Failure of a low pressure turbine rotor blade of an aeroengine

Bhaumik, SK; Sujata, M; Venkataswamy, MA; Parameswara, MA

doi:10.1016/j.engfailanal.2005.12.002

Cited by 37 publications

(14 citation statements)

References 6 publications

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“…The fracture of turbine blades often occurs during service, which seriously threatens the safety of aero-engine. 3 Consequently, failure assessment of turbine blades should be paid more attention, and it is necessary to assess the service damage of turbine blades during blade overhaul in order to improve service reliability and economic performance of aero-engine. Meanwhile, the temperature and stresswithstanding capabilities of materials are required to keep advancing.…”

Section: Introductionmentioning

confidence: 99%

Failure assessment of the first stage high‐pressure turbine blades in an aero‐engine turbine

Shi

Wang

Yang

et al. 2017

Fatigue Fract Eng Mat Struct

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In this paper, microscopic analysis and fatigue experiment were conducted to detect the damage degree of turbine blades after a 600 h service and determine the reliable service time. First, several service blades were cut into slices on different cross sections and microscopically examined. It is found that the γ′ phase particles are slightly coarsened and the γ′ phase parameters change with temperature and stress distribution. Then, fatigue test was conducted on service blades simulating the real working condition. The test result shows that the blades after a 600 h service would serve for 3596 h more until failure during actual flight. The ultimate fracture is mainly caused by the interaction of fatigue, creep and oxidation. Besides, the γ′ phase parameters change obviously compared with service blade without fatigue test. It indicates that the γ′ phase parameters could be used to evaluate the microdamage of service blades, which has great significance for service reliability of the turbine machinery.

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Section: Introductionmentioning

confidence: 99%

Failure assessment of the first stage high‐pressure turbine blades in an aero‐engine turbine

Shi

Wang

Yang

et al. 2017

Fatigue Fract Eng Mat Struct

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“…During aero-engine working, the compressor blades easily occur fatigue failure under complex loads, which is the main failure form for the blade [1][2][3][4]. Once the blade failure, a catastrophic accident will be caused in the engine and even the aircraft [5,6].…”

Section: Introductionmentioning

confidence: 99%

Study on Blade Fatigue Life of Rotating Power Machinery

Kou

Zhang

2016

MATEC Web Conf.

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Abstract. The linear damage model (LDM) is widely applied in engineering calculation, but it does not consider the relationship between damage variable and load parameters. Therefore, the life prediction based on LDM is not satisfied for the aero-engine blades. Besides, it easily brings about error in predicting fatigue life by common nonlinear damage model which neglect the influence of torsional stress. Hence, a modified nonlinear continuum damage model (CDM) is put forward based on Chaboche nonlinear damage model in this research. And to determine the damage and fatigue life of TC4 material used in aero-engine blades, axial tension and compression fatigue test is conducted. Compared with LDM results, the fatigue life prediction results of the modified CDM in this work show a good agreement with the tests data. So the correctness of the modified model is verified. Finally, the fatigue life of a certain aero-engine high pressure compressor blade is predicted by the modified nonlinear continuum damage model.

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“…However, reduction in tip clearance may result in blade rub against the casing leading to catastrophic failures [2][3][4]. Blade rub against the casing may also occur because of blade growth during operation.…”

Section: Introductionmentioning

confidence: 99%

Failure Analysis of an Air Turbine Starter

Biswas

Ganeshachar

Sridhar

et al. 2010

J Fail. Anal. and Preven.

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Air turbine starters (ATS) are used for the ground start of aircraft engines. This case history describes the failure of an ATS that occurred while starting a developmental gas turbine engine. Fractographic features indicated that few blades of the turbine rotor disc failed in a progressive mode while the remaining blades of the rotor disc indicated failure by overload. The rotor shaft also exhibited features of sudden overload. Analysis of the previous records revealed the observation of sparks developing while the starter was in operation. This indicated possibility of blade tip rubbing which resulted in fatigue crack initiation at the blade root leading to failure.

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Failure of a low pressure turbine rotor blade of an aeroengine

Cited by 37 publications

References 6 publications

Failure assessment of the first stage high‐pressure turbine blades in an aero‐engine turbine

Failure assessment of the first stage high‐pressure turbine blades in an aero‐engine turbine

Study on Blade Fatigue Life of Rotating Power Machinery

Failure Analysis of an Air Turbine Starter

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