Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Design Study of a Simulation Duct for Gas Turbine Engine Operations

가스터빈엔진을 모의하기 위한 시뮬레이션덕트 설계 연구

  • Im, Ju Hyun (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Kim, Sun Je (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Kim, Myung Ho (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Kim, You Il (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Kim, Yeong Ryeon (The 4th R&D Institute - 5th Directorate, Agency for Defense Development)
  • Received : 2018.06.26
  • Accepted : 2018.12.03
  • Published : 2019.02.01
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Abstract

A design study of gas turbine engine simulation duct was conducted to investigate the operating characteristics and control gain tunning of the Altitude Engine Test Facility(AETF). The simulation duct design involved testing variable spike nozzle and ISO standard choking nozzle to verify the measurements such as mass flow rate and thrust. The simulation duct air flow area was designed to satisfy Ma 0.4 at the aerodynamic interface plane(AIP) at engine design condition. The test conditions for verifying the AETF controls and measurement devices were deduced from 1D analysis and CFD calculation results. The spike-cone driving part was designed to withstand the applied aero-load, and satisfy the axial traversing speed of 10 mm/s at whole operation envelops.

가스터빈엔진 고도시험설비 운용특성탐색 및 설비튜닝 연구와 유량/추력 측정방안 검증을 위한 엔진 시뮬레이션덕트 설계 연구를 수행하였다. 설비 운용특성 검증은 배압/추력 제어가 필요하므로 Spikecone type의 가변노즐을 적용하였으며, 유량검증용 ISO 쵸킹노즐의 추가장착이 가능토록 설계하였다. 시뮬레이션덕트 주유로 면적은 1D Sizing으로 결정하고, 노즐면적변화에 따른 시뮬레이션덕트 내부 유동특성은 1D/CFD 해석으로 조사하였으며, 해석결과로부터 설비운용특성 탐색 및 유량/추력 검증시험을 위한 공기공급부 시험조건을 도출하였다. Spike 노즐 구동부는 시험 전운용 구간에서 공력하중조건을 견디도록 모터, 리니어 볼스크류 등의 부품모델을 선정하였으며, 시험 시 10 mm/s의 이송속도가 가능하도록 설계하였다.

Keywords

Acknowledgement

Grant : 무인항공기용 터보팬 코어엔진 시제개발 및 성능평가

Supported by : 방위사업청

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