多排反向射流角气膜冷却特性研究

doi:10.7527/S1000-6893.2013.0210

Abstract

Abstract:

An investigation on the cooling characteristics of multiple rows of opposite lateral ejection angle film cooling is conducted by means of an orthogonal numerical simulation test. The numerical simulation is conducted by a Realizable k-ε turbulent model and a two-layer velocity zonal model using commercial numerical calculation software. The purpose of the investigation is to reveal the influence of such parameters as lateral ejection angle β, orifice coefficient F, length to width ratio S/P and blowing ratio M, on film cooling. Besides, this paper also tries to find how the above parameters act on cooling respectively. The results show that, compared with the classical counter-rotating vortex pair which appears in the flow field of double-jet film cooling, the vortex pair structure in the downstream of the film-outlet of multiple-rows of opposite lateral ejection angle film cooling is asymmetrical, and cooling is maintained by ejecting cooling jets through rows of holes continuously. It is worth noting that this structure of film cooling achieves excellent cooling effect. The orifice coefficient is found to have the greatest impact on average film cooling effectiveness. Descending order of other parameters, based on their impacts on the average film cooling effectiveness, is: blowing ratio, length to width ratio, and lateral ejection angle, while descending order of the parameters, based on their influence on the heat transfer, is: β=55, M=1.2, F=2%, S/P=1.4.

Key words: orthogonal test, cooling, lateral ejection angle, film cooling effectiveness, heat transfer coefficient

CLC Number:

V231.1

DING Yang, CHANG Haiping, DU Zhineng. Investigation on Characteristics of Multiple Rows of Opposite Lateral Ejection Angle Film Cooling[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(11): 2472-2481.

References

[1] Mayle R E,Camarata F J.Multihole cooling film effectiveness and heat transfer.Journal of Heat Transfer,1975,97(2): 534-538.

[2] Sasaki M,Takahara K,Kumagai T,et al.Film cooling effectiveness for injection from multirow holes.ASME Paper,1978-GT-32,1978.

[3] Andrews G E,Khalifa I M,Asere A A,et al.Full coverage effusion film cooling with inclined holes.ASME Paper,1995-GT-274,1995.

[4] Fric T,Campbell R,Rettig M.Quantitative visualization of full coverage discrete hole film cooling.ASME Paper,1997-GT-328,1997.

[5] Lin Y Z,Song B,Li B,et al.Investigation of film cooling effectiveness of full-coverage inclined multihole walls with different hole arrangements.ASME Paper,2003-GT-38881,2003.

[6] Lin Y Z,Song B,Li B.Investigation of adiabatic wall effectiveness of the inclined multihole wall film cooling with different angles to the wall surface.Acta Aeronautica et Astronautica Sinica,1999,20(3): 201-204.(in Chinese) 林宇震,宋波,李彬.不同倾斜角多斜孔壁冷却方式绝热温比研究.航空学报,1999,20(3): 201-204.

[7] Hu Y P,Ji H H.Effect of porosity of holes array on cooling effectiveness of effusion cooling.Journal of Propulsion Technology,2005,26(1): 28-33.(in Chinese) 胡娅萍,吉洪湖.孔阵排列疏密度对致密多孔壁冷却效果的影响.推进技术,2005,26(1): 28-33.

[8] Tanaka R,Kazari M,Sugimoto T,et al.Double-jet film cooling structure: Japanese.332530.2005-11-17.

[9] Kusterer K,Bohn D,Sugimoto T,et al.Double-jet of cooling air for improved film-cooling.ASME Paper,2006-GT-90854,2006.

[10] Kusterer K,Bohn D,Sugimoto T,et al.Influence of blowing ratio on the double-jet ejection of cooling air.ASME Paper,2007-GT-27301,2007.

[11] Tanaka R,Sugimoto T,Ryu M,et al.Continuing improvements of 20MW-Class GT Kawasaki L20A.ASME Paper,2006-GT-90394,2006.

[12] Kusterer K,Elyas A,Bohn D,et al.Double-jet film-cooling for highly efficient film-cooling with low blowing ratios.ASME Paper,2008-GT-50073,2008.

