A Model-Based Controller for Commercial Aero Gas Turbines

2002 ◽  
Author(s):  
Arkadiy Turevskiy ◽  
Richard Meisner ◽  
Robert H. Luppold ◽  
Ronald A. Kern ◽  
James W. Fuller
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Controller Design ◽  
Control Loop ◽  
Turbine Engine ◽  
Model Based Control ◽  
Engine Model ◽  
Model Based ◽  
Loop Feedback

This article describes the design and development of a model-based control system for a large commercial aero gas turbine engine. The control system, referred to as the Integrated Margin Management (IMM) control, exploits a real-time engine model (RTEM) to estimate control loop feedback signals, enabling the implementation of nontraditional control modes. These nontraditional control modes include algorithms for controlling, optimizing, and/or trading off margins to key operational limits such as thrust, compressor stability, combustor stability, turbine life, redline limits, and emissions. An overview of the results produced with the IMM controller design illustrates the feasibility of this approach for commercial aero gas turbine applications.

New Model Based Gas Turbine Fault Diagnostics Using 1D Engine Model and Nonlinear Identification Algorithms

2009 ◽  
Author(s):  
Seyyed Hamid Reza Hosseini ◽  
Hiwa Khaledi ◽  
Mohsen Reza Soltani
Keyword(s):  
Gas Turbine ◽  
Diagnostic System ◽  
Gas Turbine Engine ◽  
Fault Model ◽  
Fault Identification ◽  
Identification System ◽  
Turbine Engine ◽  
Engine Model ◽  
Exhaust Temperature ◽  
Model Based

Gas turbine fault identification has been used worldwide in many aero and land engines. Model based techniques have improved isolation of faults in components and stages’ fault trend monitoring. In this paper a powerful nonlinear fault identification system is developed in order to predict the location and trend of faults in two major components: compressor and turbine. For this purpose Siemens V94.2 gas turbine engine is modeled one dimensionally. The compressor is simulated using stage stacking technique, while a stage by stage blade cooling model has been used in simulation of the turbine. New fault model has been used for turbine, in which a degradation distribution has been considered for turbine stages’ performance. In order to validate the identification system with a real case, a combined fault model (a combination of existing faults models) for compressor is used. Also the first stage of the turbine is degraded alone while keeping the other stages healthy. The target was to identify the faulty stages not faulty components. The imposed faults are one of the most common faults in a gas turbine engine and the problem is one of the most difficult cases. Results show that the fault diagnostic system could isolate faults between compressor and turbine. It also predicts the location of faulty stages of each component. The most interesting result is that the fault is predicted only in the first stage (faulty stage) of the turbine while other stages are identified as healthy. Also combined fault of compressor is well identified. However, the magnitude of degradation could not be well predicted but, using more detailed models as well as better data from gas turbine exhaust temperature, will enhance diagnostic results.

Model Based Performance Correction Methodology — A Case Study

2014 ◽  
Author(s):  
Koldo Zuniga ◽  
Thomas P. Schmitt ◽  
Herve Clement ◽  
Joao Balaco
Keyword(s):  
Control System ◽  
Control Systems ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Performance Test ◽  
Test Results ◽  
Model Based ◽  
Test Conditions ◽  
Partial Load

Correction curves are of great importance in the performance evaluation of heavy duty gas turbines (HDGT). They provide the means by which to translate performance test results from test conditions to the rated conditions. The correction factors are usually calculated using the original equipment manufacturer (OEM) gas turbine thermal model (a.k.a. cycle deck), varying one parameter at a time throughout a given range of interest. For some parameters bi-variate effects are considered when the associated secondary performance effect of another variable is significant. Although this traditional approach has been widely accepted by the industry, has offered a simple and transparent means of correcting test results, and has provided a reasonably accurate correction methodology for gas turbines with conventional control systems, it neglects the associated interdependence of each correction parameter from the remaining parameters. Also, its inherently static nature is not well suited for today’s modern gas turbine control systems employing integral gas turbine aero-thermal models in the control system that continuously adapt the turbine’s operating parameters to the “as running” aero-thermal component performance characteristics. Accordingly, the most accurate means by which to correct the measured performance from test conditions to the guarantee conditions is by use of Model-Based Performance Corrections, in agreement with the current PTC-22 and ISO 2314, although not commonly used or accepted within the industry. The implementation of Model-based Corrections is presented for the Case Study of a GE 9FA gas turbine upgrade project, with an advanced model-based control system that accommodated a multitude of operating boundaries. Unique plant operating restrictions, coupled with its focus on partial load heat rate, presented a perfect scenario to employ Model-Based Performance Corrections.

Distributed Network System for Real-Time Model Based Control of Industrial Gas Turbines

2011 ◽  
Author(s):  
V. Panov
Keyword(s):  
Control System ◽  
Real Time ◽  
Gas Turbine ◽  
Distributed Network ◽  
Hardware In The Loop ◽  
Time Model ◽  
Model Based Control ◽  
Model Based ◽  
On Line ◽  
Dedicated Hardware

This paper describes the development of a distributed network system for real-time model based control of industrial gas turbine engines. Distributed control systems contribute toward improvements in performance, testability, control system maintainability and overall life-cycle cost. The goal of this programme was to offer a modular platform for improved model based control system. Hence, another important aspect of this programme was real-time implementation of non-linear aero-thermal gas turbine models on a dedicated hardware platform. Two typical applications of real-time engine models, namely hardware-in-the-loop simulations and on-line co-simulations, have been considered in this programme. Hardware-in-the-loop platform has been proposed as a transitional architecture, which should lead towards a fully distributed on-line model based control system. Distributed control system architecture offers the possibility of integrating a real-time on-line engine model embedded within a dedicated hardware platform. Real-time executing models use engine operating conditions to generate expected values for measured and non-measured engine parameters. These virtual measurements can be used for the development of model based control methods, which can contribute towards improvements in engine stability, performance and life management. As an illustration of model based control concept, the example of gas turbine transient over-temperature protection is presented in this study.

