Application of Adaptive GPA to an Industrial Gas Turbine Using Field Data

2019 ◽  
Author(s):  
Ericcson Ramadhan ◽  
Yi-Guang Li ◽  
Deplian Maherdianta
Keyword(s):  
Performance Management ◽  
Gas Turbine ◽  
Performance Status ◽  
Engine Performance ◽  
Health Condition ◽  
Diagnostic Process ◽  
Component Level ◽  
Turbine Component ◽  
The Difference ◽  
Industrial Gas Turbine

Abstract The gas turbine inspection activities provided by the manufacturers and user maintenance scheme may be different from each other. To accommodate the difference, performing engine diagnostic as a condition-based monitoring technique is necessary to support Asset Performance Management (APM) adopted by the gas turbine users to improve the scheme. This paper provides an application of a novel Adaptive Gas Path Analysis (Adaptive GPA) to diagnose performance and health condition of a GE industrial gas turbine MS5001PA operated by PT Pupuk Kaltim (PKT). In the application, an engine thermodynamic model is constructed, adapted, and validated on the actual engine performance based on its gas path measurements. To estimate the health condition from the degraded engine data, two steps are applied in the Adaptive GPA diagnostic process. The first step is the estimation of degraded engine performance status and the second step is the prediction of engine health status at the gas turbine component level. Adaptive GPA results show that satisfactory predictions of the engine degradation have been achieved. In other words, the compressor has been predicted 5.56% degradation in flow capacity and 4.26% degradation in efficiency respectively, which is an indication of compressor fouling. Combining the diagnostic results, manufacturer’s recommendations, and user maintenance strategy, it is relatively safe and allowable to increase the maintenance inspection interval from 12,000 to 16,000 hours. Therefore, the adaptive GPA is proven to be beneficial to support condition-based maintenance decisions.

Gas Turbine Performance and Health Status Estimation Using Adaptive Gas Path Analysis

2010 ◽  
Vol 132 (4) ◽  
Author(s):  
Y. G. Li
Keyword(s):  
Health Status ◽  
Path Analysis ◽  
Gas Turbine ◽  
Performance Status ◽  
Engine Performance ◽  
Test Cases ◽  
Airflow Rate ◽  
Component Level ◽  
Turbine Engine ◽  
Time Required

In gas turbine operations, engine performance and health status are very important information for engine operators. Such engine performance is normally represented by engine airflow rate, compressor pressure ratios, compressor isentropic efficiencies, turbine entry temperature, turbine isentropic efficiencies, etc., while the engine health status is represented by compressor and turbine efficiency indices and flow capacity indices. However, these crucial performance and health information cannot be directly measured and therefore are not easily available. In this research, a novel Adaptive Gas Path Analysis (Adaptive GPA) approach has been developed to estimate actual engine performance and gas path component health status by using gas path measurements, such as gas path pressures, temperatures, shaft rotational speeds, fuel flow rate, etc. Two steps are included in the Adaptive GPA approach, the first step is the estimation of degraded engine performance status by a novel application of a performance adaptation method, and the second step is the estimation of engine health status at component level by using a new diagnostic method introduced in this paper, based on the information obtained in the first step. The developed Adaptive GPA approach has been tested in four test cases where the performance and degradation of a model gas turbine engine similar to Rolls-Royce aero engine Avon-300 have been analyzed. The case studies have shown that the developed novel linear and nonlinear Adaptive GPA approaches can accurately and quickly estimate the degraded engine performance and predict the degradation of major engine gas path components with the existence of measurement noise. The test cases have also shown that the calculation time required by the approach is short enough for its potential online applications.

scholarly journals Gas Turbine Component Fault Identification by Means of Adaptive Performance Modeling

1990 ◽  
Author(s):  
A. Stamatis ◽  
K. Mathioudakis ◽  
M. Smith ◽  
K. Papailiou
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Health Condition ◽  
Adaptive Performance ◽  
Test Vehicle ◽  
Turbine Performance ◽  
Turbine Component ◽  
Diagnostic Applications ◽  
Component Faults ◽  
Adaptive Modelling

The method of adaptive modelling of Gas Turbine performance, proposed in the past by the present authors, is finding a new application in component fault detection. An appropriate choice of component characteristic parameters gives the possibility of characterizing their “health condition”, by appropriate processing of selected measured quantities according to the principles of adaptive modelling. Both a general deterioration of components and identification (kind, location) of component faults can be achieved. The proposed methodology is presented together with an experimental investigation of Gas Turbine faults. A commercial Gas Turbine has been used as a test vehicle and various kinds of faults have been implanted. An analysis of the results of the investigation provides information about the influence of the occurrence of such faults on engine performance. On the other hand, these data provide a basis for demonstrating the capabilities of the above mentioned methodology, as a powerful tool for diagnostic applications.

