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http://dx.doi.org/10.6108/KSPE.2013.17.4.025

Effect of Shroud Split on the Performance of a Turbopump Turbine Rotor  

Lee, Hanggi (Turbopump Team, Korea Aerospace Research Institute)
Jeong, Eunhwan (Turbopump Team, Korea Aerospace Research Institute)
Park, Pyungoo (Turbopump Team, Korea Aerospace Research Institute)
Yoon, Sukhwan (Turbopump Team, Korea Aerospace Research Institute)
Kim, Jinhan (Turbopump Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.17, no.4, 2013 , pp. 25-31 More about this Journal
Abstract
A blisk with rotor shroud is usually adopted in LRE turbine to maximize its performance. However it experiences the severe thermal load and resulting damage during engine stating and stop. Shroud splitting is devised to relieve the thermal stress on the turbine rotor. Structural analysis confirmed the reduction of plastic strain at the blade hub and tip. However, split gap at the rotor shroud entails additional tip leakage and results performance degradation. In order to assess the effect of shroud split on the turbine performance, tests have been performed for various settings of shroud split. For the maximum number of shroud splitting, measured efficiency reduction ratio was 2.65% to the value of original shape rotor.
Keywords
Supersonic Impulse Turbine; Split; Shroud; Blisk; Leakage;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
연도 인용수 순위
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