Stress-Rupture Characterization in Nickel-Based Superalloy Gas Turbine 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.

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

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2020-0037 ◽

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.

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An Integrated Approach for Gas Turbine Engine Simulation

10.1115/imece2000-1349 ◽

2000 ◽

Author(s):

Zhiwu Xie ◽

Ming Su ◽

Shilie Weng

Keyword(s):

Gas Turbine ◽

Local Area Network ◽

Integrated Approach ◽

Local Area ◽

Gas Turbine Engine ◽

Future Research ◽

Area Network ◽

Turbine Engine ◽

Engine Simulation ◽

Engine Components

Abstract The static and transient performance of a gas turbine engine is determined by both the characteristics of the engine components and their interactions. This paper presents a generalized simulation framework that enables the integration of different component and system simulation codes. The concept of engine simulation integration and its implementation model is described. The model is designed as an object-oriented system, in which various simulation tasks are assigned to individual software components that interact with each other. A new design rationale called “message-based modeling” and its resulting class structure is presented and analyzed. The object model is implemented within a heterogeneous network environment. To demonstrate its flexibility, the codes that deal with different engine components are separately programmed on different computers running various operating systems. These components communicate with each other via a CORBA compliant ORB, which simulates the overall performance of an engine system. The resulting system has been tested on a Local Area Network (LAN) to simulate the transient response of a three-shaft gas turbine engine, subject to small fuel step perturbations. The simulation results for various network configurations are presented. It is evident that in contrast to a standalone computer simulation, the distributed implementation requires much longer simulation time. This difference of simulation efficiency is analyzed and explained. The limitations of this endeavor, along with some future research topics, are also reported in this paper.

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Gas Turbine Engine Components

Gas Turbine Performance ◽

10.1002/9780470774533.ch5 ◽

2008 ◽

pp. 159-291 ◽

Cited By ~ 2

Keyword(s):

Gas Turbine ◽

Gas Turbine Engine ◽

Turbine Engine ◽

Engine Components

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Ceramic Composites for Gas Turbine Engines via a New Process

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery ◽

10.1115/89-gt-316 ◽

1989 ◽

Cited By ~ 2

Author(s):

G. H. Schiroky ◽

A. W. Urquhart ◽

B. W. Sorenson

Keyword(s):

Gas Turbine ◽

Joint Venture ◽

New Technology ◽

Ceramic Composites ◽

Gas Turbine Engine ◽

Molten Metals ◽

Oxidation Reactions ◽

Turbine Engine ◽

New Process ◽

Engine Components

A new process for ceramic composites involves the growth of ceramic matrices through shaped preforms using directed oxidation reactions of molten metals. The preforms may consist of reinforcing fibers, whiskers, platelets, or particles, as needed to produce the desired properties in the finished component. This new technology is being developed by Lanxide Corporation and is being applied to gas turbine engine components by Du Pont Lanxide Composites Inc., a joint venture. The paper includes a description of the technology and a discussion of the status of its application to materials for gas turbine engine components.

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Experimental and Numerical Correlation of Impact of Spherical Projectile for Damage Analysis of Aero Engine Component

Defence Science Journal ◽

10.14429/dsj.66.9130 ◽

2016 ◽

Vol 66 (2) ◽

pp. 193 ◽

Cited By ~ 2

Author(s):

Anuradha Nayak Majila ◽

Rajeev Jain ◽

Chandru Fernando D. ◽

S. Ramachandra

Keyword(s):

Finite Element ◽

Gas Turbine ◽

Gas Turbine Engine ◽

Metallographic Analysis ◽

Damage Analysis ◽

Alloy Plate ◽

Turbine Engine ◽

Aero Engine ◽

Engine Components ◽

The Impact

<p>Studies the impact response of flat Titanium alloy plate against spherical projectile for damage analysis of aero engine components using experimental and finite element techniques. Compressed gas gun has been used to impart speed to spherical projectile at various impact velocities for damage studies. Crater dimensions (diameter and depth) obtained due to impact have been compared with finite element results using commercially available explicit finite element method code LS-DYNA. Strain hardening, high strain rate and thermal softening effect along with damage parameters have been considered using modified Johnson-Cook material model of LS-DYNA. Metallographic analysis has been performed on the indented specimen. This analysis is useful to study failure analysis of gas turbine engine components subjected to domestic object damage of gas turbine engine. </p><p> </p>

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Gas Turbine Engine Disk Retirement-for-Cause: An Application of Fracture Mechanics and NDE

Volume 1B: General ◽

10.1115/80-gt-127 ◽

1980 ◽

Cited By ~ 2

Author(s):

C. G. Annis ◽

M. C. VanWanderham ◽

J. A. Harris ◽

D. L. Sims

Keyword(s):

Fracture Mechanics ◽

Gas Turbine ◽

Life Cycle Cost ◽

Energy Savings ◽

Cost Savings ◽

Gas Turbine Engine ◽

Turbine Engine ◽

Turbine Disks ◽

Full Life ◽

Engine Components

Historically, gas turbine engine disks are retired when they accrue an analytically determined lifetime where the first fatigue crack per 1000 disks could be expected. By definition then, 99.9 percent of these components are being retired prematurely. Retirement-for-Cause (RFC) is a procedure, based on Fracture Mechanics, which would allow safe utilization of the full life capacities of each individual disk. Since gas turbine disks are among the most costly of engine components, adopting a RFC philosophy could result in substantial systems life cycle cost savings. These would accrue from reduced replacement costs, conservation of strategic materials such as cobalt, and energy savings.

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