한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제19권5호
  • /
  • Pages.1-14
  • /
  • 2015
  • /
  • 1226-6027(pISSN)
  • /
  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
권호 표지
DOI QR코드

DOI QR Code

압축기 정익, 터빈 노즐 가변 메카니즘 및 제어기법 연구

Study on Variable Systems for Compressor and Turbine and its Control Scheme

  • Kim, Sangjo (Department of Aerospace Engineering, Pusan National University) ;
  • Kim, Donghyun (Department of Aerospace Engineering, Pusan National University) ;
  • Bae, Kyoungwook (Department of Aerospace Engineering, Pusan National University) ;
  • Kim, Dae-il (School of Mechanical Engineering, Pusan National University) ;
  • Son, Changmin (School of Mechanical Engineering, Pusan National University) ;
  • Kim, Kuisoon (Department of Aerospace Engineering, Pusan National University) ;
  • Lee, Daewoo (Department of Aerospace Engineering, Pusan National University) ;
  • Go, Jeungsang (School of Mechanical Engineering, Pusan National University) ;
  • Choi, Dong-Whan (Department of Aerospace Engineering, Inha University) ;
  • Kim, Myungho (The 4th R&D Institute, Agency for Defense Development) ;
  • Min, Seongki (The 4th R&D Institute, Agency for Defense Development)
  • 투고 : 2015.07.01
  • 심사 : 2015.08.21
  • 발행 : 2015.10.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

아음속에서 초음속까지 운용되어야 하는 초음속 터빈엔진의 경우, 엔진 운용 공기량이 범위가 넓고 추력 및 연료소모율 등의 엔진 성능에 대해 요구조건이 높으므로 가변시스템 및 이를 제어하기 위한 최적의 제어로직 개발이 반드시 필요하다. 본 연구에서는 압축기 가변 시스템이 적용된 가스터빈 성능해석 모델 및 제어기법을 개발하였다. 그리고 터빈 노즐 가변에 따른 엔진 운용 특성을 분석하였다. 또한 가변 시스템을 구동하는 액추에이터에 대한 개념 설계를 수행 하였다. 저바이패스비 혼합흐름 터보팬 엔진에 대한 탈설계점에서의 성능해석을 수행하였으며, 제어기법을 적용하여 탈설계점에서의 서지마진을 확보할 수 있었다.

In case of a gas turbine engine for supersonic operation, the engine have a wide range of operating inlet mass flow rate and required high performance such as thrust and fuel consumption. Therefore, variable system and its optimal control logic are essentially needed. In this work, a method for performance prediction of a gas turbine engine with variable system compressor and its control scheme were developed. Conceptual design of compact acuation system for the operation of the variable system was also conducted. The performance of a low-bypass ratio mixed flow turbofan engine was analyzed, and it was observed that the surge margin of the engine is improved at off-design condition by applying the control scheme.

