Numerical simulation of total pressure loss on vortex-reducer with bafflers
-
摘要: 通过数值模拟的方法研究了不同形状的导流板式减涡器对总压损失特性的影响。结果表明,总压的损失主要由气体在减涡器中对导流板做功引起的平缓下降以及由于切向速度过大在转折处引起的迅速下降两部分组成。当导流板较长时,损失主要由气流对导流板做功导致,导流板较短时损失则主要由转折处突降导致。因此,应在起到限制切向速度以降低转折处的突降的同时,尽可能减少气流对导流板的做功。系统总压损失随导流板数量的增多和出口位置的提高呈现先减少后增大的趋势,导流板形状也会对总压损失造成影响。Abstract: The effect of different vortex reducers with bafflers on the characteristics of total pressure loss was studied by numerical simulation. Results showed that the total pressure loss was composed of the slow decrease in the bafflers because of work and the sharp decrease of velocity at the turning point due to the excessive tangential velocity. The loss was mainly caused by the former with long bafflers and by the latter with short bafflers. It was significant to reduce the work done by flow to bafflers, whilelimiting the tangential velocity. The total pressure loss of the system decreased and then increased with the increase of the number of bafflers and the outlet position. The shape and length of the bafflers also affected the total pressure loss.
-
Key words:
- rotating cavity /
- radial inflow /
- vortex-reducer /
- bafflers /
- total pressure loss
-
[1] 吴丽军,陈潇,邓双国,等.减涡器流阻特性计算分析[J].燃气轮机技术,2014,27(3):37-43.WU Lijun,CHEN Xiao,DENG Shuangguo,et al.Flow resistance characteristics of vortex reducer computation and analysis[J].Gas Turbine Technology,2014,27(3):37-43.(in Chinese) [2] HIDE R.On source-sink flows in a rotating fluid[J].Journal of Fluid Mechanics Digital Archive,1968,32(4):737-749. [3] GNTHER A,UFFRECHT W,KAISER E,et al.Experimental analysis of varied vortex reducer configurations for the internal air system of jet engine gas turbines[R].ASME Paper GT2008-50738,2008. [4] NEGULESCU D,PFITZNER M.Secondary air systems in aeroengines employing vortex reducers[R].ASME Paper 2001-GT-0198,2001. [5] PEITSCH D,STEIN M,HEIN S,et al.Numerical investigation of vortex reducer flows in the high pressure compressor of modern aeroengines[R].ASME Paper GT2002-30674,2002. [6] FRIEDL W H,PEITSCH D,NEGULESCU D.Improvement of high pressure turbine air systems by de-swirl nozzles[R].ASME Paper DETC2002/CIE-34449,2002. [7] CHEN X,FENG Y,WU L J.The experimental investigations of centripetal air bleed with tubed vortex reducer for secondary air system in gas turbine[R].ASME Paper GT2014-26959,2014. [8] LIANG Z R,LUO X,FENG Y,et al.Experimental investigation of pressure losses in aero-rotating cavity with radial inflow employing tubed vortex reducers with varied nozzles[J].Experimental Thermal and Fluid Science,2015,66:304-315. [9] LUO X,FENG A,QUAN Y K,et al.Experimental analysis of varied vortex reducers in reducing the pressure loss in a rotating cavity with radial inflow[J].Experimental Thermal and Fluid Science,2016,77:159-166. [10] NING B,LUO X,FENG Y,et al.Study on total pressure losses characteristics of rotating cavity with radial inflow of different drum hole shape[J].Advanced Materials Research,2013,663:483-489. [11] SIBILLI T,CHO G,KHOLI F,et al.Numerical analysis of industrial gas turbine secondary air systems employing vortex reducers[R].ASME Paper GT2018-76313,2018. [12] 杨守辉,王锁芳.不同去旋角度进气共转盘腔内流动与换热研究[J].航空发动机,2011,37(6):17-20.YANG Shouhui,WANG Suofang.Investigation on flow and heat transfer inside co-rotating disc cavity[J].Aeroengine,2011,37(6):17-20.(in Chinese) [13] 赵秋月,娄德仓,郭文.旋转盘腔去旋系统数值模拟[J].燃气涡轮试验与研究,2014,27(5):43-48.ZHAO Qiuyue,LOU Decang,GUO Wen.Numerical simulation for the de-swirled system in rotating cavity[J].Gas Turbine Experiment and Research,2014,27(5):43-48.(in Chinese) [14] 夏子龙,王锁芳,陆海鹰.径向去旋对转盘腔压力损失特性数值研究[C]//第二届中国航空科学技术大会论文集.北京:中国航空学会,2015:293-299. [15] 黄爱霞,王锁芳.反旋进气盘腔内流动与换热的数值模拟[J].航空动力学报,2008,23(9):1684-1688.HUANG Aixia,WANG Suofang.Numerical simulation of flow and heat transfer inside co-rotating disc cavity with de-swirled radial inflow[J].Journal of Aerospace Power,2008,23(9):1684-1688.(in Chinese) [16] 张光宇,王锁芳,夏子龙,等.喷嘴结构对去旋系统减阻特性影响的数值研究[J].推进技术,2018,39(5):979-985.ZHANG Guangyu,WANG Suofang,XIA Zilong,et al.Numerical investigation on effects of varied de-swirl nozzle configurations on drag reduction performance of de-swirl system[J].Journal of Propulsion Technology,2018,39(5):979-985.(in Chinese) [17] 王远东,金峰,王志雄.导流板式减涡器对共转盘腔流动特性影响的实验研究[J].重庆理工大学学报(自然科学),2016,30(12):55-62.WANG Yuandong,JIN Feng,WANG Zhixiong.Experimental research on the gas flow characteristics of the co-rotational disc cavity with bafflers[J].Journal of Chongqing University of Technology (Natural Science),2016,30(12):55-62.(inChinese) [18] DU X,ZHU H,ZHANG Z.Numerical study on varied vortex reducer configurations for the flowpath optimization in compressor cavities[R].ASMEPaper GT2011-45975,2014. [19] LIU G,DU Q,LIU J,et al.Numerical investigation of radial inflow in the impeller rear cavity with and without baffle[J].Science China Technological Sciences,2016,59(3):456-467. [20] KUMAR B G,CHEW J W,HILLS N J.Rotatingflow and heat transfer in cylindrical cavities with radial inflow[J].Journal of Engineering for Gas Turbines and Power,2013,135(3):032502.1-032502.12. [21] 冯安.径向入流旋转盘腔减涡器减阻特性研究[D].北京:北京航空航天大学,2015.FENG An.Investigation on varied vortex reducers in reducing the pressure drop in a rotating cavity with radial inflow [D].Beijing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese) [22] 冯野.高压压气机径向内流引气腔管式减阻特性研究[D].北京:北京航空航天大学,2013.FENG Ye.Investigation on total pressure loss of high compressor centripetal air-bleed system employing tubed vortex reducers[D].Beijing:Beijing University of Aeronautics and Astronautics,2013.(in Chinese)
点击查看大图
计量
- 文章访问数: 423
- HTML浏览量: 6
- PDF量: 367
- 被引次数: 0