| Citation: | TANG Runze, LI Haiwang, ZHOU Zhiyu, et al. Influence of coolant inlet angle on endwall leakage flow film cooling performance[J]. Journal of Aerospace Power, 2024, 39（X）：20230762 doi: 10.13224/j.cnki.jasp.20230762
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By using an integrated model with disc cavity and turbine blade, the endwall film cooling effectiveness was investigated numerically by using the shear stress transfer (SST) model to solve the Reynolds-averaged Naiver-Stokes (RANS) equation. The rotational Reynolds number at the outlet of the disc cavity was 1.5×105. Carbon dioxide was chosen as the coolant to maintain the coolant-to-mainstream density ratio. The diffusion process of coolant was characterized by solving the turbulent transport equation. The effect of coolant inlet angle (−45°, 0°, +45°) on the endwall film cooling effectiveness was investigated. It was found that the inlet angle of coolant had a significant impact on the endwall film cooling effectiveness, and the −45° inlet angle can significantly improve the endwall film cooling effectiveness at various coolant-to-mainstream mass flow rates.
| [1] |
UMESH U,VIGOR Y. A review of cooling technologies for high temperature rotating components in gas turbine[J]. Propulsion and Power Research,2022,11(3): 293-310. doi: 10.1016/j.jppr.2022.07.001
|
| [2] |
SHARMA O P,BUTLER T L. Predictions of endwall losses and secondary flows in axial flow turbine cascades[J]. Journal of Turbomachinery,1987,109(2): 229-236. doi: 10.1115/1.3262089
|
| [3] |
HAWTHORNE W R. Secondary circulation in fluid flow[J]. Proceedings of the Royal Society of London Series A Mathematical and Physical Sciences,1951,206(1086): 374-387.
|
| [4] |
GOLDSTEIN R J,SPORES R A. Turbulent transport on the endwall in the region between adjacent turbine blades[J]. Journal of Heat Transfer,1988,110(4a): 862-869. doi: 10.1115/1.3250586
|
| [5] |
NICKLAS M. Film-cooled turbine endwall in a transonic flow field: Part Ⅱ heat transfer and film-cooling effectiveness[J]. Journal of Turbomachinery,2001,123(4): 720-729. doi: 10.1115/1.1397308
|
| [6] |
李宁坤,闻洁. 跨声速涡轮静子端壁气膜冷却数值研究[J]. 航空发动机,2011,37(3): 50-54. LI Ningkun,WEN Jie. Numerical study on flim cooling of transonicturbine vane endwall[J]. Aeroengine,2011,37(3): 50-54. (in Chinese doi: 10.3969/j.issn.1672-3147.2011.03.015
|
| [7] |
BLAIR M F. An experimental study of heat transfer and film cooling on large-scale turbine endwalls[J]. Journal of Heat Transfer,1974,96(4): 524-529. doi: 10.1115/1.3450239
|
| [8] |
刘高文,刘松龄,朱惠人,等. 涡轮叶栅前缘上游端壁气膜冷却的传热实验研究[J]. 航空动力学报,2001,16(3): 249-255. LIU Gaowen,LIU Songling,ZHU Huiren,et al. Endwall heat transfer and film cooling measurements in a turbine cascade with injection upstream of leading edge[J]. Journal of Aerospace Power,2001,16(3): 249-255. (in Chinese doi: 10.3969/j.issn.1000-8055.2001.03.010
|
| [9] |
刘高文,刘松龄,许都纯,等. 涡轮叶栅前缘上游端壁气膜冷却的流场实验研究[J]. 航空动力学报,2001,16(2): 135-141. LIU Gaowen,LIU Songling,XU Duchun,et al. Experimental investigation of flow fields in a turbine cascade with endwall film-cooling upstream of leading edge[J]. Journal of Aerospace Power,2001,16(2): 135-141. (in Chinese doi: 10.3969/j.issn.1000-8055.2001.02.009
|
| [10] |
PAPA M,SRINIVASAN V,GOLDSTEIN R J. Film cooling effect of rotor-stator purge flow on endwall heat/mass transfer[J]. Journal of Turbomachinery,2012,134(4): 041014.
