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학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국유체기계학회 International Journal of Fluid Machinery and Systems International Journal of Fluid Machinery and Systems Vol.11 No.2
- 발행연도
- 2018.6
- 수록면
- 129 - 138 (10page)
- DOI
- 10.5293/IJFMS.2018.11.2.129
이용수
초록· 키워드
오류제보하기
To investigate the internal distribution regularities of shock wave structure in 1+1/2 (without low pressure guide vane) counter-rotating turbine, both steady and unsteady numerical simulation about a designed 1+1/2 counter-rotating turbine are conducted, and experimental research about the shock wave structure of high pressure guide vane, high pressure rotor and low pressure rotor was also conducted by using the schlieren apparatus under different working conditions. The numerical simulation divides into two parts: steady and unsteady calculation. The result of steady simulation under designed condition shows that there appears supersonic flow and shock wave at the exit of root in high pressure guide vane, while supersonic flow appears at the entire passage of the blade outlet in both the high pressure rotor and low pressure rotor, together with strong shock wave and complex wave structures. From the point of the unsteady results, the unsteady effect has few influence on the flow field of high pressure guide vane, but the wake of the high pressure guide leaves periodically sweeps through the front edge of the high pressure blade and there presents strong unsteady effect on flow field of high pressure rotor. Then, to deeply research the characteristics of the shock wave structure, 50% height section of the blade of the three types of blades are extracted respectively to make plane cascades which are conducted blowing experiments in supersonic wind tunnel. During the experiment schlieren display technology is used to record the shock wave structure changing process in three cascade flow passage under the design Angle of attack when pressure ratio changes from 1.7 to 2.5. The final photograph were analyzed by comparing with the CFD results. Results show that with the increase of expansion ratio, the wave structures in both high and low pressure blade channel move toward the exit and the caudal interference between the outer tail wave and is strengthened gradually. The results show that the current design of high pressure blade and low pressure blade show better advantages for controlling the structure of the shock wave.
목차
Abstract
1. Introduction
2. Numerical Simulation
3. The Experimental Study
4. Conclusion
References
참고문헌 (9)
참고문헌 신청
[보고서] - Macioce L.E. / 1980 / A Status Report on the Energy Efficient Engine Project, NASA-TM-81566
[보고서] - Maclin H. / 1985 / Propulsion Technology for Future Commercial Aircraft, AIAA Paper[C], 2003, AIAA-2003-2544
[보고서] - Lious J.F. / / Axial Flow Contra-Rotating Turbines[A]. ASME Paper[C], 85-GT-218
[학술지(정기간행물)] - X J Fang / 2003 / Analytic about model of high order polynomial of transonic Counter-Rotating turbine blade with large turning angle / Journal of Aeronautical dynamics 18 (1) : 76 ~ 81
[학술지(정기간행물)] - H S Wang / 2007 / Numerical study of the flow field at the top clearance of rotating rotor in a 1+ 1/2 turbine / Journal of Engineering Physics 28 (5) : 751 ~ 754
[보고서] - Maclin H. / 1985 / Propulsion Technology for Future Commercial Aircraft, AIAA Paper[C], 2003, AIAA-2003-2544
[보고서] - Lious J.F. / / Axial Flow Contra-Rotating Turbines[A]. ASME Paper[C], 85-GT-218
[학술지(정기간행물)] - X J Fang / 2003 / Analytic about model of high order polynomial of transonic Counter-Rotating turbine blade with large turning angle / Journal of Aeronautical dynamics 18 (1) : 76 ~ 81
[학술지(정기간행물)] - H S Wang / 2007 / Numerical study of the flow field at the top clearance of rotating rotor in a 1+ 1/2 turbine / Journal of Engineering Physics 28 (5) : 751 ~ 754
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UCI(KEPA) : I410-ECN-0101-2018-554-003063127