Engine Component Life Prediction Methodology for Conceptual Design Investigations

1986 ◽  
Author(s):  
John D. Cyrus
Keyword(s):  
Life Prediction ◽  
Preliminary Design ◽  
Design Decisions ◽  
Turbine Engine ◽  
Detailed Consideration ◽  
Engine Design ◽  
Engine Component ◽  
Fundamental Understanding ◽  
Engine Components ◽  
The Impact

The increasing emphasis on engine durability requires that an analytical capability be acquired to assess engine component lives during the conceptual/preliminary design phases. A generalized methodology has been developed to provide a fundamental understanding of the impact of engine design decisions, material selections, and a detailed consideration of engine usage for critical gas turbine engine components.

Life Prediction for Turbine Engine Components

Fatigue ◽  
1983 ◽  
pp. 353-375 ◽  
Author(s):  
T. Nicholas ◽  
J. M. Larsen
Keyword(s):  
Life Prediction ◽  
Turbine Engine ◽  
Engine Components

Automated Thermal and Stress Preliminary Analyses Applied to a Turbine Rotor

2016 ◽  
Author(s):  
Maxime Moret ◽  
Alexandre Delecourt ◽  
Hany Moustapha ◽  
Francois Garnier ◽  
Acher-Igal Abenhaim
Keyword(s):  
Design Process ◽  
Turbine Rotor ◽  
Tip Clearance ◽  
Conceptual System ◽  
Preliminary Design ◽  
Design Phase ◽  
Detailed Design ◽  
Turbine Engine ◽  
Cad Models ◽  
The Impact

The use of Multidisciplinary Design Optimization (MDO) techniques at the preliminary design phase (PMDO) of a gas turbine engine allows investing more effort at the pre-detailed phase in order to prevent the selection of an unsatisfactory concept early in the design process. Considering the impact of the turbine tip clearance on an engine’s efficiency, an accurate tool to predict the tip gap is a mandatory step towards the implementation of a full PMDO system for the turbine design. Tip clearance calculation is a good candidate for PMDO technique implementation considering that it implies various analyses conducted on both the rotor and stator. As a first step to the development of such tip clearance calculator satisfying PMDO principles, the present work explores the automation feasibility of the whole analysis phase of a turbine rotor preliminary design process and the potential increase in the accuracy of results and time gains. The proposed conceptual system integrates a thermal boundary conditions automated calculator and interacts with a simplified air system generator and with several conception tools based on parameterized CAD models. Great improvements were found when comparing this work’s analysis results with regular pre-detailed level tools, as they revealed to be close to the one generated by the detailed design tools used as target. Moreover, this design process revealed to be faster than a common preliminary design phase while leading to a reduction of time spent at the detailed design phase. By requiring fewer user inputs, this system decreases the risk of human errors while entirely leaving the important decisions to the designer.

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

2016 ◽  
Vol 66 (2) ◽  
pp. 193 ◽  
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>

The Method of Accounting for Loading Cycle Asymmetry in Gas Turbine Engine Components’ Cyclic Durability Analysis

2006 ◽  
Author(s):  
R. H. Muratov
Keyword(s):  
Strain Range ◽  
Cyclic Strain ◽  
Mean Stress ◽  
Turbine Engine ◽  
Transient Strain ◽  
High Durability ◽  
Durability Analysis ◽  
Cyclic Durability ◽  
Engine Components ◽  
The Impact

The proposed method has been demonstrated on the universal slopes equation (Manson 1965) and the modified universal slopes equation (Muralidharan & Manson 1998). New equations take into account independence of the transient strain range from the cycle mean stress, define more precisely the impact of the cycle mean stress upon the durability, take into account the impact of cycle mean strain plastic component upon the durability. The resulted equations have been validated with finite element analyses of smooth samples and full-scale parts, for which the results of cyclic tests in the conditions of asymmetric loading are available. The analyses have been performed employing an elastic-plastic approach using cyclic strain curves taken from original durability equations. The use of new equations ensured a good match between design and experimental durability values. Also, the new equations were used to plot Smith and Hay diagrams for low, mean and high durability. The resulted analytical diagrams represent a high quality illustration of the experimental diagrams found in the publications. The presented approach to the accounting for cycle mean stress and strain will also apply when using experimental cyclic durability curves specific for the material.

scholarly journals A Lifecycle Cost-Driven System Dynamics Approach for Considering Additive Re-Manufacturing or Repair in Aero-Engine Component Design

2019 ◽  
Vol 1 (1) ◽  
pp. 1343-1352
Author(s):  
Lydia Lawand ◽  
Khalil Al Handawi ◽  
Massimo Panarotto ◽  
Petter Andersson ◽  
Ola Isaksson ◽  
...  
Keyword(s):  
Additive Manufacturing ◽  
System Dynamics ◽  
Development Stage ◽  
Life Extension ◽  
Design Decisions ◽  
Component Design ◽  
Design Variables ◽  
Engine Component ◽  
Aero Engine ◽  
The Impact

AbstractAero-engine component design decisions should consider re-manufacturing and/or repair strategies and their impact on lifecycle cost. Existing design approaches do not account for alternative production technologies such as the use of additive manufacturing in life extension processes. This paper presents a modeling and optimization methodology for examining the impact of design decisions in the early development stage on component lifecycle cost during the in-service phase while considering the potential use of additive manufacturing in life extension strategies. Specifically, a system dynamics model is developed to assess different end-of-life scenarios. Finally, an optimization problem is formulated and solved to minimize lifecycle cost with respect to design variables related to re-manufacturing.

