On Line Fault Detection and Isolation in Gas Turbine Combustion Chambers

2008 ◽  
Author(s):  
Pablo Medina ◽  
Doris Saez ◽  
Roberto Roman
Keyword(s):  
Fault Detection ◽  
Combustion Chamber ◽  
Gas Turbines ◽  
Model Identification ◽  
Fault Detection And Isolation ◽  
Gas Temperature ◽  
Combustion Chambers ◽  
Base Function ◽  
Swirl Angle ◽  
On Line

This work presents the development of a new model for the exhaust gas temperature based on both basis function expansion and the Brayton cycle. This model is a function of the power generated, ambient temperature, compression rate, and the temperature of each combustion chamber. This last temperature is unknown, but could be estimated. The model basis functions also include the spatial distribution of the combustion chamber and exhaust gases swirl angle surface. Thus, based on the gas path in the turbine, each base function of the model is related to a particular combustion chamber. This is the main assumption that allows solving the fault detection and isolation problem in gas turbines at the level of combustion chambers. As a result of the model identification at every instant, there is a group of coefficients, which are associated to each combustion chamber. From these coefficients, it is possible to generate signals that can be analyzed with statistical techniques and also with wavelets to detect abrupt changes in its behavior.

scholarly journals Aircraft Engine On-Line Diagnostics Through Dual-Channel Sensor Measurements: Development of a Baseline System

2008 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Fault Detection ◽  
Aircraft Engine ◽  
Fault Detection And Isolation ◽  
Channel Measurements ◽  
Sensor Fault ◽  
Engine Model ◽  
Dual Channel ◽  
Sensor Fault Detection ◽  
Baseline System ◽  
On Line

In this paper, a baseline system which utilizes dual-channel sensor measurements for aircraft engine on-line diagnostics is developed. This system is composed of a linear on-board engine model (LOBEM) and fault detection and isolation (FDI) logic. The LOBEM provides the analytical third channel against which the dual-channel measurements are compared. When the discrepancy among the triplex channels exceeds a tolerance level, the FDI logic determines the cause of the discrepancy. Through this approach, the baseline system achieves the following objectives: 1) anomaly detection, 2) component fault detection, and 3) sensor fault detection and isolation. The performance of the baseline system is evaluated in a simulation environment using faults in sensors and components.

scholarly journals Aircraft Engine On-Line Diagnostics Through Dual-Channel Sensor Measurements: Development of an Enhanced System

2008 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Fault Detection ◽  
Diagnostic System ◽  
Aircraft Engine ◽  
Fault Detection And Isolation ◽  
Channel Measurements ◽  
Engine Model ◽  
Dual Channel ◽  
Sensor Fault Detection ◽  
Baseline System ◽  
On Line

In this paper, an enhanced on-line diagnostic system which utilizes dual-channel sensor measurements is developed for the aircraft engine application. The enhanced system is composed of a nonlinear on-board engine model (NOBEM), the hybrid Kalman filter (HKF) algorithm, and fault detection and isolation (FDI) logic. The NOBEM provides the analytical third channel against which the dual-channel measurements are compared. The NOBEM is further utilized as part of the HKF algorithm which estimates measured engine parameters. Engine parameters obtained from the dual-channel measurements, the NOBEM, and the HKF are compared against each other. When the discrepancy among the signals exceeds a tolerance level, the FDI logic determines the cause of discrepancy. Through this approach, the enhanced system achieves the following objectives: 1) anomaly detection, 2) component fault detection, and 3) sensor fault detection and isolation. The performance of the enhanced system is evaluated in a simulation environment using faults in sensors and components, and it is compared to an existing baseline system.

Combination of 1D Code and CFD for Performance Analysis of a Silo Type Gas Turbine Combustor

2010 ◽  
Author(s):  
N. Rasooli ◽  
S. Besharat Shafiei ◽  
H. Khaledi
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Mass Distribution ◽  
Gas Turbines ◽  
Pressure Loss ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Empirical Correlations ◽  
Combustion Chambers ◽  
Cfd Simulations

Whereas Gas Turbines are the most important producers of Propulsion and Power in the world and with attention to the importance of combustion chamber as one of the three basic components of Gas Turbine, various activities in different levels have been done on this component. Because of the environmental limitations and laws related to the pollutants such as NOx and CO, Lean Premixed Combustion Chambers are specially considered in gas turbine industries. This study is part of a Multi-Layer simulation of the whole gas turbine cycle in MPG Company. In this work, the combination of a general 1D code and CFD is used for deriving appropriate performance curves for a 1D and 0D gas turbine design, off-design and dynamic cycle code. This 1D code is a general code which has been developed for different combustion chambers; annular, can-annular, can type and silo type combustion chambers. The purpose of generating this 1D code is the possibility of fast analysis of combustors in different operating conditions and reaching required outputs. This 1D code is a part of a general simulation 1D code for gas turbine and was used for a silo type combustor performance prediction. This code generates required quantities such as pressure loss, exit temperature, liner temperature and mass distribution through the combustion chamber. Mass distribution and pressure loss are analyzed and determined with an electrical analogy. Results derived from 1D code are validated with empirical data available for different combustors. There is appropriate agreement between these experimental and analytical results. Drag coefficients for liner holes are available from experimental data and for burner are calculated as a curve with CFD simulations. What differs this code from other 1D codes for gas turbine combustors is the advantage of using combustion efficiencies evolved from numerical simulation results in different loads. These efficiencies are determined with CFD simulations and are available as maps and inserted into the gas temperature calculation algorithm of 1D code. In other 1D codes in this field, empirical correlations are used for combustion efficiency determination. Combustion efficiency curves for design and off-design conditions in this study are achieved by 2D and 3D simulation of combustion chamber with application of EBU/Finite Rate model and 8 step reactions of CH4 burning. Diffusion flame in low loads and premixed flame in high loads are considered. Flame stability and Lean Blow Out charts are evolved from CFD simulation and Heat transfer is applied with empirical correlations.

