Transactions of the Korean Society of Mechanical Engineers B (대한기계학회논문집B)

The Korean Society of Mechanical Engineers (대한기계학회)
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Aerodynamic Rig Test of Radial Turbine for APU

APU용 구심터빈의 공력리그시험

  • Kang, Jeong-Seek (Turboshaft Engine Team, Korea Aerospace Research Institute) ;
  • Lim, Byeung-Jun (Turboshaft Engine Team, Korea Aerospace Research Institute) ;
  • Ahn, Iee-Ki (Rotorcraft Technology Division, Korea Aerospace Research Institute)
  • 강정식 (한국항공우주연구원 터보샤프트엔진팀) ;
  • 임병준 (한국항공우주연구원 터보샤프트엔진팀) ;
  • 안이기 (한국항공우주연구원 회전익기술실)
  • Received : 2011.03.11
  • Accepted : 2012.10.11
  • Published : 2013.01.01
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Abstract

An aerodynamic rig test of a radial turbine for an auxiliary power unit (APU) was performed at a high-temperature turbine test facility at the Korea Aerospace Research Institute. The pressure ratio, Mach number, and flow coefficient in the rig test are the same as those under normal engine operation conditions. The design pressure ratio is 3.096, design test speed is 34909 rpm, and turbine inlet temperature is $160^{\circ}C$. The turbine has airfoil-type nozzles, and the diameter of the turbine wheel is 175.74 mm. The turbine map is experimentally measured, and the detailed flow at the turbine inlet is measured. The pressure distribution in the nozzle at both the hub and the shroud sides and the pressure distribution along the shroud casing of the turbine wheel were measured, and this confirmed that the expansion process in the turbine wheel is acceptable.

본 연구는 보조동력장치에 적용되는 구심터빈의 공력성능시험을 한국항공우주연구원의 고온 터빈 시험리그에서 수행한 결과이다. 리그시험을 위하여 터빈의 형상은 동일하되 팽창비, 마하수 및 유량계수는 실제 엔진과 동일한 값이 되도록 상사법칙을 적용하여 시험하였다. 설계 팽창비는 3.096이며, 상사된 설계회전수는 34909 rpm이고 상사된 터빈 입구온도는 $160^{\circ}C$이다. 터빈의 입구에는 익형 형상의 노즐이 설치되었으며 터빈 휠의 직경은 175.74mm이다. 시험을 통하여 터빈의 성능지도가 생성되었으며 터빈 입구에서의 상세 유동이 측정되었다. 노즐의 허브면에서 측정한 압력과 노즐의 쉬라우드 면과 터빈 휠 케이싱에서 측정한 압력 분포를 볼 때 터빈 내부에서의 팽창과정이 적절함을 확인할 수 있었다.

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References

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