TED-Turbine Engine Diagnostics: an expert diagnostic system for the M1 Abrams AGT1500 turbine engine

2002 ◽  
Author(s):  
R. Helfman ◽  
J. Dumer ◽  
T. Hanratty
Keyword(s):  
Diagnostic System ◽  
Turbine Engine

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.

scholarly journals On Designing an Expert Diagnostic System of the Aircraft Turbine Engine Functional Units

2020 ◽  
Vol 50 (1) ◽  
pp. 171-192
Author(s):  
Henryk Borowczyk ◽  
Jarosław Spychała
Keyword(s):  
Dynamic Models ◽  
Diagnostic System ◽  
Compact Representation ◽  
Diagnostic Model ◽  
Diagnostic Systems ◽  
Turbine Engine ◽  
Flight Data ◽  
Diagnostic Parameters ◽  
Functional Units ◽  
The Relationship

AbstractThe paper presents issues related to the design of an expert diagnostic system of turbine engine functional units. Dedicated diagnostic stations and on-board flight data recorders are the sources of diagnostic signals. The signals were parameterized or identified dynamic models to get a compact representation in the form of a set of parameters. The set of diagnostic parameters was subjected to integer encoding. On this basis, a multi-valued diagnostic model describing the relationship between the set of faults and the set of symptoms (code values of diagnostic parameters) was determined. The proposed approach can be used in the design of expert diagnostic systems for propulsion units of any aircraft.

scholarly journals Prototype of the expert tribological diagnostic system of turbine engine

2018 ◽  
Vol 48 (1) ◽  
pp. 323-340
Author(s):  
Henryk Borowczyk ◽  
Marek Zboiński ◽  
Przemysław Jóźwiak ◽  
Kamila Dobosz ◽  
Andrzej Czarnecki ◽  
...  
Keyword(s):  
Expert System ◽  
Research Methods ◽  
Diagnostic System ◽  
Computer Application ◽  
Turbine Engine ◽  
Sources Of Knowledge ◽  
Physico Chemical ◽  
Wear Products ◽  
New Research ◽  
Representation Of Knowledge

Abstract The article presents issues related to the construction of a prototype of an expert tribological diagnostic system for a turbine engine. The database consists of the results of tests on the chemical composition and concentration of the wear products in the oil sample as well as the physico-chemical parameters of the oil. For all diagnostic parameters, threshold values have been defined to classify the level of wear (normal, elevated, increased and emergency). PC Shell software enabling the combination of a rule representation of knowledge and procedural programming was used to build the expert system. The computer application consists of the main module and sources of knowledge dedicated to the applied research methods. The modular structure allows the development of an expert system by adding new research methods.

scholarly journals Scopus as a Meta-Source of Knowledge About Turbine Blade Damage in the Aspect of Designing an Expert Diagnostic System

2017 ◽  
Vol 43 (1) ◽  
pp. 145-162
Author(s):  
Henryk Borowczyk ◽  
Józef Błachnio ◽  
Jarosław Spychała
Keyword(s):  
Turbine Blade ◽  
Diagnostic System ◽  
General Term ◽  
Diagnostic Methods ◽  
Turbine Engine ◽  
Second Stage ◽  
Automatic Mode ◽  
Search Terms ◽  
Repair Technology ◽  
Rotary Machines

AbstractThe paper presents the concept of using the Scopus as a meta-source of knowledge about turbine blade damage in the aspect of designing an expert diagnostic system. In the first stage, the search was limited to the scope of the general term “turbine engine”, followed by a refinement of the search terms within the area of rotary machines components degradation including their construction, manufacturing, repair technology and diagnostic methods. By using EndNote software in semi-automatic mode, specific issue groups have been designated. In the second stage, a query focused on the main causes of turbine blade damage and diagnostic methods was proposed. Using the Scopus-based search and archiving tools, one can systematically update the knowledge.

scholarly journals Ensuring permissible level of gas turbine dynamic loading in operation by means of standard engine control devices

2019 ◽  
Vol 18 (2) ◽  
pp. 112-120
Author(s):  
V. V. Chervonyuk ◽  
B. B. Korovin
Keyword(s):  
Gas Turbine ◽  
Dynamic Loading ◽  
Diagnostic System ◽  
Gas Turbine Engine ◽  
Drop Out ◽  
Combustion Chambers ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Supersonic Aircraft ◽  
Engine Dynamic

To solve the fatigue resistance problems of gas turbine engine elements using the existing principles of regulation based on the use of safe load factors for various loading schemes we suggest exercising controlled influence upon the loading sources in operation using a system of automatic control and standard devices for engine monitoring. The article discusses the use of this approach to minimize the dynamic loading of the LPC (low pressure compressor) blades of afterburning turbojet engines installed on supersonic aircraft, as well as to combat oscillatory combustion in combustion chambers with shock actuation of free wheel clutches and self-induced oscillation in the helicopter transmission system. Besides, it is shown that the monitoring of GTE (gas turbine engine) dynamic load should be accompanied by improving the efficiency of the on-board engine diagnostic system. It is impossible to reduce the probability of target drop-out or faulty actuation of the existing standard means and facilities of such systems down to the required level without applying an individual approach to the determination of permissible levels of adjustable diagnostic parameters.

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