy and to consequently reduce the vibratory stresses, hence ultimately extending the lifetime of turbine blades by reducing the severity of HCF [39].…”

Section: Modementioning

confidence: 99%

Experimental and Numerical Vibration Analysis of Octet-Truss-Lattice-Based Gas Turbine Blades

Hussain

Ghopa

Singh

et al. 2022

Metals

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This paper aims to investigate the utilization of octet truss lattice structures in gas turbine blades to achieve weight reduction and improvement in vibration characteristics, which are desired for turbine blades to improve the efficiency and load capacity of turbines. A solid blade model using NACA 23012 airfoil was designed as reference. Three lattice-based blades were designed and manufactured via additive manufacturing by replacing the internal volume of solid blades with octet truss unit cells of variable strut thickness. Experimental and numerical vibration analyses were performed on the blades to establish their suitability for potential use in turbine blades. A maximum weight reduction of 24.91% was achieved. The natural frequencies of lattice blades were higher than those of solid blades. A stress reduction up to 38.6% and deformation reduction of up to 21.5% compared with solid blades were also observed. Both experimental and numerical results showed good agreement with a maximum difference of 3.94% in natural frequencies. Therefore, apart from being lightweight, octet-truss-lattice-based blades have excellent vibration characteristics and low stress levels, thereby making these blades ideal for enhancing the efficiency and durability of gas turbines.

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Section: Modementioning

confidence: 99%

Experimental and Numerical Vibration Analysis of Octet-Truss-Lattice-Based Gas Turbine Blades

Hussain

Ghopa

Singh

et al. 2022

Metals

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“…The application of hard coatings in the existing literature mostly focuses on simplifying coated discs [5][6][7][8][9][10][11][12][13][14][15], straight blades [16][17][18][19][20][21], plates [22][23][24][25][26], thin shells [27][28][29][30], and disk drums [31]. Yan et al [5] proposed using virtual layers to simulate changes in coating thickness and analyzed the impact of coating thickness on the natural frequency and forced response of actual disks.…”

Section: Introductionmentioning

confidence: 99%

Vibration Analysis and Damping Effect of Blade-Hard Coating Composite Structure Based on Base Excitation

et al. 2023

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Hard coatings are widely employed on blades to enhance impact resistance and mitigate fatigue failure caused by vibration. While previous studies have focused on the dynamic characteristics of beams and plates, research on real blades remains limited. Specifically, there is a lack of investigation into the dynamic characteristics of hard-coated blades under base excitation. In this paper, the finite element model (FEM) of blade-hard coating (BHC) composite structure is established based on finite element methods in which the hard coating (HC) material and the substrate are considered as the isotropic material. Harmonic response analysis is conducted to calculate the resonance amplitude of the composite under base excitation. Numerical simulations and experimental tests are performed to examine the effects of various HC parameters, including energy storage modulus, loss factors, coating thickness, and coating positions, on the dynamic characteristics and vibration reduction of the hard-coated blade composite structures. The results indicate that the difference in natural frequency and modal loss factor of blades increases with higher storage modulus and HC thickness. Moreover, the vibration response of the BHC decreases with higher storage modulus, loss factor, and coating thickness of the HC material. Blades with a complete coating exhibit superior damping effects compared to other coating distributions. These findings are significant for establishing accurate dynamic models of HC composite structures, assessing the effectiveness of HC vibration suppression, and guiding the selection and preparation of HC materials.

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“…There was a lot of research on the resonance frequencies of blades. These were mainly experimental studies [ 12 , 13 , 14 ] in which the blade was permanently mounted on the head of the device inducing the resonance state. The tests concerned both ordinary rotor blades [ 13 , 14 ] and those with special protective coatings [ 12 ].…”

Section: Introductionmentioning

confidence: 99%

“…These were mainly experimental studies [ 12 , 13 , 14 ] in which the blade was permanently mounted on the head of the device inducing the resonance state. The tests concerned both ordinary rotor blades [ 13 , 14 ] and those with special protective coatings [ 12 ]. Unfortunately, such studies do not provide information on how operating conditions will affect the resonance frequency.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Influence of Aerodynamic Loads on the Resonant Frequency of a Compressor Blade Made of EI-961 Alloy

et al. 2022

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The aim of this work was to numerically determine the influence of aerodynamic loads on the value of the resonant frequency of the compressor blade. The object of the research was the 1st stage compressor blade of the PZL-10W engine. As part of the research, analytical calculations of the resonance frequency were performed and compared with the literature ones (first, second, and third forms of forced vibrations). In the next step of the investigation, a computational model of the compressor stage (fluid domain and rotors) was built and FSI analysis was performed. This analysis was based on CFD modeling of the state of aerodynamic loads on the blade surfaces, and then these values were imported as external loads for the structural analysis, which was the basis for the modal analysis, in which the resonant frequency of the first three vibration modes was determined. As part of the analyzes, both the influence of aerodynamic loads and the rotational speed of the compressor rotor were verified. Thus, it was possible to evaluate the influence of both the rotational speed (and the arising centrifugal force) and the influence of the emerging aerodynamic load. The results obtained will allow for the assessment of the impact of the aforementioned operating conditions of the aircraft engine on the resonance frequency, which in turn may translate into the durability of critical components of the aircraft engine.

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Experimental investigation on fatigue of blade specimen subjected to resonance and effect of a damping hard coating treatment

Cited by 14 publications

References 24 publications

Experimental and Numerical Vibration Analysis of Octet-Truss-Lattice-Based Gas Turbine Blades

Experimental and Numerical Vibration Analysis of Octet-Truss-Lattice-Based Gas Turbine Blades

Vibration Analysis and Damping Effect of Blade-Hard Coating Composite Structure Based on Base Excitation

Numerical Investigation of the Influence of Aerodynamic Loads on the Resonant Frequency of a Compressor Blade Made of EI-961 Alloy

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