Remaining Life Assessment of Power Turbine Disks

Jin, Huitang; Lowden, P.; Pistor, Robert

doi:10.1115/gt2008-51010

Cited by 6 publications

(6 citation statements)

References 4 publications

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“…The parameters T * S1 , T * S2 , and k α are unmeasured parameters, which further will be referred as thermal boundary conditions; since this unmeasured parameters are the input data in Eqs. (1) and (3), it is necessary to develop mathematical models for their prediction. In the following section, the model developing methodology is explained.…”

Section: Turbine Blade Thermal and Stress Monitoring Modelsmentioning

confidence: 99%

“…The thermal-stress engine condition was calculated using Eqs. (1) and (2). The prediction of the turbine blade lifetime is a very complex process, which involves different factors; however, a conservative lifetime prediction will be enough to assess the impact that a new model developing methodology has on the accuracy of the lifetime prediction.…”

Section: Prediction Of the Thermal-stress Condition And Engine Lifetimementioning

confidence: 99%

“…Lifetime monitoring systems are an effective way to perform condition base maintenance of gas turbine engines [1][2][3]; this allows a better use of the available lifetime and improvement of the engine's reliability.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A New Approach for Model Developing to Estimate Unmeasured Parameters in an Engine Lifetime Monitoring System

Maravilla¹,

Yepifanov²

2019

Gas Turbines - Control, Diagnostics, Simulation, and Measurements [Working Title]

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Monitoring systems to predict the remaining lifetime of gas turbine engines are a major field of investigation, in particular, the monitoring systems that allow an online prediction. This chapter introduces and analyzes a new approach to develop mathematical models to estimate unmeasured parameters in an engine lifetime monitoring system; these models in contrast to previously developed models allow an on-line monitoring of unmeasured parameters, which are necessary to perform an on-line lifetime prediction. The blade of a high-pressure turbine (HPT) of a twospool free turbine power plant is the test case. Several candidate models are developed for each unmeasured parameter; the best models are selected by their accuracy and robustness using the instrumental and truncation error as criteria. Ten faulty engine conditions are considered to analyze the model robustness. Two methods for model developing are compared; the first method uses physics-based models (proposed in this chapter), and the second method develops the models using the similarity concept (reference methodology). The results of the comparison show that the physics-based models are more robust to engine faults and overall they deliver a significantly more accurate prediction of the engine lifetime.

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Section: Turbine Blade Thermal and Stress Monitoring Modelsmentioning

confidence: 99%

Section: Prediction Of the Thermal-stress Condition And Engine Lifetimementioning

confidence: 99%

See 1 more Smart Citation

A New Approach for Model Developing to Estimate Unmeasured Parameters in an Engine Lifetime Monitoring System

Maravilla¹,

Yepifanov²

2019

Gas Turbines - Control, Diagnostics, Simulation, and Measurements [Working Title]

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“…The turbine blades' thermal SC was assessed using expressions (1) and (2). The prediction of the lifetime of turbine blades is a very complex process in which a significant number of factors influence.…”

Section: Accuracy Analysis On Real Datamentioning

confidence: 99%

Improvement of turbine blade lifetime assessment by more accurate estimation of the thermal boundary conditions

Herrera

Yepifanov

Loboda

2017

Advances in Mechanical Engineering

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The known studies in the area of gas turbine lifetime prediction do not result in the algorithms for on-line engine monitoring. This article introduces and investigates a new method for developing ''light'' mathematical models to estimate static thermal boundary conditions for gas turbine hot elements. In contrast to the previous developments, these models allow on-line lifetime monitoring of such elements. The blade of the high-pressure turbine of a two-spool free turbine power plant was chosen as a test case. The models of blade boundary conditions were developed based on well-known thermodynamic relations and a steady-state nonlinear physics-based model of this engine. Many candidate models are analyzed in the article, and the best models are selected by their accuracy and robustness to engine faults using instrumental and truncation errors as criteria. The instrumentation errors are induced by measurement inaccuracy of gas path variables used. For the analysis of the model robustness, the truncation errors are computed. They appear when performance of an engine deviates from a baseline due to normal degradation of the engine and because of its faults. The gas path parameters under healthy and faulty engine health conditions are simulated by the thermodynamic model. These simulated quantities are used as the input data to perform the comparison of the candidate models. The final accuracy analysis shows that the proposed method improves the estimates of the thermal boundary conditions. As a result, prediction of an engine lifetime becomes significantly more accurate. The article also determines the positive effect of the compressor discharge temperature sensor. When it is installed in addition to a standard gas path measurement system, the accuracy of the measurement-based lifetime prediction grows drastically.

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“…Monitoring systems of the engine lifetime are an effective method of implementing condition-based maintenance of a gas turbine engine [1][2]. Such systems help to fully use the assigned resource of the engine as well as increase its reliability.…”

mentioning

confidence: 99%

Steady and Transient Thermal State of Turbine Disk Estimation for Life Time Monitoring

Martseniuk

2020

Transactions on Aerospace Research

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In connection with increasing intensification of the working process in a gas turbine engine and increasing requirements for economy, the problem of defining and monitoring the main parts lifetime is becoming more vital. Modern algorithms of the monitoring systems are based on taking into account the levels of part temperature and total equivalent stress throughout the flight cycle. Thermal and stress-strain states of the critical zones of the main parts are determined on the basis of information received from the sensors installed in the engine gas path. Turbine disks are located in the internal cavities of the engine and are cooled by air from the compressor. However, in some designs, the disk cavity can be separated from the place of cooling air bleed by several stages of non-contact labyrinth seals, which will lead to some delay in changing the parameters of the cooling air flow when changing the engine operating mode. It has been observed that if this situation is not taken into account, it can lead to significant errors (more than 40%) in determining the lifetime for the peripheral zone of the disk. At the same time, this error is minimal for the hub and the middle zone of the disk, and the existing monitoring algorithms can be used.

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Remaining Life Assessment of Power Turbine Disks

Cited by 6 publications

References 4 publications

A New Approach for Model Developing to Estimate Unmeasured Parameters in an Engine Lifetime Monitoring System

A New Approach for Model Developing to Estimate Unmeasured Parameters in an Engine Lifetime Monitoring System

Improvement of turbine blade lifetime assessment by more accurate estimation of the thermal boundary conditions

Steady and Transient Thermal State of Turbine Disk Estimation for Life Time Monitoring

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