DOI QR코드

DOI QR Code

Effects of Stator Shroud Injection on the Aerodynamic Performance of a Single-Stage Transonic Axial Compressor

정익 슈라우드 공기분사가 단단 천음속 축류압축기의 공력성능에 미치는 영향

  • Received : 2016.08.01
  • Accepted : 2016.10.31
  • Published : 2017.01.01

Abstract

In this study, stator shroud injection in a single-stage transonic axial compressor is proposed. A parametric study of the effect of stator shroud injection on aerodynamic performances was conducted using the three-dimensional Reynolds-averaged Navier-Stokes equations. The curvature, length, width, and circumferential angle of the stator shroud injector and the air injection mass flow rate were selected as the test parameters. The results of the parametric study show that the aerodynamic performances of the single-stage transonic axial compressor were improved by stator shroud injection. The aerodynamic performances were the most sensitive to the injection mass flow rate. Further, the total pressure ratio and adiabatic efficiency were the maximum when the ratio of circumferential angle was 10%.

본 연구에서는 단단 천음속 축류압축기 정익부 슈라우드에 공기분사기를 설치하는 방안을 제시하고 이 것이 공력성능에 미치는 영향을 분석하기 위해 매개변수 연구를 수행하였다. 분사기의 곡률, 폭, 정익 앞전으로부터의 거리, 원주방향 각도 및 공기분사 비율을 변수로 선정하였고, 각 변수의 변화에 따른 공력성능 영향을 분석하기 위해 삼차원 레이놀즈평균 나비어-스톡스 방정식을 사용한 공력해석을 수행하였다. 매개변수 연구 결과, 정익 분사가 적용된 단단 축류압축기의 공력성능이 향상되었고, 공력성능이 공기분사 비율에 민감한 영향을 받는 것이 확인되었다. 원주방향 각도의 비율이 10%일 때 전압력비와 단열 효율이 가장 크게 향상되었다.

Keywords

References

  1. Ciorciari, R., Lesser, A., Blaim, F. and Niehuis, R., 2012, "Numerical Investigation of Tip Clearance Effects in an Axial Transonic Compressor," Journal of Thermal Science, Vol. 21, No. 2, pp. 109-119. https://doi.org/10.1007/s11630-012-0525-6
  2. Geng, S., Lin, F., Chen, J. and Nie, C., 2011, "Evolution of Unsteady Flow Near Rotor Tip During Stall Inception," Journal of Thermal Science, Vol. 20, No. 4, pp. 294-303. https://doi.org/10.1007/s11630-011-0473-6
  3. Tan, C, Day, I., Morris, S. and Wadia, A., 2010, "Spike-Type Compressor Stall Inception, Detection and Control," Annual Reviews of Fluid Mechanics, Vol. 42, No. 1, pp.275-300. https://doi.org/10.1146/annurev-fluid-121108-145603
  4. Dobrzynski, B., Saathoff, H. and Kosyna, G., 2008, "Active Flow Control in a Single-stage Axial Compressor Using Tip Injection and Endwall Boundary Layer Removal," Proceedings of ASME Turbo Expo 2008: Power for Land, Sea and Air, June 9-13, Berlin, Germany, GT2008-50214.
  5. Kern, M., Horn, W., Hiller, S. J. and Staudacher, S., 2011, "Effects of Tip Injection on the Performance of a Multi-stage High-pressure Compressor," CEAS Aeronaut J, Vol. 2, pp. 99-110. https://doi.org/10.1007/s13272-011-0035-3
  6. Benhegouga, I. and Ce, Y., 2013, "Steady Air Injection Flow Control Parameters in a Transonic Axial Compressor," Research Journal of Applied Sciences, Engineering and Technology, Vol. 5, No. 4, pp. 1441-1448. https://doi.org/10.19026/rjaset.5.4885
  7. Dinh, C. T., Heo, M. W. and Kim, K. Y., 2015, "Aerodynamic Performance of Transonic Axial Compressor with a Casing Groove Combined with Blade Tip Injection and Ejection," Aerospace Science and Technology, Vol. 46, pp. 176-187. https://doi.org/10.1016/j.ast.2015.07.006
  8. Culley, D. E., Bright, M. M., Prahst, P. S. and Strazisar, A. J., 2003, "Active Flow Separation Control of a Stator Vane Using Surface Injection in a Multistage Compressor Experiment," Proceedings of ASME Turbo Expo 2003, Atlanta, Georgia, June 16-19, GT2003-38863.
  9. Wundrow, D. W., Braunscheidel, E. P., Culley, D. E. and Bright, M. M., 2006, "Separation Control in a Multistage Compressor Using Impulsive Surface Injection," NASA/TM-2006-214361.
  10. ANSYS CFX-15.0, ANSYS CFX-Solver Theory Guide, ANSYS Inc., 2013.
  11. Chen, H., Huang, X. D. and Fu, S., 2006, "CFD Investigation on Stall Mechanisms and Casing Treatment of a Transonic Compressor," 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Sacramento, USA, AIAA-2006-479.