Design and testing of composite compressor blades with focus on the vibration behaviour

Wollmann, Tino; Modler, Niels; Dannemann, Martin; Langkamp, Αlbert; Nitschke, S.; Filippatos, Angelos

doi:10.1016/j.compositesa.2016.06.012

Cited by 34 publications

(15 citation statements)

References 19 publications

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“…The flow will separate and reverse from the last stage blade because of the effect of the diffuser of stator blades and the centrifugal force of rotor blades [1]. A large range of separation vortices is formed on the pressure surface, which causes a dramatic change of the blades dynamic stress [2][3][4], as well as blades vibration [5][6][7][8]. When the volume flow decreases to a certain extent, the last stage blades will go into the steam blast condition, which leads to a sudden temperature increase and the over-temperature deformation of the blade surface [9].…”

Section: Introductionmentioning

confidence: 99%

Analysis on flow separation characteristics of last stage blade in steam turbine under small volume flow condition

et al. 2019

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The inlet steam flow of steam turbine is obviously reduced and even in the state of small volume flow when the thermal power unit is involved in peak load operation, which greatly influences the safety of steam turbine. The last stage flow field of steam turbine under small volume flow condition is calculated by the CFX to study the formation, development, influencing range, and the variation rule of the flow separation vortex cores. The results show that the flow separation vortices appear near last stage blade at 30% of the rated volume flow. With the decrease of volume flow, the flow separation vortices gradually spread to the root of blade. When the volume flow decreases to 8% of the rated volume flow, the flow separation vortices almost occupy the whole blade. The position of the flow separation vortex cores shifts from 72.7% of the relative blade height to 49.1%. The results of this paper lay a foundation for the safety analysis of the last stage blade in the steam turbine under the small volume flow condition.

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Section: Introductionmentioning

confidence: 99%

Analysis on flow separation characteristics of last stage blade in steam turbine under small volume flow condition

et al. 2019

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“…However, the direction-dependent damping coefficients of anisotropic materials are not supported. To overcome this deficiency, a post-processing feature has been developed in Matlab , able to calculate the modal loss factor of anisotropic fibre-reinforced composite structures and is here also implemented [36,37]. The model includes the anisotropic material damping by an extension of the FEM using the strain energy concept [38,39].…”

Section: Development Of a Parametric Simulation Modelmentioning

confidence: 99%

Influence of Gradual Damage on the Structural Dynamic Behaviour of Composite Rotors: Simulation Assessment

2018

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Fibre-reinforced composite structures under complex loads exhibit gradual damage behaviour with degradation of effective mechanical properties and change of their structural dynamic behaviour. In case of composite rotors, this can lead to catastrophic failure if an eigenfrequency is met by the rotational speed. The description and simulation analysis of the gradual damage behaviour of composite rotors therefore provides the fundamentals for a first understanding of complex and partially-unpredicted structural phenomena. Therefore, a simulation tool is developed using a finite element model, which calculates the damage-dependent structural dynamic behaviour of selected composite rotors considering both damage initiation and in-plane damage evolution due to a combination of out-of-plane and in-plane loads. Damage initiation is determined using failure criteria, whereas the gradual damage evolution using a validated continuum damage mechanics model. Numerical results are compared with experimental results for rotor-typical stress states to assess the model quality, which could be later used for damage identification approaches.

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“…The development of new materials-such as composite materials-has paved the way for significant mass reduction in aerospace structural components [1]. The use of such materials is indeed increasingly common for aircraft structures and even aircraft engines as they are typically found in the fan stage [7,8], acoustic lining panels [9,10,11] as well as various components of the nacelle [12,13]. However, the use of composite materials within the hot sections of an aircraft engine remains a challenge for engineers due to extreme thermal conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

Nyssen

Tableau

Lavazec

et al. 2020

Journal of Sound and Vibration

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This work focuses on the experimental and numerical characterization of stress levels within a shroud segment made of ceramic matrix composite (CMC) material undergoing repeated blade contacts. The dedicated experimental setup consists in a rotating disk with three notched mock blades that impact the shroud segment as they rotate. The underplatform on which the shroud is fixed progressively gets closer to the blades, so that the abradable layer deposited onto the shroud is progressively worn out from a blade revolution to another. Four sensors, located under the shroud segment, are used to record forces during the experiments. Different blade/shroud relative positions are tested, in such a way that impacts may occur at distinct locations. In addition to the experimental tests, a numerical model is built based on both reduced order models of the blade and the shroud segment, in order to numerically predict the forces at the four sensors. This numerical model is first calibrated based on a single reference test case to retrieve the same force magnitude at each sensor. Then, the other tests are simulated using the calibrated model. Predicted contact forces are in good agreement with experimental data, which validates the numerical model. Finally, simulations are carried out considering engine-like conditions, which could not be reproduced using the experimental test bench. The influence of several parameters (radial velocity, impact location, number of blades in contact and angular speed) is analyzed in detail.

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Design and testing of composite compressor blades with focus on the vibration behaviour

Cited by 34 publications

References 19 publications

Analysis on flow separation characteristics of last stage blade in steam turbine under small volume flow condition

Analysis on flow separation characteristics of last stage blade in steam turbine under small volume flow condition

Influence of Gradual Damage on the Structural Dynamic Behaviour of Composite Rotors: Simulation Assessment

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

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