Effects of Compressor Fouling and Compressor Turbine Degradation on Engine Creep Life Consumption

2018 ◽  
Vol 140 (10) ◽  
Author(s):  
Ebigenibo Genuine Saturday ◽  
Thank-God Isaiah
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Model ◽  
Capacity Degradation ◽  
Engine Components ◽  
Stress Models ◽  
Industrial Gas Turbine ◽  
Life Consumption

The effect of engine degradation in the form of compressor fouling and compressor turbine degradation on the creep life consumption of the high-pressure (HP) turbine blades of an LM2500+ industrial gas turbine engine is investigated in this work. The degradations are flow capacity degradation and isentropic efficiency degradation. An engine model was created in Cranfield gas turbine performance and diagnostics software, pythia. Blade thermal and stress models were developed together with the Larson–Miller parameter (LMP) method for creep life analysis. The percentage decreases in creep life due to each effect were examined. For the engine considered, compressor degradation has more impact on engine creep life toward peak power operation, while HP turbine degradation has more impact on creep life at lower power levels. The results of this work will give engine operators an idea of how engine components creep life is consumed and make reasonable decisions concerning operating at part loads.

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.

Probabilistic High-Cycle Fretting Fatigue Assessment of Gas Turbine Engine Components

2011 ◽  
Author(s):  
Kwai S. Chan ◽  
Michael P. Enright ◽  
Patrick J. Golden ◽  
Samir Naboulsi ◽  
Ramesh Chandra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Real Life ◽  
Fretting Fatigue ◽  
Gas Turbine Engine ◽  
Rotating Stall ◽  
Worst Case ◽  
Design Assessment ◽  
Turbine Engine ◽  
Engine Components

High-cycle fatigue (HCF) is arguably one of the costliest sources of in-service damage in military aircraft engines. HCF of turbine blades and disks can pose a significant engine risk because fatigue failure can result from resonant vibratory stresses sustained over a relatively short time. A common approach to mitigate HCF risk is to avoid dangerous resonant vibration modes (first bending and torsion modes, etc.) and instabilities (flutter and rotating stall) in the operating range. However, it might be impossible to avoid all the resonance for all flight conditions. In this paper, a methodology is presented to assess the influences of HCF loading on the fracture risk of gas turbine engine components subjected to fretting fatigue. The methodology is based on an integration of a global finite element analysis of the disk-blade assembly, numerical solution of the singular integral equations using the CAPRI (Contact Analysis for Profiles of Random Indenters) and Worst Case Fret methods, and risk assessment using the DARWIN (Design Assessment of Reliability with Inspection) probabilistic fracture mechanics code. The methodology is illustrated for an actual military engine disk under real life loading conditions.

scholarly journals Allison Model 501-K14 Gas Turbine 1000-Hr Saltwater Ingestion Test

1969 ◽  
Author(s):  
W. R. Humphrey ◽  
L. M. Maas
Keyword(s):  
Gas Turbine ◽  
Salt Water ◽  
Aircraft Engine ◽  
Industrial Applications ◽  
Application Performance ◽  
Turbine Engine ◽  
Water Ingestion ◽  
Marine Application ◽  
Engine Components ◽  
Industrial Gas Turbine

The Allison Model 501-K14 industrial gas turbine engine, a modified version of the T56 aircraft engine, has been used extensively as a prime mover for industrial applications. The areas of application to date have been in the gas transmission field driving centrifugal gas compressors and driving electrical generators. This paper describes a 1000-hr cyclic test of the Model 501-K14 engine with salt water ingestion as the first step in qualifying the engine for marine application. Performance data, photographs of the installation and engine components, and inspection results are included in this report.

Rig and Gas Turbine Engine Testing of MI-CMC Combustor and Shroud Components

2001 ◽  
Author(s):  
Gregory Corman ◽  
Anthony Dean ◽  
Stephen Brabetz ◽  
Keith McManus ◽  
Milivoj Brun ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Matrix Composites ◽  
Gas Turbine Engine ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Single Piece ◽  
Engine Testing ◽  
Engine Components ◽  
Industrial Gas Turbine

GE is continuing work on the development of Melt-Infiltrated Ceramic Matrix Composites (MI-CMC) for use in industrial gas turbine engine components. Long-term environmental degradation of test samples under realistic engine conditions is being determined using a unique high-pressure combustion rig apparatus. Rig testing is also being used to evaluate an F-class 1st stage shroud system incorporating an MI-CMC inner shroud component. While large, advanced engines, such as the F and H classes, offer the greatest benefits for using MI-CMC components, initial engine tests have been done using a GE-2 (2MW) machine to reduce costs and risk. Long term (1000 hours) engine testing results for single piece GE-2 shrouds are also described.

