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http://dx.doi.org/10.5293/kfma.2015.18.6.037

Conjugate Heat Transfer Analysis of High Pressure Turbine with Secondary Flow Path and Thermal Barrier Coating  

Kang, Young-Seok (Korea Aerospace Research Institute, Engine Components Research Team)
Rhee, Dong Ho (Korea Aerospace Research Institute, Engine Components Research Team)
Cha, Bong Jun (Korea Aerospace Research Institute, Engine Components Research Team)
Publication Information
The KSFM Journal of Fluid Machinery / v.18, no.6, 2015 , pp. 37-44 More about this Journal
Abstract
Conjugate heat analysis on a high pressure turbine stage including secondary flow paths has been carried out. The secondary flow paths were designed to be located in front of the nozzle and between the nozzle and rotor domains. Thermal boundary conditions such as empirical based temperature or heat transfer coefficient were specified at nozzle and rotor solid domains. To create heat transfer interface between the nozzle solid domain and the rotor fluid domain, frozen rotor with automatic pitch control was used assuming that there is little temperature variation along the circumferential direction at the nozzle solid and rotor fluid domain interface. The simulation results showed that secondary flow injected from the secondary flow path not only prevents main flow from penetrating into the secondary flow path, but also effectively cools down the nozzle and rotor surfaces. Also thermal barrier coating with different thickness was numerically implemented on the nozzle surface. The thermal barrier coating further reduces temperature gradient over the entire nozzle surface as well as the overall temperature level.
Keywords
Conjugate Heat Analysis; Cooled Turbine; High-Pressure Turbine; Secondary Flow Path; Thermal Barrier Coating;
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Times Cited By KSCI : 1  (Citation Analysis)
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