Gas Turbine Performance and Health Status Estimation Using Adaptive Gas Path Analysis

2009 ◽  
Author(s):  
Y. G. Li
Keyword(s):  
Health Status ◽  
Path Analysis ◽  
Gas Turbine ◽  
Flow Rate ◽  
Performance Status ◽  
Engine Performance ◽  
Test Cases ◽  
Component Level ◽  
Turbine Engine ◽  
Time Required

In gas turbine operation, engine performance and health status is very important information for engine operators. Such engine performance is normally represented by engine air flow rate, compressor pressure ratios, compressor isentropic efficiencies, turbine entry temperature, turbine isentropic efficiencies, etc. while the engine health status is represented by compressor and turbine efficiency indices and flow capacity indices, etc. However, these crucial performance and health information can not be directly measured and therefore are not easily available. In this research, a novel Adaptive Gas Path Analysis (Adaptive GPA) approach has been developed to estimate actual engine performance and gas path component health status by using gas path measurements, such as gas path pressures, temperatures, shaft rotational speeds, fuel flow rate, etc. Two steps are included in the Adaptive GPA approach, the first step is the estimation of degraded engine performance status by a novel application of a performance adaptation method and the second step is the estimation of engine health status at component level by using a new diagnostic method introduced in this paper based on the information obtained in the first step. The developed Adaptive GPA approach has been tested in four test cases where the performance and degradation of a model gas turbine engine similar to Rolls-Royce aero engine AVON-300 have been analyzed. The case studies have shown that the developed novel linear and non-linear Adaptive GPA approach can accurately and quickly estimate the degraded engine performance and predict the degradation of major engine gas path components with the existence of measurement noise. The test cases have also shown that the calculation time required by the approach is short enough for its potential online applications.

Some Effects of Size on the Performances of Small Gas Turbines

2003 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Lessons Learned ◽  
Rapid Expansion ◽  
Cycle Performance ◽  
Frictional Drag ◽  
Component Design ◽  
Turbine Component ◽  
Performance Development

By the new millennia gas turbine technology standards the size of the first gas turbines of Von Ohain and Whittle would be considered small. Since those first pioneer achievements the sizes of gas turbines have diverged to unbelievable extremes. Large aircraft turbofans delivering the equivalent of 150 megawatts, and research micro engines designed for 20 watts. Microturbine generator sets rated from 2 to 200kW are penetrating the market to satisfy a rapid expansion use of electronic equipment. Tiny turbojets the size of a coca cola can are being flown in model aircraft applications. Shirt button sized gas turbines are now being researched intended to develop output powers below 0.5kW at rotational speeds in excess of 200 Krpm, where it is discussed that parasitic frictional drag and component heat transfer effects can significantly impact cycle performance. The demarcation zone between small and large gas turbines arbitrarily chosen in this treatise is rotational speeds of the order 100 Krpm, and above. This resurgence of impetus in the small gas turbine, beyond that witnessed some forty years ago for potential automobile applications, fostered this timely review of the small gas turbine, and a re-address of the question, what are the effects of size and clearances gaps on the performances of small gas turbines?. The possible resolution of this question lies in autopsy of the many small gas turbine component design constraints, aided by lessons learned in small engine performance development, which are the major topics of this paper.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

25MW Class Modern Industrial Gas Turbine Suitable for Wide Range of Applications in CoGen/CC Power Plants

1996 ◽  
Author(s):  
Chuck Stankiewicz ◽  
Septimus van der Linden
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Developing Economies ◽  
District Heating ◽  
Advanced Technology ◽  
South East Asia ◽  
Wide Range ◽  
Turbine Component ◽  
Industrial Gas Turbine ◽  
Petrochemical Industries

The GT10 25MW class industrial gas turbine from ABB has seen a rapid success in power as well as heat generation for utilities, district heating plants, refineries, communities, universities, paper & food, cement and petrochemical industries. This broad application attests to the versatility of a modern gas turbine benefiting from advanced technology concepts in combustion, as well as turbine component efficiencies. The paper will review these developments and some interesting applications that could benefit dispersed industrial power plants in the fast developing economies of South East Asia.

