Operational experience with intelligent software agents for shipboard diesel and gas turbine engine health monitoring

2005 ◽  
Author(s):  
K.P. Logan
Keyword(s):  
Gas Turbine ◽  
Health Monitoring ◽  
Software Agents ◽  
Gas Turbine Engine ◽  
Operational Experience ◽  
Turbine Engine ◽  
Intelligent Software ◽  
Intelligent Software Agents

Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Exhaust Gas ◽  
Cycle Fatigue ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Components

AbstractTemperature probes of different designs were widely used in aero gas turbine engines for measurement of air and gas temperatures at various locations starting from inlet of fan to exhaust gas from the nozzle. Exhaust Gas Temperature (EGT) downstream of low pressure turbine is one of the key parameters in performance evaluation and digital engine control. The paper presents a holistic approach towards life assessment of a high temperature probe housing thermocouple sensors designed to measure EGT in an aero gas turbine engine. Stress and vibration analysis were carried out from mechanical integrity point of view and the same was evaluated in rig and on the engine. Application of 500 g load concept to clear the probe design was evolved. The design showed strength margin of more than 20% in terms of stress and vibratory loads. Coffin Manson criteria, Larsen Miller Parameter (LMP) were used to assess the Low Cycle Fatigue (LCF) and creep life while Goodman criteria was used to assess High Cycle Fatigue (HCF) margin. LCF and HCF are fatigue related damage from high frequency vibrations of engine components and from ground-air-ground engine cycles (zero-max-zero) respectively and both are of critical importance for ensuring structural integrity of engine components. The life estimation showed LCF life of more than 4000 mission reference cycles, infinite HCF life and well above 2000 h of creep life. This work had become an integral part of the health monitoring, performance evaluation as well as control system of the aero gas turbine engine.

Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Exhaust Gas ◽  
Cycle Fatigue ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Components

Abstract Temperature probes of different designs were widely used in aero gas turbine engines for measurement of air and gas temperatures at various locations starting from inlet of fan to exhaust gas from the nozzle. Exhaust Gas Temperature (EGT) downstream of low pressure turbine is one of the key parameters in performance evaluation and digital engine control. The paper presents a holistic approach towards life assessment of a high temperature probe housing thermocouple sensors designed to measure EGT in an aero gas turbine engine. Stress and vibration analysis were carried out from mechanical integrity point of view and the same was evaluated in rig and on the engine. Application of 500 g load concept to clear the probe design was evolved. The design showed strength margin of more than 20% in terms of stress and vibratory loads. Coffin Manson criteria, Larsen Miller Parameter (LMP) were used to assess the Low Cycle Fatigue (LCF) and creep life while Goodman criteria was used to assess High Cycle Fatigue (HCF) margin. LCF and HCF are fatigue related damage from high frequency vibrations of engine components and from ground-air-ground engine cycles (zero-max-zero) respectively and both are of critical importance for ensuring structural integrity of engine components. The life estimation showed LCF life of more than 4000 mission reference cycles, infinite HCF life and well above 2000 h of creep life. This work had become an integral part of the health monitoring, performance evaluation as well as control system of the aero gas turbine engine.

Advanced Diagnostic and Prognostic Technologies for Gas Turbine Engine Risk Assessment

2000 ◽  
Author(s):  
Michael J. Roemer ◽  
Gregory J. Kacprzynski
Keyword(s):  
Anomaly Detection ◽  
Real Time ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Management Practices ◽  
Probabilistic Models ◽  
Gas Turbine Engine ◽  
Probabilistic Methods ◽  
Great Opportunity ◽  
Turbine Engine

Real-time, integrated health monitoring of gas turbine engines that can detect, classify, and predict developing engine faults is critical to reducing operating and maintenance costs while optimizing the life of critical engine components. Statistical-based anomaly detection algorithms, fault pattern recognition techniques and advanced probabilistic models for diagnosing structural, performance and vibration related faults and degradation can now be developed for real-time monitoring environments. Integration and implementation of these advanced technologies presents a great opportunity to significantly enhance current engine health monitoring capabilities and risk management practices. This paper describes some novel diagnostic and prognostic technologies for dedicated, real-time sensor analysis, performance anomaly detection and diagnosis, vibration fault detection, and component prognostics. The technologies have been developed for gas turbine engine health monitoring and prediction applications which includes an array of intelligent algorithms for assessing the total ‘health’ of an engine, both mechanically and thermodynamically. This includes the ability to account for uncertainties from engine transient conditions, random measurement fluctuations and modeling errors associated with model-based diagnostic and prognostic procedures. The implementation of probabilistic methods in the diagnostic and prognostic methodology is critical to accommodating for these types of uncertainties.

Determination of Allowable FOD Defects Sizes on the Surface of Gas-Turbine Engine Stator Parts Based on Stress-Concentration Factors

2014 ◽  
Author(s):  
Alexandr Pakhomenkov ◽  
Denis Slobodskoy
Keyword(s):  
Stress Concentration ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Operational Experience ◽  
Foreign Object ◽  
Turbine Engine ◽  
Periodic Inspection ◽  
Concentration Factors ◽  
Stress Concentration Factors

Requirements for reliability and safety of modern aircraft engines are constantly growing [1–2]. Among these requirements is periodic inspection of the engine condition and condition of its individual parts during operation, for the purpose of evaluation of the risk to operation. This is to ascertain possible damage to various engine parts in the course of operation and progressive wear. Damage can occur for a variety of reasons: ingestion of foreign matter in the engine gas path, operation in extreme and off-design conditions, wear, etc. To trace the engine parts condition and detect various damage on the engine parts, periodic inspection is provided. In case of any damage or deviations on parts, the question of their performance and possibility to break during operation are addressed. There are two ways of answering this question: 1 – experimental demonstration of the required strength of parts with damage; 2 – computational demonstration of the required strength of parts with damage. The first way requires a good deal of time and money for carrying out the experiments. It is efficient only with enough operational experience in typical parts with various surface damage. While developing a new engine (having no prototypes) it is more reasonable to use computational methods. To determine the allowable damage of gas-turbine engine parts, a special procedure has been developed. Its main principles consist of the following: - classification of the typical parts damage by foreign object ingestion; - determination of the stress concentration factors (Kt) due to damage for various defect sizes; - determination of strength factors of safety and life for various zones of parts without damage; - determination of Kt values with which minimum allowable values of strength safety factor and life are attained; - determination of allowable sizes of various types of damage for all zones of each part based on previously defined Kt dependencies on typical damage sizes. This methodology is proposed for determination of allowable damage on the surface of gas-turbine engines stator parts caused by foreign object ingestion in order to ensure the required reliability and safety; its experimental verification is foreseen for the future.

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