Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Optimal Design for the Rotor Overlap of a Supersonic Impulse Turbine to Improve the Performance

초음속 충동형 터빈 성능개선을 위한 동익 오버랩 최적설계

  • Cho, Jongjae (Advanced Technology Center, Samsung Techwin) ;
  • Shin, Bong Gun (Advanced Technology Center, Samsung Techwin) ;
  • Kim, Kuisoon (Department of Aerospace Engineering, Pusan National University) ;
  • Jeong, Eunhwan (Turbopump Group, Korea Aerospace Research Institute)
  • Received : 2012.11.30
  • Accepted : 2014.01.03
  • Published : 2014.02.01
Download PDF
⟨ Previous Next ⟩

Abstract

In a supersonic turbine, A rotor overlap technique reduced the chance of chocking in the rotor passage, and made the design pressure ratio satisfied. However, the technique also made additional losses, like a pumping loss, expansion loss, etc. Therefore, an approximate optimization technique was appled to find the optimal shape of overlap which maximizes the improvement of the turbine performance. The design variables were shape factors of a rotor overlap. An optimal design for rotor overlap reduces leakage mass flow rate at tip clearance by about 50% and increases about 4% of total-static efficiency compared with the base model. It was found that the most effective design variable is the tip overlap and that the hub overlap size is the lowest.

초음속 터빈에서는 동익 유로에서의 질식 가능성을 줄이며, 설계 압력비를 구현할 수 있도록 한다. 하지만 동익 오버랩을 적용하면, 펌핑손실, 확산손실 등의 추가적인 손실이 동반된다. 따라서 터빈성능을 극대화하기 위한 최적 오버랩 형상을 찾기 위해 근사최적화 기법을 적용하였다. 설계변수는 동익 오버랩의 형상변수이다. 최적설계 결과, 기준모델 대비 팁 누설유량은 약 50% 감소하였으며, 정효율은 약 4% 증가하였다. 팁 오버랩 크기가 성능에 미치는 영향이 크게 나타난 반면, 허브 오버랩 크기가 성능에 미치는 영향은 작게 나타났다.

Keywords

References

  1. Kim, J.H., Hong, S.S., Jeong, E.H., Choi. C.H., and Jeon, S.M., "Development Status of a Turbopump for 30-ton Thrust Level of Engine," 2005 the Korean Society of Propulsion Engineers Fall Conference, pp. 375-383, 2005.
  2. Stratford, B.S. and Sansome, G.E., "Theory and Tunnel Tests of Rotor Blades for Supersonic Turbines," Aeronautical Research Council Reports and Memoranda, R.&M. No. 3275, 1962.
  3. Kalmykovi, C.P., "Calculation of Gas dynamic and Geometric Parameters of Turbine," HYSA-99-S0001, 1999.
  4. Ovsyanikov, B.V. and Borovsky, B.I., "Theory and Calculation of Liquid Propellant Rocket Engine Pumps," Mashinostroyenie, Moscow, 1986.
  5. Kurzrock, J.W., "Experimental Investigation of Supersonic Turbine Performance," 89-GT-238, Gas Turbine and Aeroengine Congress and Exposition, Toronto, Canada, 1989.
  6. Dorney, D.J., Griffin, L.W., Huber, F.W., and Sondak, D.L., "Effects of Endwall Geometry and Stacking on Two-stage Supersonic Turbine Performance," AIAA-2002-0078, 40th AIAA Aerospace Sciences Meeting, Reno, The United States, 2002.
  7. iSIGHT Designer's Guide, Version FD 3.1, Engineous Software, Inc., 2008.
  8. Gambit Modeling Guide, Fluent Inc., 2004.
  9. Fluent User's Guide, Fluent, Inc., 2006.
  10. Van Leer, B., "Towards the Ultimate Conservative Difference Scheme, V. A Second Order Sequel to Godunov's Method," Journal of Computational Physics, Vol. 32, pp. 101-136, 1979. https://doi.org/10.1016/0021-9991(79)90145-1
  11. Yakhot V. and Orszag S.A., "Renormal ization Group Analysis of Turbulence. 1. Basic Theory," Journal of Science Computation, Vol. 1, pp. 3-51, 1986. https://doi.org/10.1007/BF01061452
  12. Moffitt, T.P., "Design and Experimental Investigation of a Single-stage Turbine with a Rotor Entering Relative Mach number of 2," NACA-RM-E58F20a, 1958.
  13. Iman, R.L., Davenport, J.M., and Zeigler, D.K., "Latin Hypercube Sampling (Program User's Guide)," OSTI 5571631, 1980.
  14. Myers, R.H. and Montgomery, D.C., "Re sponse Surface Methodology - Process and Product Optimization Using Designed Ex periments," John Wiley & Sons, New York, 1995.
  15. Cho, J.J., Kim, K.S., and Jeong, E.H., "Performance Characteristics of Velocity Compound Supersonic Impulse Turbine with the Rotor Overlaps," Journal of the Korean Society of Propulsion Engineers, Vol. 15, No. 1, pp. 19-28, 2011.