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http://dx.doi.org/10.5139/JKSAS.2004.32.3.058

Transient Heat Transfer and Structural Analyses for the Turbopump Turbine of a Liquid Rocket Engine  

Yoo, Jae-Han (한국과학기술원 항공우주공학과 대학원)
Choi, Ji-Hoon (삼성전자 DA연구소 요소기술 그룹)
Lee, In (한국과학기술원 항공우주공학과)
Han, Jae-Hung (한국과학기술원 항공우주공학과)
Jeon, Seong-Min (한국항공우주연구원)
Kim, Jin-Han (한국항공우주연구원)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.32, no.3, 2004 , pp. 58-65 More about this Journal
Abstract
Thermal and structural finite element analyses were performed for the turbopump turbine bladed disk model with shroud of a liquid rocket engine. The only 1/80 part model was analyzed which consists of 3D eight node isoparametric solid elements. The applied loading history consists of a startup condition with a thermal spike and a steady state. Heat transfer coefficient on the blade was predicted using the commercial Navier-Stokes solver, Fluent. Transient thermal responses during startup and steady states were calculated using a 3D finite element code developed. Maximum stress and shroud tip displacement under the influence of centrifugal and thermal loading were also determined.
Keywords
turbopump; turbine; transient heat transfer; structural analyses; Fluent; FEM;
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