Advanced SearchSearch Tips
A Study on Variations of the Low Cycle Fatigue Life of a High Pressure Turbine Nozzle Caused by Inlet Temperature Profiles and Installation Conditions
facebook(new window)  Pirnt(new window) E-mail(new window) Excel Download
 Title & Authors
A Study on Variations of the Low Cycle Fatigue Life of a High Pressure Turbine Nozzle Caused by Inlet Temperature Profiles and Installation Conditions
Huh, Jae Sung; Kang, Young Seok; Rhee, Dong Ho; Seo, Do Young;
  PDF(new window)
High pressure components of a gas turbine engine must operate for a long life under severe conditions in order to maximize the performance and minimize the maintenance cost. Enhanced cooling design, thermal barrier coating techniques, and nickel-base superalloys have been applied for overcoming them and furthermore, material modeling, finite element analysis, statistical techniques, and etc. in design stage have been utilized widely. This article aims to evaluate the effects on the low cycle fatigue life of the high pressure turbine nozzle caused by different turbine inlet temperature profiles and installation conditions and to investigate the most favorable operating condition to the turbine nozzle. To achieve it, the structural analysis, which utilized the results of conjugate heat transfer analysis as loading boundary conditions, was performed and its results were the input for the assessment of low cycle fatigue life at several critical zones.
High Pressure Turbine Nozzle;Directionally Solidified Material;Turbine Inlet Temperature Profile;Installation Condition;Low Cycle Fatigue Life;Critical Plane Approach;
 Cited by
Halila, E. E., Lenahan, D. T. and Thomas, T. T., 1982, High Pressure Turbine Test Hardware Detailed Design Report, NASA CR-167955.

Mazur, Z., Hernandez-Rossette, A., Garcia-Illescas, R. and Luna-Ramirez, A., 2008, "Failure Analysis of a Gas Turbine Nozzle," Engineering Failure Analysis, Vol. 15, pp. 913-921. crossref(new window)

Arkhipov, A. N., Krasnovskiy, Y. E. and Putchkov, I. V., 2011, "Probabilistic Life Assessment of Turbine Vanes," Proceeding of ASME Turbo Expo 2011, GT2011-45841.

Mazur, Z. and Perez-Hernandez, E. B., 2011, "Gas Turbine Nozzle Life Assessment due to Thermal Fatigue," Proceedings of ASME Turbo Expo 2011, GT2011-45247.

Zheng, X. Q., Du, T. and Zhang, Y. J., 2011, "Prediction of Thermal Fatigue Life of a Turbine Nozzle Guide Vane," Journal of Zhejiang University- Science A(Applied Physics & Engineering), Vol. 12, No. 3, pp. 214-222. crossref(new window)

Huh, J. S., Rhee, D. H., Kang, Y. S., Seo, D. C. and Cha, B. J. 2014, "A Parametric Study on the High Pressure Turbine Nozzle of a Gas Turbine Engine for Structural Integrity," 8th China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems, W2E_5_145.

Socie, D. F. and Marquis, G. B., 1999, Multiaxial fatigue, SAE, Int.

You, B. R. and Lee, S. B., 1996, "A Critical Review on Multiaxial Fatigue Assessments of Metals," International Journal of Fatigue, Vol. 18, No. 4, pp. 235-244. crossref(new window)

Das, J. and Sivakumar, S. M., 2008, "Life Modeling of Notched CM247LC DS Nickel-Base Superalloy," Engineering Failure Analysis, Vol. 7, pp. 347-358.

Moore, Z. J., 2006, "Multiaxial Fatigue Life Prediction of a High Pressure Steam Turbine Rotor Using a Critical Plane Approach," Master thesis, Georgia Institute of Technology.

Kupkovits, P. A., 2008, "Thermomechanical Fatigue Behavior of the Directionally-Solidified Nickel-Base Superalloy CM247LC," Master Thesis, Georgia Institute of Technology.

Kang, Y. S., Rhee, D. H., Huh, J. S. and Cha, B. J., 2015, "Thermal Boundary Condition Effects on Conjugate Heat Transfer Analysis of High Pressure Turbine Nozzle," 2015 The 8th Asian-Pacific Conference on Aerospace Technology, 140223.

Military Handbook, 2002, "Engine Structural Integrity Program (ENSIP)," MIL-HDBK-1783B.