Early fault detection of gas turbine hot components under different ambient and operating conditions

2021 ◽  
pp. 095441002098689
Author(s):  
Jiao Liu ◽  
Jinfu Liu ◽  
Daren Yu ◽  
Zhongqi Wang ◽  
Weizhong Yan ◽  
...  
Keyword(s):  
Fault Detection ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Detection Method ◽  
Operating Conditions ◽  
Exhaust Gas ◽  
Gas Temperature ◽  
Spatial Correlations ◽  
Early Fault Detection ◽  
Exhaust Gas Temperature

Failure of hot components in gas turbines often causes catastrophic results. Early fault detection can prevent serious incidents and improve the availability. A novel early fault detection method of hot components is proposed in this article. Exhaust gas temperature is usually used as the indicator to detect the fault in the hot components, which is measured by several exhaust thermocouples with uniform distribution at the turbine exhaust section. The healthy hot components cause uniform exhaust gas temperature (EGT) profile, whereas the hot component faults could cause the uneven EGT profile. However, the temperature differences between different thermocouple readings are also affected by different ambient and operating conditions, and it sometimes has a greater influence on EGT than the faults. In this article, an accurate EGT model is presented to eliminate the influence of different ambient and operating conditions on EGT. Especially, the EGT profile swirl under different ambient and operating conditions is also included by considering the information of the thermocouples’ spatial correlations and the EGT profile swirl angle. Based on the developed EGT model, the detection performance of early fault detection of hot components in gas turbine is improved. The accuracy and effectiveness of the developed early fault detection method are evaluated by the real-world gas turbine data.

scholarly journals Measurements on a Blast-Furnace-Gas and Oil-Fired Combustion Chamber of a 17.25-MWe Closed-Cycle Gas Turbine Plant

1970 ◽  
Author(s):  
K. Bammert ◽  
H. Rehwinkel
Keyword(s):  
Blast Furnace ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Fuel Oil ◽  
Test Results ◽  
Closed Cycle ◽  
Combustion Chambers ◽  
Blast Furnace Gas ◽  
Stage Of Development

The paper discusses the present stage of development of combustion chambers for fossil-fired closed-cycle gas turbines, describing West Germany’s “Gelsenkirchen” plant which can be operated with blast-furnace gas and fuel oil with any desired ratio of gas to oil. The output data and the efficiency of this plant are illustrated by test results. In the development and construction of fossil-fired closed-cycle gas turbine plants, the gas heater presents the greatest difficulties and is the most expensive part of the plant. Therefore, very detailed measurements were taken to determine the total heat absorption in the combustion chamber and its local distribution over the length of the chamber. The results obtained are compared with previous measurements at a smaller plant, the mine-gas and pulverized-coal fired “Haus Aden” plant.

scholarly journals Experience With Large Gas Turbine Combustion Chambers

1982 ◽  
Author(s):  
A. Lienert ◽  
O. Schmoch
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Peak Load ◽  
Combustion Chambers ◽  
Initial Stage ◽  
Gas Turbine Combustion ◽  
Maintenance And Inspection ◽  
Positive Effect ◽  
Base Load

Large gas turbine combustion chambers, being arranged outside of the unit, exhibit quite a lot of advantages with respect to combustion. Moreover, they are characterized by a long life of all components. Thus, in case of such gas turbine units the maintenance and inspection intervals are relatively large being not determined by the combustion chamber or combustion chamber components. There are not many failures. They may easily be recognized at their initial stage and can be eliminated quickly as the inside is accessible via a manhole. This in turn has a positive effect on overall maintenance and service cost. Besides, this easy accessibility allows for a direct examination of the turbine inner casing and the first turbine stages in case of maintenanced works. Experiences are based on the operation of more than 100 gas turbines of such a kind, whereby several have been run at peak load with more than 5000 starts, others at base load with more than 100,000 operating hours.

MULTIFOCAL IGNITION OF COMBUSTION CHAMBER BY SUBCRITICAL STREAMER MICROWAVE DISCHARGE

2020 ◽  
Author(s):  
P. V. Bulat ◽  
◽  
M. P. Bulat ◽  
P. V. Denissenko ◽  
V. V. Upyrev ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbines ◽  
Internal Combustion Engines ◽  
Microwave Discharge ◽  
Fuel Mixture ◽  
Combustion Products ◽  
Combustion Chambers ◽  
Entire Volume ◽  
Gas Pumping ◽  
Pumping Units

The challenges facing engine developers, aimed at improving the technical and operational characteristics, more stringent environmental standards, make the work aimed at increasing the efficiency of ignition, systems highly relevant. Technologies of prechamber, arc ignition, and ignition by corona discharge known to date require significant energy costs. In addition, ignition of a fuel mixture by such systems is local which leads to the limitation in the burning rate, incomplete combustion of fuel, and formation of harmful impurities in combustion products. Volumetric or multipoint ignition may significantly increase the effectiveness of the use of ignition systems. The use of a subcritical streamer microwave discharge, which is a network of thin hot channels propagating in the volume of the combustion chamber, seems promising because it provides virtually instantaneous ignition of the mixture in the entire volume. In this paper, the results of experiments using a subcritical streamer microwave discharge are presented. The possibility of volumetric ignition and a substantial increase in the completeness of fuel combustion is demonstrated. A number of indirect evidences indicate the absence of nitrogen oxides in combustion products. The results can be applied to the development of multivolumetric ignition systems in internal combustion engines, gas pumping units, power gas turbines, low-emission combustion chambers, etc.

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