키워드

참고문헌

  1. Rolls-Royce, The jet engine, 5th ed., Rolls-Royce plc, London, England, 2005.
  2. Gallar, L., Arias, M., Pachidis, V. and Singh, R., "Stochastic Axial Compressor Variable Geometry Schedule Optimisation," Aerospace Science and Technology, Vol. 15, No. 5, pp. 366-374, 2011. https://doi.org/10.1016/j.ast.2010.08.010
  3. Plencner, R.M., "Plotting Component Maps in the Navy/NASA Engine Program (NNEP) - A Method and its Usage," NASA TM 101433, 1989.
  4. Mallett, W.E. and Groesbeck, D.E., "Effects of Compressor Interstage Bleed and Adjustable Inlet Guide Vanes on Compressor Stall Characteristics of a High-pressure-ratio Turbojet Engine at Altitude," NASA RM E55G27, 1956.
  5. Barbosa, J.R., Silva F.J., Tomita, J.T. and Bringhenti, C., "Influence of Variable Geometry Transients on Gas Turbine Performance," ASME Turbo Expo 2011, Vancouver, Canada, GT2011-46565, June 2011.
  6. Bringhenti, C., Tomita, J.T., de Sousa Junior, F. and Barbosa, J.R., "Gas Turbine Performance Simulation Using an Optimized Axial Flow Compressor," ASME Turbo Expo 2006, Barcelona, Spain, GT2006-91225, May 2006.
  7. Gallar, L., Arias, M., Pachidis, V. and Pilidis, P., "Compressor Variable Geometry Schedule Optimisation Using Genetic Algorithms," ASME Turbo Expo 2009, Orlando, F.L., USA, GT2009-60049, June 2009.
  8. Shadaram, A., Fathi, A. and Azizi, R., "Optimization of Variable Stator's Angle for Off Design Compression Systems Using Streamline Curvature Method," ASME Turbo Expo 2009, Orlando, F.L., USA, GT2009-59772, June 2009.
  9. Kim, S.J., Kim, D.H., Kim, K., Son, C.M., Kim, Y.I. and Min, S.K., "An Approach for the Integrated Performance Analysis of a Small Turbofan Engine with Variable Inlet Guide and Variable Stator Vane," Journal of the Korean Society of Propulsion Engineers, Vol. 16, No. 4, pp. 23-32, 2012. https://doi.org/10.6108/KSPE.2012.16.4.023
  10. Kim, D., Kim, S., Kim, K., Son, C., Kim, Y.I. and Min, S., "A Study on the Performance Prediction Method for an Axial Compressor with Variable Inlet Guide Vane," Journal of the Korean Society of Propulsion Engineers, Vol. 16, No. 4, pp. 1-8, 2012. https://doi.org/10.6108/KSPE.2012.16.4.001
  11. Kim, D., Kim, S., Son, C., Kim, K., Kim, M. and Min, S., "Transient Performance Prediction of an Axial Compressor Considering VIGV Operation Speeds," Journal of Mechanical Science and Technology, Vol. 28, No. 10, pp. 4099-4107, 2014. https://doi.org/10.1007/s12206-014-0923-7
  12. Kim, S., Kim, D., Son, C., Kim, K., Kim, M. and Min, S., "New Profile Loss Model for Improved Prediction of Transonic Axial Flow Compressor Performance in Choking Region," ASME Turbo Expo 2015, Montreal, Canada, GT2015-42797, June 2015.
  13. Kang, Y.S., Park, T.C., Hwang, O.S. and Yang, S.S., "Experimental Research on Multi Stage Transonic Axial Compressor Performance Evaluation," Journal of Fluid Machinery, Vol. 14, No. 6, pp. 96-101, 2011.
  14. Steinke, R.J., "A Computer Code for Predicting Multistage Axial-Flow Compressor Performance by a Meanline Stage-Stacking Method," NASA TP 2020, 1982.
  15. Park, T.J., Yoon, S. and Baek J.H., "Performance Prediction Comparison of Multi-Stage Axial-Compressor by Stage-Stacking Method," 2001 Korea Society for Fluid Machinery Conference, Daejeon, Republic of Korea, pp. 143-148, Nov. 2001.
  16. Kim, J., Min, J., Cho, L., Gang, Y.S. and Cho, J., "Numerical Simulation of Steady and Unsteady High-Pressure Turbine Performance," 2013 KSAS conference, Jeongseon, Republic of Korea, pp.273-276, April 2013.
  17. Honeywell F124 Turbofan Engine Brochure, http://www51.honeywell.com/aero/portal/Common/Documents/myaerospacecatalog-d ocuments/Defense_Brochures-documents/F124_Engine.pdf, June 2015.
  18. NPSS Team, "NPSS User Guide Software Release: NPSS 2.4.1," Ohio Aerospace Institute, Cleveland, O.H., USA, 2012.
  19. Bae, K., Min, C., Cheon, B., Lee, C. and Lee, D., "Control System of Turbofan Engine with Variable Inlet Guide Vane," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 42, No. 3, pp. 237-242, 2014. https://doi.org/10.5139/JKSAS.2014.42.3.237
  20. Kim, M., Kim, H.H., Park, H.W., Go, J., Son, C., Kim, K. and Lee, D., "Displacement Amplification Output Device using Flexible Link," KR-A-10-2013-0093994, 2013.