Cycle Optimisation Using an Advanced, Real Engine Performance Prediction Model

2002 ◽  
Author(s):  
Miles Coppinger ◽  
Graham Cox ◽  
John Hannis ◽  
Nigel Cox
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Integer Number ◽  
Turbine Engine ◽  
Engine Model ◽  
Engine Design ◽  
Industrial Gas Turbines ◽  
High Degree ◽  
Technology Level

A whole gas-turbine engine model has been developed incorporating all of the key turbomachinery aerothermal relationships. The aim of the model has been to predict trends in gas-turbine performance with a high degree of confidence that they reflect real engine design limitations. Simple cycles, recuperated, inter-cooled, and inter-cooled recuperated cycles can be assessed across a wide of range of operating parameters. The model is spreadsheet-based with additional macro programming. The major part of it is concerned with establishing representative overall turbine characteristics. A non-integer number of stages is determined as a function of technology level inputs. Individual stage geometry features are derived allowing the calculation of the coolant requirements and efficiencies. The results of various studies are presented for a number of cycle types. The resulting trends are believed to be sensible because of the realistic turbine features. Confidence in the method is established by the modelling of a number of existing industrial gas turbines.

Computational Simulation of Gas Turbines: Part 2—Extensible Domain Framework

2000 ◽  
Vol 122 (3) ◽  
pp. 377-386 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Design Patterns ◽  
Heterogeneous Computing ◽  
Computational Simulation ◽  
Object Oriented ◽  
Turbine Engine ◽  
Engine Model ◽  
Computationally Intensive ◽  
High Level

This paper describes the design concepts and object-oriented architecture of Onyx, an extensible domain framework for computational simulation of gas turbine engines. Onyx provides a flexible environment for defining, modifying, and simulating the component-based gas turbine models described in Part 1 of this paper. Using advanced object-oriented technologies such as design patterns and frameworks, Onyx enables users to customize and extend the framework to add new functionality or adapt simulation behavior as required. A customizable visual interface provides high-level symbolic control of propulsion system construction and execution. For computationally-intensive analysis, components may be distributed across heterogeneous computing architectures and operating systems. A distributed gas turbine engine model is developed and simulated to illustrate the use of the framework. [S0742-4795(00)02403-0]

scholarly journals Computational Simulation of Gas Turbines: Part II — Extensible Domain Framework

1999 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Design Patterns ◽  
Heterogeneous Computing ◽  
Computational Simulation ◽  
Object Oriented ◽  
Turbine Engine ◽  
Engine Model ◽  
Computationally Intensive ◽  
High Level

This paper describes the design concepts and object-oriented architecture of Onyx, an extensible domain framework for computational simulation of gas turbine engines. Onyx provides a flexible environment for defining, modifying and simulating the component-based gas turbine models described in Part 1 of this paper. Using advanced object-oriented technologies such as design patterns and frameworks, Onyx enables users to customize and extend the framework to add new functionality or adapt simulation behavior as required. A customizable visual interface provides high-level symbolic control of propulsion system construction and execution. For computationally-intensive analysis, components may be distributed across heterogeneous computing architectures and operating systems. A distributed gas turbine engine model is developed and simulated to illustrate the use of the framework.

scholarly journals Computational Simulation of Gas Turbines: Part I — Foundations of Component-Based Models

1999 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Computational Simulation ◽  
Simulation Models ◽  
Engineering Model ◽  
Levels Of Abstraction ◽  
Turbine Engine ◽  
Engine Model ◽  
Flexible Component ◽  
Aerospace Propulsion

Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part II of this paper.

scholarly journals The Use of Compressor-Inlet Prewhirl for the Control of Small Gas Turbines

1963 ◽  
Author(s):  
J. R. Anderson ◽  
A. R. Shouman
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Test Results ◽  
Turbine Engine ◽  
Instantaneous Power ◽  
Compressor Inlet ◽  
Power Response ◽  
Principal Elements

The objective of this paper is to describe a control system recently developed to provide nearly instantaneous power response with a two-shaft gas turbine. The principal elements in this system are movable guide vanes in the compressor inlet. The effects of air prewhirl on centrifugal compressor and gas-turbine-engine performance are discussed and test results are presented.

Computational Simulation of Gas Turbines: Part 1—Foundations of Component-Based Models

2000 ◽  
Vol 122 (3) ◽  
pp. 366-376 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Computational Simulation ◽  
Simulation Models ◽  
Engineering Model ◽  
Levels Of Abstraction ◽  
Turbine Engine ◽  
Engine Model ◽  
Flexible Component ◽  
Aerospace Propulsion

Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part 2 of this paper. [S0742-4795(00)02303-6]

The Use of Compressor-Inlet Prewhirl for the Control of Small Gas Turbines

1964 ◽  
Vol 86 (2) ◽  
pp. 136-140 ◽  
Author(s):  
A. R. Shouman ◽  
J. R. Anderson
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Test Results ◽  
Turbine Engine ◽  
Instantaneous Power ◽  
Compressor Inlet ◽  
Power Response ◽  
Principal Elements

The objective of this paper is to describe a control system recently developed to provide nearly instantaneous power response with a two-shaft gas turbine. The principal elements in this system are movable guide vanes in the compressor inlet. The effects of air prewhirl on centrifugal compressor and gas-turbine engine performance are discussed and test results are presented.

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