Surge-Induced Structural Loads in Gas Turbines

1980 ◽  
Vol 102 (1) ◽  
pp. 162-168 ◽  
Author(s):  
R. S. Mazzawy
Keyword(s):  
Gas Turbines ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Turbine Engine ◽  
Compression System ◽  
Engine Design ◽  
Steady State Levels ◽  
Flow Compression ◽  
Engine Components ◽  
Bypass Ratio

The axial flow compression system of a modern gas turbine engine normally delivers a large quantity of airflow at relatively high velocity. The sudden stoppage (and reversal) of this flow when an engine surges can result in structural loads in excess of steady state levels. These loads can be quite complex due to inherent asymmetry in the surge event. The increasing requirements for lighter weight engine structures, coupled with the higher pressure ratio cycles required for minimizing fuel consumption, make the accurate prediction of these loads an important part of the engine design process. This paper is aimed toward explaining the fluid mechanics of the surge phenomenon and its impact on engine structures. It offers relatively simple models for estimating surge-induced loads on various engine components. The basis for these models is an empirical correlation of surge-induced inlet overpressure based on engine pressure ratio and bypass ratio. An approximate estimate of the post-surge axial pressure distribution can be derived from this correlation by assuming that surge initiation occurs in the rear of the compression system.

High-Temperature Surface Measurements of Turbine Engine Components Using Thermographic Phosphors

1997 ◽  
Author(s):  
Sami Alaruri ◽  
Andy Brewington
Keyword(s):  
High Temperature ◽  
Gas Flow ◽  
Single Point ◽  
Temperature Measurements ◽  
Turbine Engine ◽  
Thermographic Phosphors ◽  
Engine Component ◽  
Surface Measurements ◽  
Engine Components ◽  
Temperature Surface

A laser-based system for single point high-temperature measurements of turbine engine component surfaces coated with thermographic phosphors is described. Decay lifetime calibration measurements obtained for Y2O3:Eu over the temperature range ∼530–1000°C are presented. Further, the results obtained from a coupon placed in the outlet gas flow of an atmospheric-combustor are described.

Size- and Temperature-Dependent Collision and Deposition Model for Micron-Sized Sand Particles

2019 ◽  
Vol 141 (3) ◽  
Author(s):  
Kuahai Yu ◽  
Danesh Tafti
Keyword(s):  
Gas Turbine ◽  
Recovery Process ◽  
Recovery Stage ◽  
Turbine Engine ◽  
Collision Model ◽  
Size Dependent ◽  
Plastic Stage ◽  
Sand Particles ◽  
Engine Components ◽  
The Impact

Sand ingestion and deposition in gas turbine engine components can lead to several operational hazards. This paper discusses a physics-based model for modeling the impact, deposition, and sticking of sand particles to surfaces. The collision model includes both normal and tangential components of impact. The normal collision model divides the impact process into three stages, the elastic stage, the elastic–plastic stage, and full plastic stage, and the recovery process is assumed to be fully elastic. The adhesion loss in the recovery stage is described using Timoshenko's model and Tsai's model, and shows that the two models are consistent under certain conditions. Plastic deformation losses of surface asperities are also considered for particle–wall collisions. The normal impact model is supplemented by an impulse-based tangential model, which includes both sliding and rolling frictions. Sand properties are characterized by size and temperature dependencies. The predicted coefficient of restitution (COR) of micron-sized sand particles is in very good agreement with experimental data at room temperature and at higher temperatures from 1073 K to 1340 K. The predicted COR decreases rapidly at temperatures above 1340 K. There is a strong interplay between the size-dependent properties of micron sand particles and the temperature dependency of yield stress on the collision and deposition characteristics. This is the first physics-based high temperature model including translation and rotation of micron-sized sand particles with sliding and rolling modes in the gas turbine literature.

scholarly journals Contemporary approaches to research supporting the development of microturbine power generation systems

2018 ◽  
pp. 72-79
Author(s):  
A. S. Kosoy ◽  
S. V. Monin ◽  
M. V. Sinkevich
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Low Cost ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Design ◽  
Testing Facility ◽  
Engine Components ◽  
Power Generation Systems

The paper provides an analysis of how much it is possible to improve the efficiency of low-power gas-turbine engines. We show that refining those features of the main blading section units that affect the gas dynamics significantly enhances engine performance. We present a new concept of developing highly efficient turbomachinery, pumps and propellers using modern additive manufacturing technology. We describe a unique research and testing facility for studies, per-node refinement and testing concerning gas-turbine engine components, which should ensure low cost and high efficiency of gas-turbine engine design.

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