Industrial Gas Turbine Diagnostics Using Fuzzy Logic

2012 ◽  
Author(s):  
Rafael Barbosa ◽  
Sandro Ferreira
Keyword(s):  
Gas Turbine ◽  
Process Simulation ◽  
Fuzzy System ◽  
Fuzzy Systems ◽  
Test Cases ◽  
Variable Geometry ◽  
Turbine Engine ◽  
Fault Diagnosis System ◽  
Deviation Pattern ◽  
Industrial Gas Turbine

In this work a fuzzy based fault diagnosis system for an industrial gas turbine engine is presented. The system compares measured parameters and those calculated by a computer model, which sets the new and clean reference of the equipment. A fuzzy system classifies and quantifies the faults, which includes part load operation and takes into consideration the compressor variable geometry, which implies in a modification of the deviation pattern between the reference and the model. A commercial software, the GSP (Gas turbine Simulation Program), has been used for the process simulation. The reference software used is called NGGT (Natural Gas and Gas Turbine). Both were calibrated using a real industrial gas turbine operation data. Two compressor faults were simulated using GSP, the resulting variables were compared with those generated by NGGT. The fuzzy sets of the entry variables and the inference rules implemented in the fuzzy systems are dedicated to each fault. Thus, it is possible to add new faults and correct existing fault patterns without disturbing the other faults implemented. The system was tested for the two implemented faults by generating faulty test cases to several geometries and levels of damage. The results showed the robustness of the system and that it is possible to clearly identify the faults, for the several cases tested.

scholarly journals Multifuel Evaluation of Rich/Quench/Lean Combustor

1983 ◽  
Author(s):  
A. S. Novick ◽  
D. L. Troth ◽  
J. Notardonato
Keyword(s):  
Gas Turbine ◽  
Combustion Zone ◽  
Program Management ◽  
Department Of Energy ◽  
Variable Geometry ◽  
Technical Program ◽  
Turbine Engine ◽  
Technology Project ◽  
Industrial Gas Turbine ◽  
Alternate Fuels

The work described in this paper is a part of the DOE/LeRC “Advanced Conversion Technology Project” (ACT). The program is a multiple contract effort with funding provided by the Department of Energy and Technical Program Management provided by NASA LeRC. The emphasis in this paper is the fuel flexible combustor technology developed under the “Low NOx Heavy Fuel Combustor Concept Program” for application to the Detroit Diesel Allison (DDA) Model 570-K industrial gas turbine engine. The technology, to achieve emission goals, emphasizes dry fuel-bound nitrogen (FBN), control of NOx can be effected through a stated combustor with a rich initial combustion zone. A rich/quench/lean (RQL) variable geometry combustor utilizes the technology that will be presented to achieve low NOx from alternate fuels containing FBN. The results will focus on emissions and durability for multifuel operation.

scholarly journals Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing

2010 ◽  
Author(s):  
Shahrokh Etemad ◽  
Benjamin Baird ◽  
Sandeep Alavandi ◽  
William Pfefferle
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Industrial Gas Turbine ◽  
Prototype Testing

scholarly journals Mars™ SoLoNOx Combustion System CFD Modeling

1995 ◽  
Author(s):  
Matthew E. Thomas ◽  
Mark J. Ostrander ◽  
Andy D. Leonard ◽  
Mel Noble ◽  
Colin Etheridge
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Cfd Modeling ◽  
Cfd Analysis ◽  
Combustion System ◽  
Design Environment ◽  
Turbine Engine ◽  
Combustion Modeling ◽  
Premix Combustion ◽  
Industrial Gas Turbine

CFD analysis methods were successfully implemented and verified with ongoing industrial gas turbine engine lean premix combustion system development. Selected aspects of diffusion and lean premix combustion modeling, predictions, observations and validated CFD results associated with the Solar Turbines Mars™ SoLoNOx combustor are presented. CO and NOx emission formation modeling details applicable to parametric CFD analysis in an industrial design environment are discussed. This effort culminated in identifying phenomena and methods of potentially further reducing NOx and CO emissions while improving engine operability in the Mars™ SoLoNOx combustion system. A potential explanation for the abrupt rise in CO formation observed in many gas turbine lean premix combustion systems is presented.

scholarly journals Multi-mode diagnosis of a gas turbine engine using an adaptive neuro-fuzzy system