Performance Deterioration in Industrial Gas Turbines

1991 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

Ridge Estimation and Principal Component Analysis to Solve an Ill-Conditioned Problem of Estimating Unmeasured Gas Turbine Parameters

2013 ◽  
Author(s):  
Maksim Shevchenko ◽  
Sergiy Yepifanov ◽  
Igor Loboda
Keyword(s):  
Principal Component Analysis ◽  
Gas Turbine ◽  
Measurement Errors ◽  
Principal Component ◽  
Component Analysis ◽  
Gas Turbine Engine ◽  
Health Condition ◽  
Component Level ◽  
Estimation Errors ◽  
Turbine Engine

This paper addresses the problem of estimation of unmeasured gas turbine engine variables using statistical analysis of measured data. Possible changes of an engine health condition and lack of information about these changes caused by limited instrumentation are taken into account. Engine thrust is under consideration as one of the most important unmeasured parameters. Two common methods of aircraft gas turbine engine (GTE) thrust monitoring and their errors due to health condition changes are analyzed. Additionally, two mathematical techniques that allow reducing in-flight thrust estimation errors in the case of GTE deterioration are suggested and verified in the paper. They are a ridge trace and a principal component analysis. A turbofan engine has been chosen as a test case. The engine has five measured variables and 23 health parameters to describe its health condition. Measurement errors are simulated using a generator of random numbers with the normal distribution. The engine is presented in calculations by its nonlinear component level model (CLM). Results of the comparison of thrust estimates computed by the CLM and the proposed techniques confirm accuracy of the techniques. The regression model on principal components has demonstrated the highest accuracy.

Effects of Anti-Icing System Operation on Gas Turbine Performance and Monitoring

2001 ◽  
Author(s):  
K. Mathioudakis ◽  
A. Tsalavoutas
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Performance Model ◽  
False Alarms ◽  
System Operation ◽  
Diagnostic Ability ◽  
Engine Model ◽  
On Line ◽  
Industrial Gas Turbine ◽  
Engine Condition

The effect of operation of compressor bleed anti-icing on the performance of an industrial gas turbine is analysed. The effect of putting this system in operation is first qualitatively discussed, while the changes on various performance parameters are derived by using a computer engine performance model. The main point of the paper is the study of the effect of anti-icing system operation on parameters used for engine condition monitoring. It is shown that operation of the anti-icing system causes an apparent modification of such parameters, which may reduce the diagnostic ability of an on-line monitoring system and produce false alarms. It is shown that by incorporating the effect of anti-icing system operation into a diagnostic engine model, such problems can be avoided and the diagnostic ability of the system is not influenced by anti-icing activation. The analysis presented is substantiated through experimental data from a twin shaft gas turbine operating in the field.

A Gas Path Diagnostic and Prognostic Approach for Gas Turbine Applications

2007 ◽  
Author(s):  
Y. G. Li ◽  
P. Nilkitsaranont
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Health Condition ◽  
Remaining Useful Life ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Major Overhaul ◽  
Useful Life ◽  
Engine Reliability ◽  
Over Time

Gas turbine engines experience degradation over time that cause great concern to gas turbine users on engine reliability, availability and operating costs. It has been realized in recent years that gas turbine diagnostics and prognostics is one of the key technologies to enable the move from time-scheduled maintenance to condition-based maintenance in order to improve engine reliability and availability and reduce life cycle costs. The objective of this paper is to introduce a systematic diagnostic and prognostic approach to assess the health condition and estimate the remaining useful life of gas turbine engines before their next major overhaul. A non-linear Gas Path Analysis (GPA) approach is used to assess engine performance degradation with the confidence measured by a GPA Index. A combined regression techniques, including both linear and quadratic models, is proposed to predict the remaining useful life of gas turbine engines. A statistic “Compatibility Check” is used to determine the switch point from linear regression to quadratic regression. The developed diagnostic and prognostic approach has been applied to a model gas turbine engine similar to Rolls-Royce Industrial AVON 1535 implemented with compressor degradation over time. The analysis shows that the developed diagnostic and prognostic approach has great potential to provide an estimation of engine remaining useful life before next major overhaul for gas turbine engines experiencing a typical slow degradation.

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