Quantification of Low-Cycle Fatigue Life for a Gas Turbine Compressor Vane Carrier Under Varying Operating Conditions

2021 ◽  
Author(s):  
Zixi Han ◽  
Zixian Jiang ◽  
Sophie Ehrt ◽  
Mian Li
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Operating Conditions ◽  
Cycle Fatigue ◽  
Gas Turbine Compressor

Low-Cycle Fatigue Lifetime Estimation and Predictive Maintenance for a Gas Turbine Compressor Vane Carrier under Varying Operating Conditions

2021 ◽  
pp. 1-47
Author(s):  
Zixi Han ◽  
Zixian Jiang ◽  
Sophie Ehrt ◽  
Mian Li
Keyword(s):  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Operating Conditions ◽  
Predictive Maintenance ◽  
Cycle Fatigue ◽  
Operating Cycle ◽  
Miner’S Rule ◽  
Miner's Rule ◽  
Gas Turbine Compressor ◽  
Operational Data

Abstract In the age of Industry 4.0, the capability of health management is critical to the design and maintenance of gas turbines. This work presents a probabilistic method to estimate the low-cycle fatigue (LCF) life of a gas turbine compressor vane carrier (CVC) under varying operating conditions. Sensitivity analysis based on finite element analysis (FEA) indicates that an operating cycle can be characterized by three predominant contributors to the LCF damage of the CVC among multiple parameters of an operating cycle. Two surrogate models mapping these three features to equivalent stresses are then built for fast computation of the LCF damage. Miner's rule is applied in a probabilistic way to calculate the distribution of accumulated LCF damage over varying operating cycles. Finally, the probabilistic LCF life of the CVC is assessed using real operational data. The proposed approach includes two novel solutions: 1) a new data processing technique inspired by the cumulative sum (CUSUM) control chart to identify the first ramp-up period as well as the shutdown period of each cycle from noisy operational data; 2) the sequential convolution strategy adapted from Miner's rule to compute the probability distribution of accumulated LCF damage (and hence LCF life) from the single-cycle damage distribution, and an approximative quick estimation method to reduce computational expense. Both the offline application for design and online implementation for predictive maintenance show that the expected LCF life at a critical location of the CVC is significantly longer than the deterministically assessed life.

3D Crack Growth Analysis and Its Correlation With Experiments for Critical Turbine Components Under an International Collaborative Program

2008 ◽  
Author(s):  
J. Hou ◽  
J. Dubke ◽  
K. Barlow ◽  
S. Slater ◽  
L. Harris ◽  
...  
Keyword(s):  
Fatigue Life ◽  
Crack Growth ◽  
Low Cycle Fatigue ◽  
Operating Conditions ◽  
Cycle Fatigue ◽  
3D Crack Growth ◽  
International Collaborative ◽  
2D And 3D ◽  
Growth Analyses ◽  
Stress Analyses

Following a reanalysis of the original material data plus supplementary Low Cycle Fatigue (LCF) specimen testing, an Original Equipment Manufacturer (OEM) reduced the low cycle fatigue life limits for a number of turbine components. To ascertain the validity of the new life limits, an international collaborative spin rig test program was initiated to provide more accurate low cycle fatigue life limits. The program covered a broad range of activities including, Finite Element (FE) stress analyses, cyclic spin rig testing, fractographic assessment and fatigue crack growth (FCG) analyses. This paper describes the 2D and 3D crack growth analyses of critical turbine components in a turboprop gas turbine engine, comparison of predicted results obtained using different software and also correlations with spin test results from the program. First, FE stress analyses of selected turbine components were carried out under both engine operating conditions and spin-rig test configurations in order to determine the maximum and minimum operating speeds required to match the stress ranges at the critical location specified by the OEM under engine operating conditions. Second, 2D and 3D crack growth analyses were performed independently by three organisations for a disk bolthole using the state-of-the-art software. Third, the predictions from different software were compared, and the relative technical merits of each software were evaluated. Finally, the predicted results were correlated against the striation counts determined by the OEM from the results of spin rig tests.

