항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제9권1호
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  • Pages.1-6
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  • 2015
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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7톤급 액체로켓엔진 산화제펌프 임계속도 해석

Critical Speed Analysis of a 7 Ton Class Liquid Rocket Engine Oxidizer Pump

  • 투고 : 2015.02.21
  • 심사 : 2015.03.31
  • 발행 : 2015.03.31
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초록

A critical speed analysis of oxidizer pump was peformed for a 7 ton class liquid rocket engine as the third stage engine of the Korea Space Launch Vehicle II. Based on the previously developed experimental 30 ton class turbopump and presently developing 75 ton class turbopump for the first and second stage rocket engine of Korea Space Launch Vehicle II, a layout and configuration of the 7 ton class turbopump rotor assembly are determined. A ball bearing stiffness analysis and rotordynamic analysis are performed for both of the bearing unloaded condition and loaded condition. Structural flexibility of the oxidizer pump casing is also included to predict critical speeds. From the numerical analysis, it is confirmed that the rotor system acquires sufficient separate margin of critical speed as a sub-critical rotor even though decrease of critical speed due to the casing structural flexibility.

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참고문헌

  1. Kim, J., Hong, S. S., Jeong, E. H., Choi, C. H., Jeon, S. M.,"Development of a Tur bopump for a 30 Ton Class Engine", Proceedings of the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, OH, 2007, AIAA 2007- 5516.
  2. Jeon, S. M., Kwak, H. D., Yoon, S. H., Kim, J.,"Rotordynamic Analysis of a Turbopump with the Casing Structural Flexibility", Journal of Propulsion and Power, Vol. 24, No. 3, May-June, 2008, pp. 433-436. https://doi.org/10.2514/1.33551
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  5. 홍순삼, 김진선, 김대진, 김진한, "75톤급 액체로 켓엔진용 터보펌프 조립체의 상사매질 성능시험", 한국추진공학회지, 제 15권, 제 2호, 2011, pp. 56-61.
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