叶尖间隙泄漏对厘米级高亚声微型轴流涡轮性能的影响
Effect of tip clearance leakage on performance of centimetre-level high subsonic micro axial flow turbine
-
摘要: 针对某微型涡轮发动机(MTE)原理样机的直径为78.4mm的微型轴流涡轮,采用数值模拟手段研究了叶尖间隙泄漏对该厘米级高亚声微型轴流涡轮流场结构及涡轮性能的影响.结果表明:微型轴流涡轮相对叶尖间隙尺寸在3.1%~4.6%,明显高于常规轴流涡轮;微型轴流涡轮叶尖间隙泄漏涡影响范围较常规轴流涡轮扩大(至叶中高度),泄漏损失占涡轮级总损失的35%,也较常规轴流涡轮明显增大.研究获得了间隙尺寸对该厘米级高亚声微型轴流涡轮性能的影响规律,叶尖相对间隙尺寸每增加1%叶高,效率最快下降1.9%,其变化幅度较常规轴流涡轮更为明显.最后,根据工程安装的限制(离心力变形及热变形、轴承游隙、加工装配误差等),确定了一个较优的叶尖间隙(0.4mm),通过数值模拟获得了在该间隙下的涡轮性能参数:落压比为2.12,效率为0.87,流量为0.35kg/s.Abstract: The effect of the tip leakage on the flow field structure and turbine performance of a 78.4mm diameter centimetre-level high subsonic micro axial flow turbine of a micro turbine engine(MTE) prototype was analyzed by numerical simulation. Results show that the relative tip clearance size of micro axial turbine is within the range of 3.1%-4.6%, which is higher than that of conventional axial flow turbine. The effect of tip leakage vortex extends towards the mid of the vanes, of which the leakage losses account for 35% of total losses of the turbine stage, showing a significant increase compared to the conventional axial flow turbine. Studies on the impacts of the law of the gap size of the centimetre-level high subsonic micro axial flow turbine have shown that, once the gap size for each increases by 1% of the blade height, the efficiency will decrease up to 1.9%, which is more distinct than the conventional turbine. Finally, an optimum gap size (0.4mm) was determined due to the restrictions of engineering installation (centrifugal deformation, thermal deformation, bearing clearance, machining and assembly errors, etc), and the performance parameter of the impeller was acquired by numerical simulation: total pressure ratio of 2.12, efficiency of 0.87, mass flow of 0.35kg/s.
-
Key words:
- high subsonic /
- micro axial flow turbine /
- tip clearance /
- leakage /
- numerical simulation
-
[1] 刘大响,金捷.21 世纪世界航空动力技术发展趋势与展望[J].中国工程科学,2004,6(9):1-8. LIU Daxiang,JIN Jie.Development tendency and prospect of world aerospace power techniques in 21 century[J].Engineering Science,2004,6(9):1-8.(in Chinese) [2] 黄国平,温泉,李博,等.微型涡喷发动机顶层设计研究[J].航空动力学报,2003,18(6):832-838. HUANG Guoping,WEN Quan.LI Bo,et al.Top level design of micro turbine jet engine[J].Journal of Aerospace Power,2003,18(6):832-838.(in Chinese) [3] Peris J,Reynaerts D,Verplaetsen F,et al.Development of a micro gas turbine for electric power generation.Delft,US:the 14th Micromechanics Europe Workshop,2003. [4] 黄国平,梁德旺,何志强.大型飞机辅助动力装置与微型涡轮发动机技术特点对比[J].航空动力学报,2008,23(2):383-388. HUANG Guoping,LIANG Dewang,HE Zhiqiang.Comparison of technical characteristics of APU and micro turbine engines for large aircraft[J].Journal of Aerospace Power,2008,23(2):383-388.(in Chinese) [5] 夏晨,黄国平,邱建.某微型发动机对比分析轴流涡轮与向心涡轮的气动性能与尺寸质量[J].航空动力学报,2011,26(3):489-497. XIA Chen,HUANG Guoping,QIU Jian.Comparison research on performance and size of micro axial turbine and radial turbine[J].Journal of Aerospace Power,2011,26(3):489-497.(in Chinese) [6] 石靖,韩鉴元.小发动机涡轮的气动设计问题[J].航空动力学报,1991,6(1):29-32. SHI Jing,HAN Jianyuan.Aerodynamical design for small gasturbines[J].Journal of Aerospace Power,1991,6(1):29-32.(in Chinese) [7] Gummer V,Goller M,Swobada M.Numerical investigation of endwall boundary layer removal on highly-loaded axial compressor blade rows.ASME Paper GT 2005-68699,2005. [8] Rao N M,Camci C.Axial turbine tip desensitization by injection from a tip trench:Part 1 effect of injection mass flow rat.ASME Ppaer GT 2004-53256,2004. [9] Rao N M,Camci C.Axial turbine tip desensitization by injection from a tip trench:Part 2 leakage flow sensitivity to injection location.ASME Paper GT 2004-53258,2004. [10] 贾希诚,王正明.叶顶间隙对环形叶栅三维粘性流场影响的数值分析[J].工程热物理学报,1999,20(6):707-710. JIA Xicheng,WANG Zhengming.Numerical analysis of the effects of tip clearance on three-dimensional viscous flow in annular cascade[J].Journal of Engineering Thermophysics,1999,20(6):707-710.(in Chinese) [11] Merz R,Krueckels J,Mayer J F,et al.Computation of three-dimensional viscous transonic turbine stage flow including tip clearance effects.ASME Paper 95-GT-76,1995. [12] 杨策,马朝臣,王延生,等.透平机械叶尖间隙流场研究的进展[J].力学进展,2001,31(1):70-83. YANG Ce,MA Chaochen,WANG Yansheng,et al.A review of studies on turbomachinery tip gap leakage flow[J].Advances in Mechanics,2001,31(1):70-83.(in Chinese) [13] 石宝龙,岂兴明,矫津毅,等.二次流与叶顶间隙损失的数值研究[J].航空动力学报,2009,24(5):1096-1100. SHI Baolong,QI Xingming,JIAO Jinyi,et al.Numerical analysis of the secondary flow and tip clearance leakage loss[J].Journal of Aerospace Power,2009,24(5):1096-1100.(in Chinese) [14] Wbitney W J,Szanca E M,Moffitt T P,et al.Cold-air investigation of a turbine for high-temperature-engine application:Part 1 turbine design and overall stator performance.NASA TN D-3751,1967. [15] Prust H W Jr,Schum H J.Cold-air investigation of a turbine for high-temperature-engine application:Part 2 detailed analytical and experimental investigation of stator performance.NASA TN D-4418,1968. [16] Wbitney W J,Szanca E M,Bider B,et al.Cold-air investigation of a turbine for high-temperature-engine application:Part 3 overall stage performance.NASA TN D-4389,1968. [17] 王大磊,朴英.叶尖间隙高度对某高压涡轮级损失分布的影响[J].航空动力学报,2012,27(1):169-175. WANG Dalei,PIAO Ying.Influence of tip clearance size on flow losses of a transonic high pressure turbine stage[J].Journal of Aerospace Power,2012,27(1):169-175.(in Chinese) [18] 熊宇飞.航空发动机转子叶尖间隙测量[J].测控技术,2004,23(1):5-7.
点击查看大图
计量
- 文章访问数: 1419
- HTML浏览量: 2
- PDF量: 918
- 被引次数: 0