한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제22권3호
  • /
  • Pages.119-127
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  • 2018
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  • 1226-6027(pISSN)
  • /
  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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왕복동 엔진의 고도성능시험을 위한 시험장치 개발

Development of Test Stand for Altitude Test of Reciprocating Engine

  • Lee, Kyung-Jae (Aeropropulsion Office, Korea Aerospace Research Institute) ;
  • Yang, Inyoung (Aeropropulsion Office, Korea Aerospace Research Institute) ;
  • Kim, Chun Taek (Aeropropulsion Office, Korea Aerospace Research Institute) ;
  • Kim, Dongsik (R&D Division, Tec-Eye system Engineering) ;
  • Baek, Cheulwoo (The 7th R&D Institute 3th Directorate 2th team, Agency for Defence Development) ;
  • Yang, Gyaebyung (The 7th R&D Institute 3th Directorate 2th team, Agency for Defence Development)
  • 투고 : 2017.06.04
  • 심사 : 2017.10.25
  • 발행 : 2018.06.01
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초록

중소형급 무인 항공기에 활용되고 있는 왕복동 엔진의 고도시험을 위한 시험 장치를 설계 및 제작하였으며, 예비 성능시험과 계산을 통하여 활용가능 여부를 판단해 보았다. 시험 장치는 현재 한국항공우주연구원에서 운용 중인 터보샤프트 엔진 고도시험설비에서 활용이 가능하도록 구성하였으며, 왕복동 엔진의 고도시험을 수행하기 위한 각종 제한조건을 가정하고 이를 만족할 수 있도록 개발하였다. 특히 대유량의 공기와 연료가 필요한 터보샤프트 엔진에 비하여 적은 유량이 필요한 왕복동 엔진의 성능시험을 위하여 고도 및 비행 마하수 조건의 제어가 가능하도록 장치를 구성하였으며, 엔진에 공급되는 연료의 온도를 보다 손쉽게 조절할 수 있는 장치들을 개발하였다.

A test stand for an altitude test of reciprocating engine was designed, manufactured and validated by preliminary tests and simple calculations. The test stand was designed to interface with the altitude turbo-shaft engine test facility of Korea Aerospace Research Institute. Many limiting conditions for altitude test of reciprocating engine were assumed and the test stand was developed to satisfy these limitations. The test stand design was focused especially on the altitude, Mach number and fuel temperature control for reciprocating engine altitude tests with smaller air and fuel flow than those of turbo shaft engines.

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참고문헌

  1. Peter, D. and Darren, L., Unmanned Vehicles HANDBOOK 2008, 1st ed., A Shephard Press Publication, 2008.
  2. Kang, Y.S., Lim, B.J. and Kim, J.K., "Establishment of Multi-Stage Turbocharger Layout for HALE UAV Engine and Its Performance Assessment," The KSFM Journal of Fluid Machinery, Vol. 18, No. 6, pp. 31-36, 2015. https://doi.org/10.5293/kfma.2015.18.6.031
  3. Kim, Y.R., Choi, Y. and Lee, J.H., "Start and Idle Combustion Characteristics of Hydrogen Engine for the HALE UAV," Journal of the Korean Institute of Gas, Vol. 19, No. 6, pp. 22-27, 2015. https://doi.org/10.7842/KIGAS.2015.19.6.22
  4. Lee, K.J., Yang, I.Y., Kim C.T. and Yang, S.S., "Altitude Test Facility for Gas Turbine Engine of Korea Aerospace Research Institute," KSPE Fall Conference, Jungsun, Korea, pp. 259-267, 2014.
  5. Swamee, P. and Jain, A., "Explicit equation for pipe-flow problems," Journal of the Hydraulics Division(ASCE), Vol. 102, No. 5, pp. 657-664, 1976.
  6. Coordinating Research Council, Handbook of Aviation Fuel Properties, Society of Automotive Engineers, CRC Report No. 530, 1983.
  7. Yunus A. Cengel, Heat Transfer: A Practical Approach, 2nd ed., McGraw-Hill, 2003.
  8. ASME PTE COMMITTEE, Gas Turbine Aircraft Engines-Performance Test Codes, ASME PTC 55-2013, 2013.