Probabilistic High-Cycle Fretting Fatigue Assessment of Gas Turbine Engine Components

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
Kwai S. Chan ◽  
Michael P. Enright ◽  
Patrick J. Golden ◽  
Samir Naboulsi ◽  
Ramesh Chandra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Real Life ◽  
Fretting Fatigue ◽  
Gas Turbine Engine ◽  
Rotating Stall ◽  
Worst Case ◽  
Design Assessment ◽  
Turbine Engine ◽  
Engine Components

High-cycle fatigue (HCF) is arguably one of the costliest sources of in-service damage in military aircraft engines. HCF of turbine blades and disks can pose a significant engine risk because fatigue failure can result from resonant vibratory stresses sustained over a relatively short time. A common approach to mitigate HCF risk is to avoid dangerous resonant vibration modes (first bending and torsion modes, etc.) and instabilities (flutter and rotating stall) in the operating range. However, it might be impossible to avoid all the resonance for all flight conditions. In this paper, a methodology is presented to assess the influences of HCF loading on the fracture risk of gas turbine engine components subjected to fretting fatigue. The methodology is based on an integration of a global finite element analysis of the disk-blade assembly, numerical solution of the singular integral equations using the CAPRI (Contact Analysis for Profiles of Random Indenters) and Worst Case Fret methods, and risk assessment using the DARWIN (Design Assessment of Reliability with Inspection) probabilistic fracture mechanics code. The methodology is illustrated for an actual military engine disk under real life loading conditions.

scholarly journals Fully Loaded Factory Test of the CW251B12 Gas Turbine Engine

1990 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Engine Performance ◽  
Test Facility ◽  
Test Results ◽  
Turbine Engine ◽  
Engine Model ◽  
Factory Test ◽  
Industrial Gas Turbine

The fully loaded factory test of the CW251B12 45 MW class industrial gas turbine is described in this paper. This gas turbine is the latest uprating of the W251 series of engines. The main objectives of the factory test were the verification of the performance and the mechanical integrity of the new engine model. A brief description of the main features of the engine, the application of the first unit, the test facility, and the engine instrumentation used in the test is included. Details of the engine performance test results, telemetry test data results, and the hot end component metal temperature measurements are provided.

A Three Thousand-Hour Durability Test of a Marine Gas Turbine Engine

1972 ◽  
Author(s):  
L. M. Maas ◽  
C. L. Miller
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Industrial Applications ◽  
Prime Mover ◽  
Durability Test ◽  
Turbine Engine ◽  
Engine Components ◽  
Industrial Gas Turbine ◽  
Marine Environmental ◽  
Distillate Fuel

The Allison Model 501 industrial gas turbine engine has been used extensively as a prime mover for industrial applications. The areas of application to date have been in the driving of electrical generators and natural gas compressors. This paper describes a 3000-hr durability test of a modified Allison Model 501-K15 engine with saltwater ingestion, 100 F engine inlet air temperature, and operating on Navy distillate fuel. The purpose of the test was to verify that the engine was qualified for marine environmental applications. Performance data, photographs of the installation and engine components, and inspection results are included in this paper.

Fully Loaded Factory Test of the CW251B12 Gas Turbine Engine

1991 ◽  
Vol 113 (4) ◽  
pp. 482-487 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Engine Performance ◽  
Test Facility ◽  
Test Results ◽  
Turbine Engine ◽  
Engine Model ◽  
Factory Test ◽  
Industrial Gas Turbine

The fully loaded factory test of the CW251B12 45 MW class industrial gas turbine is described in this paper. This gas turbine is the latest uprating of the W251 series of engines. The main objectives of the factory test were the verification of the performance and the mechanical integrity of the new engine model. A brief description of the main features of the engine, the application of the first unit, the test facility, and the engine instrumentation used in the test is included. Details of the engine performance test results, telemetry test data results, and the hot end component metal temperature measurements are provided.

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