|
| [11] |
LI Xueying,REN Jing,JIANG Hongde. Influence of different film cooling arrangements on endwall cooling[J]. International Journal of Heat and Mass Transfer,2016,102: 348-359. doi: 10.1016/j.ijheatmasstransfer.2016.06.047
|
| [12] |
姚韵嘉,祝培源,陈云,等. 间隙位置对叶片端壁气膜冷却性能影响的实验研究[J]. 工程热物理学报,2019,40(10): 2327-2333. YAO Yunjia,ZHU Peiyuan,CHEN Yun,et al. Experimental study on the effect of the locations of slot jet on film cooling performance of endwall[J]. Journal of Engineering Thermophysics,2019,40(10): 2327-2333. (in Chinese
|
| [13] |
ZHU Peiyuan,SONG Liming,LI Jun,et al. Effects of upstream slot geometry on the endwall aerothermal performance of a gas turbine blade under different ejection angle conditions[J]. International Journal of Heat and Mass Transfer,2017,115: 652-669. doi: 10.1016/j.ijheatmasstransfer.2017.08.072
|
| [14] |
杜昆,李军,晏鑫. 槽缝射流对静叶端壁冷却性能的影响[J]. 西安交通大学学报,2015,49(1): 21-26. DU Kun,LI Jun,YAN Xin. Effect of the slot jet impingement on the cooling performance of the vane endwall[J]. Journal of Xi’an Jiaotong University,2015,49(1): 21-26. (in Chinese
|
| [15] |
高庆,屈杰,王汀,等. 轮缘间隙出流对下游动叶端壁气膜冷却特性的影响[J]. 动力工程学报,41(5): 374-379. GAO Qing,QU Jie,WANG Ting,et al. Effects of rim seal purge flow on film cooling characteristics of downstream rotor endwall[J]. Journal of Chinese Society of Power Engineering,41(5): 374-379. (in Chinese
GAO Qing, QU Jie, WANG Ting, et al. Effects of rim seal purge flow on film cooling characteristics of downstream rotor endwall[J]. Journal of Chinese Society of Power Engineering, 41(5): 374-379. (in Chinese)
|
| [16] |
张垲垣,杜昆,宋立明,等. 预旋槽缝流及间隙射流对端壁冷却性能的影响[J]. 工程热物理学报,2019,40(6): 1250-1255. ZHANG Kaiyuan,DU Kun,SONG Liming,et al. Effect of swirled purge flow and slashface leakage flow on endwall cooling performance[J]. Journal of Engineering Thermophysics,2019,40(6): 1250-1255. (in Chinese
|
| [17] |
REZASOLTANI M,SCHOBEIRI M T,HAN J C. Experimental investigation of the effect of purge flow on film cooling effectiveness on a rotating turbine with nonaxisymmetric end wall contouring[J]. Journal of Turbomachinery,2014,136(9): 091009. doi: 10.1115/1.4027196
|
| [18] |
SURYANARAYANAN A,OZTURK B,SCHOBEIRI M T,et al. Film-cooling effectiveness on a rotating turbine platform using pressure sensitive paint technique[J]. Journal of Turbomachinery,2010,132(4): 1-13.
|
| [19] |
GAO Feng,CHEW J,CHANA K S,et al. Unsteady flow phenomena in turbine rim seals[J]. Journal of Engineering for Gas Turbines and Power,2016,139(3): 032501.
|
| [20] |
SANGAN C M,POUNTNEY O J,SCOBIE J A,et al. Experimental measurements of ingestion through turbine rim seals: Part Ⅲ single and double seals[J]. Journal of Turbomachinery,2013,135(5): 051011. doi: 10.1115/1.4007504
|
| [21] |
POPOVÍC I,HODSON H P. Improving turbine stage efficiency and sealing effectiveness through modifications of the rim seal geometry[J]. Journal of Turbomachinery,2013,135(6): 061016. doi: 10.1115/1.4024872
|
| [22] |
DA SOGHE R,BIANCHINI C,SANGAN C M,et al. Numerical characterization of hot-gas ingestion through turbine rim seals[J]. Journal of Engineering for Gas Turbines and Power,2017,139(3): 032602. doi: 10.1115/1.4034540
|
| [23] |
ZHANG Feng,WANG Xinjun,LI Jun,et al. Numerical investigation on the effect of radial location of sealing air inlet and its geometry on the sealing performance of a stator-well cavity[J]. International Journal of Heat and Mass Transfer,2017,115: 820-832. doi: 10.1016/j.ijheatmasstransfer.2017.08.053
|
| [24] |
陶加银,高庆,宋立明,等. 基于附加示踪变量法的涡轮轮缘密封非定常封严特性研究[J]. 工程热物理学报,2014,35(11): 2154-2158. TAO Jiayin,GAO Qing,SONG Liming,et al. Numerical investigations on the unsteady mainstream ingestion characteristics of turbine rim seals with additional passive tracer method[J]. Journal of Engineering Thermophysics,2014,35(11): 2154-2158. (in Chinese
|
| [25] |
XIE Gang,TAO Zhi,ZHOU Zhiyu,et al. Hole arrangement effect to film cooling performance on leading edge region of rotating blade[J]. International Journal of Thermal Sciences,2021,169: 107034. doi: 10.1016/j.ijthermalsci.2021.107034
|
| [26] |
LIU T,SULLIVAN J P. Pressure and temperature sensitive paints[M]. Berlin,Germany: Springer,2005.
|
| [27] |
NATSUI G,LITTLE Z,KAPAT J S,et al. A detailed uncertainty analysis of adiabatic film cooling effectiveness measurements using pressure-sensitive paint[J]. Journal of Turbomachinery,2016,138(8): 081007. doi: 10.1115/1.4032674
|
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