지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.18 Number.1
- 발행연도
- 2017.3
- 수록면
- 91 - 98 (8page)
- DOI
- 10.5139/IJASS.2017.18.1.91
이용수
초록· 키워드
오류제보하기
Performance of a low speed axial compressor is enhanced through a proper configuration of blade row tip injection and casing treatment of groove type. Air injectors were mounted evenly spaced upstream of the blade row within the casing groove and were all aligned parallel to the compressor axis. The groove, which covers all the blade tip chord length, extends all-round the casing circumference. Method of investigation is based on solution of the unsteady form of the Navier-Stokes equations utilizing k-ω SST turbulence model. Extensive parametric studies have been carried out to explore effects of injectors’ flow momentums and yaw angles on compressor performance, while being run at different throttle valve setting. Emphasis has been focused on situations near to stall condition. Unsteady numerical analyses for untreated casing and no-injection case for near stall condition provided to discover two well-known criteria for spike stall inception, i.e., blade leading edge spillage and trailing edge back-flow. Final results showed that with only 6 injectors mounted axially in the casing groove and at yaw angle of 15 degrees opposite the direction of the blade row rotation, with a total mass flow rate of only 0.5% of the compressor main flow, surprisingly, the stall margin improves by 15.5%.
목차
Abstract
1. Introduction
2. Model specification and numerical approach
3. Results and discussion
4. Conclusion
References
참고문헌 (18)
참고문헌 신청
Cumpsty, N. A., Compressor Aerodynamics, Longman Scientific & Technical, 1989.
Inoue, M., Kuroumaru, M., Yoshida, S., Minami, T., Yamada, K. and Furukawa, M., “Effect of Tip Clearance on Stall Evolution Process in a Low-Speed Axial Compressor Stage”, ASME Turbo Expo 2004: Power for Land, Sea, and Air, 2004.
Storer, J. and Cumpsty, N., “Tip Leakage Flow in Axial Compressors”, Journal of Turbomachinery, Vol. 113, No. 2, 1991, pp. 252-259.
Vo, H. D., Tan, C. S. and Greitzer, E. M., “Criteria for Spike Initiated Rotating Stall”, Journal of Turbomachinery, Vol. 130, No. 1, 2008, pp. 011023.
Hah, C., Bergner, J. and Schiffer, H. P., “Short Length-Scale Rotating Stall Inception in a Transonic Axial Compressor: Criteria and Mechanisms”, ASME Turbo Expo 2006: Power for Land, Sea, and Air, 2006.
Inoue, M., Kuroumaru, M., Yoshida, S., Minami, T., Yamada, K. and Furukawa, M., “Effect of Tip Clearance on Stall Evolution Process in a Low-Speed Axial Compressor Stage”, ASME Turbo Expo 2004: Power for Land, Sea, and Air, 2004.
Storer, J. and Cumpsty, N., “Tip Leakage Flow in Axial Compressors”, Journal of Turbomachinery, Vol. 113, No. 2, 1991, pp. 252-259.
Vo, H. D., Tan, C. S. and Greitzer, E. M., “Criteria for Spike Initiated Rotating Stall”, Journal of Turbomachinery, Vol. 130, No. 1, 2008, pp. 011023.
Hah, C., Bergner, J. and Schiffer, H. P., “Short Length-Scale Rotating Stall Inception in a Transonic Axial Compressor: Criteria and Mechanisms”, ASME Turbo Expo 2006: Power for Land, Sea, and Air, 2006.
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UCI(KEPA) : I410-ECN-0101-2017-558-002392156