2018 ◽  
Vol 31 (1) ◽  
pp. 1-9 ◽  
Author(s):  
Houman HANACHI ◽  
Jie LIU ◽  
Christopher MECHEFSKE
Keyword(s):  
Gas Turbine ◽  
Fuzzy System ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Neuro Fuzzy ◽  
Multi Mode

Part-Load Versus Downrated Industrial Gas Turbine Performance

2004 ◽  
Author(s):  
Cleverson Bringhenti ◽  
Joa˜o R. Barbosa
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Cycle Performance ◽  
Variable Geometry ◽  
Part Load ◽  
Distributed Power Generation ◽  
Development Costs ◽  
Base Engine ◽  
Variable Geometry Turbine ◽  
Industrial Gas Turbine

For distributed power generation, sometimes the available gas turbines cannot match the power demands. It has been usual to uprate an existing gas turbine in the lower power range by increasing the firing temperature and speeding it up. The development costs are high and the time to make it operational is large. In the other hand, de-rating an existing gas turbine in the upper power range may be more convenient since it is expected to cut significantly the time for development and costs. In addition, the experience achieved with this engine may be easily extrapolated to the new engine. This paper deals with the performance analysis of an existing gas turbine, in the range of 25 MW, de-rated to the range of 18 MW, concerning the compressor modifications that could be more easily implemented. Analysis is performed for the base engine, running at part-load of MW. A variable geometry compressor is derived from the existing one. Search for optimized performance is carried out for new firing temperatures. A variable geometry turbine analysis is performed for new NGV settings, aiming at better cycle performance.

Steady and Dynamic Performance and Emissions of a Variable Geometry Combustor in a Gas Turbine Engine

2002 ◽  
Author(s):  
Y. G. Li ◽  
R. L. Hales
Keyword(s):  
Gas Turbine ◽  
Dynamic Performance ◽  
Flame Temperature ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Variable Geometry ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
Control Schemes ◽  
Fuel Staging

One of the remedies to reduce the major emissions production of nitric oxide (NOx), carbon monoxide (CO) and unburned hydrocarbon (UHC) from conventional gas turbine engine combustors at both high and low operating conditions without losing its performance and stability is to use variable geometry combustors. This type of combustor configuration provides the possibility of dynamically controlling the airflow distribution of the combustor based on its operating conditions and therefore controlling the combustion in certain lean burn conditions. Two control schemes are described and analyzed in this paper: both are based on airflow control with variable geometry, the second including fuel staging. A model two-spool turbofan engine is chosen in this study to test the effectiveness of the variable geometry combustor and control schemes. The steady and dynamic performance of the turbofan engine is simulated and analyzed using an engine transient performance analysis code implemented with the variable geometry combustor. Empirical correlations for NOx, CO and UHC are used for the estimation of emissions. Some conclusions are obtained from this study: • With variable geometry combustors significant reduction of NOx emissions at high operating conditions and CO and UHC at low operating condition is possible; • Combustion efficiency and stability can be improved at low operating conditions, which is symbolized by the higher flame temperature in the variable geometry combustor; • The introduced correlation between non-dimensional fuel flow rate and air flow ratio to the primary zone is effective and simple in the control of flame temperature; • Circumferential fuel staging can reduce the range of air splitter movement in most of the operating conditions from idle to maximum power and have the great potential to reduce the inlet distortion to the combustor and improve the combustion efficiency; • During transient processes, the maximum moving rate of the hydraulic driven system may delay the air splitter movement but this effect on engine combustor performance is not significant.

Development of FT9 Marine Gas Turbine

1981 ◽  
Author(s):  
D. A. Groghan ◽  
C. L. Miller
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
System A ◽  
On Line ◽  
Condition Monitoring System ◽  
Industrial Gas Turbine ◽  
Engine Condition

The FT9 Marine Gas Turbine development program was initiated in August 1973 by the Naval Sea Systems Command to fulfill, in part, the requirement for a family of gas turbine engines ranging in power from 1000 to 30,000 hp. The FT9 satisfied the requirement to develop a 30,000 hp class marine gas turbine. The FT9 is a derivative of the Pratt & Whitney Aircraft JT9D engine, which powers Boeing 747, DC-10 and A300 aircraft, and of the FT4 industrial gas turbine engine. The FT9 specification also required development of an on-line engine condition monitoring system. A rigorous development test program showed the FT9 has met all specified U.S. Navy requirements and demonstrated its suitability for use in U.S. Navy combatant ships.

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