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http://dx.doi.org/10.3795/KSME-C.2016.4.2.093

A Study on the Structural Integrity of the First Stage Turbine Blade Caused by Thermal Barrier Coatings and the Cooling Design of the Nozzle  

Huh, Jae Sung (Aero-propulsion division, Korea Aerospace Research Institute)
Kang, Young Seok (Aero-propulsion division, Korea Aerospace Research Institute)
Rhee, Dong Ho (Aero-propulsion division, Korea Aerospace Research Institute)
Publication Information
Transactions of the KSME C: Technology and Education / v.4, no.2, 2016 , pp. 93-99 More about this Journal
Abstract
High pressure nozzles and turbines of a gas turbine engine should be required to be operated under extreme operating conditions in order to maximize the performance. Engine manufactures have utilized nickel-base superalloys, enhanced cooling design, and thermal barrier coating techniques to overcome them and furthermore, material modeling, finite element analysis, optimization techniques, and etc. have been utilized widely for elaborate predictions. We aim to evaluate the effects on the low cycle fatigue life of the high pressure turbine blade caused by thermal barrier coatings and the cooling design of the endwall of the first stage turbine nozzle. To achieve it, the structural analysis, which utilized the results of conjugate heat transfer analysis as loading boundary conditions, was performed and then the results were the input for the assessment of low cycle fatigue life at several critical zones.
Keywords
Turbine Blade; Turbine Nozzle; Cooling Design; Thermal Barrier Coating; Low Cycle Fatigue;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
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