Implications of engine deterioration for creep life

Naeem, Muhammad; Singh, Riti; Probert, Douglas

doi:10.1016/s0306-2619(98)00028-2

Cited by 23 publications

(14 citation statements)

References 10 publications

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“…plastic deformation, crack initiation and propagation, suffered by a component. If the same amount of damage is done to a component at any stress level as a result of a given fraction of the number of cycles required to cause failure, then this may be described in more a general form (according to Minor's rule (15) ) by or the cumulative damage is given as When the Larson-Miller parameter, as expressed by Equation 1, is applied to determine the creep life, the above Equation can be rewritten to indicate the time to failure of each segment in a mission as described by Equation (2). Then, the mission creep life is calculated through use of Minor's rule for linear damage-accumulation, viz,…”

Section: Cummulation Of Creep Damagementioning

confidence: 99%

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Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption

Naeem

2006

Aeronaut. j.

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Some in-service deterioration in any mechanical device, such as an aero-engine, is inevitable. As a result of experiencing a deterioration of efficiency and/or mass flow, an aero-engine will automatically adjust to a different set of operating characteristics; thereby frequently resulting in changes of rpm and/or turbine entry temperature in order to provide the same thrust. Rises in the turbine entry-temperatures and the high-pressure turbine’s rotational speed result in greater rates of creep and fatigue damage being incurred by the hot-end components and thereby higher engine’s life cycle costs. Possessing a better knowledge of the effects of engine deterioration upon the aircraft’s performance, as well as fuel and life usages, helps the users to take wiser management decisions and hence achieve improved engine utilisation. For a military aircraft, using a computer performance simulation, the consequences of low-pressure (LP) compressor’s deterioration upon an aero-engine high-pressure (HP) turbine blade’s life-consumption have been predicted.

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Section: Cummulation Of Creep Damagementioning

confidence: 99%

“…The relationship between applied stress and the component's remaining life is logarithmic, and that mechanical stresses imposed upon the engine vary as the square of its rotational speed. Therefore, a modest increase in the range of throttle movement can have a major adverse impact on the fatigue-life consumption (15) .…”

Section: Cumulative-damage Lawsmentioning

confidence: 99%

Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption

Naeem

2006

Aeronaut. j.

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“…The gas turbines are mainly operated on a safe‐life principle at present, whereby the engine is withdrawn from service for maintenance well before failure is likely to ensue . The description of experiments for full‐scale turbine blades under the mechanical loading of LCF and creep is limited at present .…”

Section: Introductionmentioning

confidence: 99%

“…The gas turbines are mainly operated on a safe-life principle at present, whereby the engine is withdrawn from service for maintenance well before failure is likely to ensue. 18 The description of experiments for full-scale turbine blades under the mechanical loading of LCF and creep is limited at present. 19,20 Yan 19 proposed an experimental method to conducted creep fatigue of directionally solidified turbine blades with a uniform temperature distribution of the critical section.…”

mentioning

confidence: 99%

Accelerated LCF‐creep experimental methodology for durability life evaluation of turbine blade

Shi

Yang

et al. 2018

Fatigue Fract Eng Mat Struct

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This paper proposes an accelerated low cycle fatigue (LCF)‐creep experimental methodology in laboratory to investigate the durability life of turbine blades. A typical mission profile of the turbine blade was obtained by means of rain flow counting method, considering both the actual flight condition and ground test data. Finite element analysis (FEA) was conducted to obtain the stress and temperature fields of turbine blade. A test system was constructed to conduct LCF‐creep experiments of turbine blades, simulating the stress and temperature distributions of critical section properly. LCF‐creep experiments of full‐scale turbine blades were performed under a trapezoidal loading spectrum. Experiment results showed that the durability life of turbine blade based on numerical method was longer than that based on this experimental methodology, even an order of magnitude. Furthermore, this experimental methodology helped to extend the service life of this blade safely, and its validity was verified in actual service condition.

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“…The valve failures are caused by leakage in membrane or line system, selenoid valve stucked, contactor and relay broken and fail in air and electric power supply [5]. Therefore, the preventive maintanance is required to overcome hidden failure in the valve by perform optimization of preventive maintenance [6,7].…”

Section: Introductionmentioning

confidence: 99%

Method Of Valve Preventive Maintenance Via Additional Overview On Pos For Decreasing Failure Risk At Starting And Change Over Fuel Gas To Fuel Oil In Block 1 And 2 Gas Turbine GT13E2 PT. PJB UP Muara Tawar

M¹,

Sugianto²,

Ihsan³

et al. 2017

IOSR JMCE

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Block 1 and 2 Combined Cycle Power Plant (CCPP) Muara Tawar have 5 units gas turbine can be operated by using fuel gas. Due to limitation of fuel gas from gas company. Several gas turbine are operated using High Speed Diesel fuel (HSD) to fulfil load demand. The equipment that used for fuel gas system must have high realibility to serve in dual fuel system neither operated using fuel oil or gas without unit trip. In actual, there are several disturbances occur during change over from gas to oil, even when the plant operated using fuel oil. From the data of failure causes, one of the failure causes is valve failure. By considering the availbility of plant, in term of possibility to modify instrumentation and control system, gas turbine 1.3 was choosen as object of the study. Additional indicator in HMI can be described as follows additional pressure switch attribute at EDS-P3 using symbol K, upload program to EPROM at card 70BK06 as communication card, and the cycle time less than 1 second in both valve open or close. It indicate valve system under good condition or no maintenance action is required. Valve maintenance at gas turbine ALSTOM 13E2 in Block 1 and 2 CCPP Muara Tawar can be done by additional indicator of pressure switch and aux relay contact as feedback signal on POS 30. Therefore, no disturbances in valve system and gas turbine performance increases.

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Implications of engine deterioration for creep life

Cited by 23 publications

References 10 publications

Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption

Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption

Accelerated LCF‐creep experimental methodology for durability life evaluation of turbine blade

Method Of Valve Preventive Maintenance Via Additional Overview On Pos For Decreasing Failure Risk At Starting And Change Over Fuel Gas To Fuel Oil In Block 1 And 2 Gas Turbine GT13E2 PT. PJB UP Muara Tawar

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