Advanced Models for Fatigue Life Estimation of Combustor Components for Gas Turbine Application

2019 ◽  
Author(s):  
Dileep Sivarama Iyer ◽  
Nikhil Chandran Pillai
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Fatigue Damage ◽  
Low Cycle Fatigue ◽  
Damage Model ◽  
Multiaxial Fatigue ◽  
Universal Method ◽  
Cycle Fatigue ◽  
Operating Cycle ◽  
Experimental Values

Abstract Modern day combustors operate at very high temperatures which are close to combustor material softening temperatures. At the same time, to meet stringent emission legislations there is a strong drive to improve upon the rich burn combustor technology or shift to advanced lean burn combustor technologies. One of the key driver to improve emission is to save the cooling air budget and use the saved air for primary combustion but this approach would require more advanced and efficient cooling techniques. Fan shaped effusion cooling technology is a very promising technique as it offers high film cooling effectiveness. However, complex cooling features associated with this technology can lead to higher stress concertation and localized triaxial stress state. This stressstrain field in combination with a typical gas turbine engine operating cycle makes such effusion holes highly vulnerable to the thermo-mechanical fatigue failure. Hence to ensure the safety and reliability of combustor liners with such innovative features, it is essential to have thorough understanding of the stress-strain field in the vicinity and accurate prediction of life to first crack. The biggest challenge the designers and engineers face while predicting the initiation life of a structure is selecting the appropriate fatigue damage model for an application. This is due to following reasons: (a) The scatter in fatigue life predicted using different models and experimental values are very huge (b) There is no general universal method which can predict the multiaxial fatigue life accurately for all the materials and loading conditions (c) No general consensus exits among the researchers on which model have to be used for a particular application, material, loading and geometry (d) Application level studies are seldom available on this subject, most of the studies are restricted to laboratory level specimens with very limited implications to industry. Ideally, the fatigue damage model which has to be used for a particular application has to be validated through experiments. To meet this objective, several test specimens featuring novel fan shaped hole geometries were mass-produced using state of the art laser drilling technology. All these specimens were subjected to strain controlled isothermal low cycle fatigue test and the cycles to crack initiation was monitored using potential drop method. Six different multiaxial fatigue damage models (which can be used in low cycle fatigue regime) viz. Walker model, Smith Watson and Topper model (SWT), Fatemi Socie model (FS), Wang and Brown model (WB), Shang model (SW) and Xu model were selected and the life estimated by these models were compared with the experimental values. From the study it is observed that Xu model in which the damage parameter is built using the concept of shear strain energy looks most promising for this application.

The Study on Failure Behavior and Low Cycle Fatigue Life of Hot Gas Casing for Gas Turbine

2007 ◽  
pp. 499-502
Author(s):  
Jae Hoon Kim ◽  
Duck Hoi Kim ◽  
Kyoung Joo Kim ◽  
Woo Sung Sim ◽  
Young Shin Lee ◽  
...  
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Failure Behavior ◽  
Cycle Fatigue ◽  
Hot Gas

Calculation of low cycle fatigue life for gas-turbine engine critical parts

2017 ◽  
Vol 60 (3) ◽  
pp. 421-427
Author(s):  
A. V. Pakhomenkov ◽  
R. A. Azimov ◽  
S. A. Bukatyi
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Gas Turbine Engine ◽  
Cycle Fatigue ◽  
Turbine Engine

Low-cycle fatigue life assessment for gas turbine engine disks under flight cycle conditions

2009 ◽  
Vol 41 (1) ◽  
pp. 102-105 ◽  
Author(s):  
K. D. Karimbaev ◽  
A. N. Servetnik
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Cycle Fatigue ◽  
Turbine Engine ◽  
Fatigue Life Assessment

scholarly journals THE EFFECT OF NOTCHES ON THE FATIGUE LIFE OF A NICKEL-BASE GAS TURBINE DISK MATERIAL

2018 ◽  
Vol 20 ◽  
pp. 34-42 ◽  
Author(s):  
Robert Eriksson ◽  
Johan Moverare ◽  
Zhe Chen ◽  
Kjell Simonsson
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Notch Root ◽  
Strain Range ◽  
Compact Tension ◽  
Critical Distance ◽  
Cycle Fatigue ◽  
Plastic Strain Range ◽  
Life Model

Gas turbine disks carry significant load under high temperatures and may be subject to fatigue failure. Disks contain several notches in the form of the fir tree blade attachments. Low cycle fatigue tests were performed on blunt notch compact tension specimens made from alloy 718. The results indicated that notch support needed to be incorporated not to cause an overly conservative life prediction. The notch support diminished as the plastic strain range decreased, indicating that notch support is only present in the low cycle fatigue regime. A critical distance approach was applied to account for the notch support. An equation relating the critical distance to the notch root stress was derived. The chosen life model was formulated in terms of a variation on the Smith–Watson–Topper (SWT) parameter. The modified SWT parameter taken at the critical distance was used in a life model calibrated for smooth specimens to successfully predict the fatigue life of notched specimens.

Sign in / Sign up

Export Citation Format

Share Document