【作者】 韩阳；

【导师】 陈浮；

【作者基本信息】 哈尔滨工业大学 ， 动力机械及工程， 2011， 硕士

【摘要】 随着科技的发展,航空发动机在国民经济和国防中的地位越来越重要。而涡轮作为航空发动机的核心部件,其设计工作受到越来越多的国家重视。现代涡轮向着高负荷方向发展,叶片流道内的流动状态趋于复杂化和高速化,经常会出现跨音速流动,甚至是超音速流动。因此对跨音速涡轮的设计理论和设计方法的研究,以及对跨音速涡轮的数值模拟和性能的提高是近些年国内外关注的热点。跨音速涡轮的损失主要包括叶型损失、二次流损失、端壁损失、叶顶泄漏损失以及导向器根部和转子上部的激波损失。本文采用了可控涡设计思想,可以有效的提高根部反动度,减小顶部的反动度。根部反动度的提高可以在一定程度上减小导向器根部的激波强度和超音区域;而顶部反动度的减小,可以减弱转子上部的激波强度和超音区域。研究结果表明,通过调整各截面的叶型角和厚度沿子午方向的分布,实现合理分配各叶型截面以及子午方向的气动负荷,是获得高气动性能跨音速涡轮的有效方法。此外,设计中还采用了后掠叶片的设计方法,使叶片压力呈现C型分布,驱使流体从两端向中间流动,中间流体卷吸两端低能流体,减小两端端壁损失,提高了涡轮的气动性能。本文从设计要求开始,进行一维和三维气动设计,采用可控涡扭曲规律,获得叶片尺寸,使用商用软件CFX进行三维气动计算,对设计结果进行修正。最终获得了满足设计要求的设计结果。分析了设计工况下的三维流场,研究了新设计方案相对于原方案的改进之处。分析了在涡轮工作条件改变时,涡轮所表现出的流量效率等特性。最后对新设计涡轮进行了强度分析,在耦合了压力场和温度场的条件下进行了强度校核。认为涡轮设计满足强度要求。涡轮设计是成功的。更多还原

【Abstract】 With the development of technology, the aviation engine becomes more and more important in the national economy and defense. The turbine is the main component of the aviation engine, whose design is paid increasingly attention to by many countries. With the development of the modern high load turbine, the flow condition in the blade channel becomes more and more complex and high speed, often associated with transonic flow and even supersonic flow. Therefore, the focus of attention is paid on the theories and methodologies of transonic turbine, as well as numerical simulation and performance improvement by the scholars at home and abroad in the recent years.The energy loss in the transonic turbine mainly include the end walls corner loss, tip leakage loss and the shock loss in the roots of the stator and the upper part of the rotor. In this paper, the controller vortex design is chosen, which can effectively improve the reaction degree in the roots, and can reduce it at the top. It can reduce the shock strength and shock region in the turbine guide vane by increasing the reaction degree in the roots. The decrease of the reaction degree at the top can weaken the shock strength and shock region. The results show that it’s an important method to design a high aerodynamic performance transonic turbine, that blade angle and thickness are adjusted cross the blade section and along the meridian to make the profile aerodynamic load allocated rationally. Furthermore, a swept blade design is applied to show the C-type blade pressure distribution, which can make the fluid in the middle entrainment the loss energy fluid at in the end walls corner, enhance the trend of the fluid toward the middle from both ends. It can reduce the end walls corner loss at both ends to improve the turbine aerodynamic performance.In this paper, do the 1-D and 3-D aerodynamic design according to the design requirements, and apply the controlled vortex design to generate the blade geometry. With the commercial software CFX 3-D aerodynamic calculation results, trim the geometry to meet the design requirements. We analyze the 3-D flow field in the design conditions and study the improvements compared to the original design. Analyze the mass and efficiency performance off the design conditions. Finally, the strength analysis and check are done for the new design turbine coupled with the pressure and temperature field, which meet the strength requirements. The turbine design is successful.更多还原