[13] Kusterer K,Bohn D,Sugimoto T,et al.A parametric study on the influence of the lateral ejection angle of double-jet holes on the film cooling effectiveness for high blowing rations.ASME Paper,2009-GT-59321,2009.

[14] Wang W S,Tang F,Zhao Q J,et al.An investigation of the effect of new-type double-jet film cooling(DJFC) hole on film cooling effectiveness.Journal of Engineering Thermophysics,2011,32(8): 1291-1294.(in Chinese) 王文三,唐菲,赵庆军,等.新型双射流冷却孔对气膜冷却效率影响的研究.工程热物理学报,2011,32(8):1291-1294.

[15] Yu X H,Dong Z R,Liu S L,et al.Study for flow resistance characteristics of the modelled laminated porous wall.Journal of Propulsion Technology,2000,21(4): 47-50.(in Chinese) 郁新华,董志锐,刘松岭,等.层板模型流阻特性的研究.推进技术,2000,21(4): 47-50.

[16] Yang C F,Zhang J Z,Yang W H.Effect of the holes array arrangement on the full coverage film cooling characteristics.Journal of Aerospace Power,2010,25(7): 1524-1529.(in Chinese) 杨成风,张靖周,杨卫华.全覆盖气膜孔阵列方式对冷却特性的影响.航空动力学报,2010,25(7): 1524-1529.

Investigation on Characteristics of Multiple Rows of Opposite Lateral Ejection Angle Film Cooling

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Xiaoyong LIU, Mingfu WANG, Jianwen LIU, Xin REN, Xuan ZHANG. Review and prospect of research on scramjet [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529878-529878.
[2]	Yi ZHANG, Binwen WANG, Jingtao WU, Linhua CONG, Hong CHEN, Shiping LI. Graphite-based simulation method of wide temperature range and rapidly time-varying aerothermal load [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 228732-228732.
[3]	Weiping LI, Longjin YANG. Cooling performance analysis of combustion liner in reverse-flow combustor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 127326-127326.
[4]	Siyuan LIU, Yongqi XIE, Jian SU, Hongxing ZHANG, Guoguang LI. Steady-state working performance of loop heat pipes in acceleration environment: Comparative study [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 126803-126803.
[5]	Xiao HOU. Research progress in combined cycle engines [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 529824-529824.
[6]	Ming REN, Cunliang LIU, Kun DU, Li ZHANG, Huiren ZHU, Bolun ZHANG. Film cooling with compound angle holes in leading edge of twisted turbine blade [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 128315-128315.
[7]	Youkui LAI, Haiteng MA, Yisu LIU, Hua OUYANG. Flow measurement and analysis of a turbine blade with multiple cooling structures based on magnetic resonance velocimetry [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 627920-627920.
[8]	Mei ZHENG, Lijuan FENG, Na QIN, Jinge YIN. 3D computational method for conjugate heat transfer between internal and external flow of nacelle anti-icing system [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627425-627425.
[9]	WANG Bin, WANG Haitao, WANG Yufeng, ZHANG Wenwu. Water-assisted laser scanning machining test of thermal barrier coating [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525353-525353.
[10]	YE Lin, LIU Cunliang, ZHU Andong, ZHOU Tianliang. Influence of compact-ribbed passage on trailing-edge cutback film cooling performance [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125174-125174.
[11]	XIA Kailong, HE Qing, ZHANG Yusheng. Measurement method of turbine blade film aperture based on infrared thermal imaging and shrinkage law [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 426271-426271.
[12]	LUO Shibin, MIAO Zhichao, SONG Jiawen. Influencing factors of active cooling at leading edge of hypersonic vehicles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 627023-627023.
[13]	CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun. Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124884-124884.
[14]	BAO Jun, WANG Yu, NIU Qian, ZHU Xidong, CHENG Jianjie. Influencing parameters and film flow mechanism of spray droplet impacting liquid film [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726360-726360.
[15]	YANG Yuquan, LIU Cunliang, ZHANG Jie, HUANG Rong. Effect of mass flow ratios on film cooling characteristics of endwall: Experimental study [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124399-124399.