叶根倒角对跨音轴流压气机气动性能的影响

发布时间：2018-01-16 23:04

  本文关键词：叶根倒角对跨音轴流压气机气动性能的影响　出处：《机械工程学报》2016年20期 　论文类型：期刊论文

  更多相关文章： Rotor 叶根倒角 刀具干涉 最小角度 数值模拟

【摘要】：为了获得叶根倒角对跨音轴流压气机气动特性影响规律,研究充分考虑了加工工艺及气动影响两方面,用倒角半径及最小角度两个参数确定倒角几何。研究基于Rotor37分析倒角参数对叶片几何的影响,并从整体性能及内部流场细节两方面对转子气动特性变化进行详细分析,获得了倒角参数变化对气动性能的影响规律。研究结果表明,相对于最小角度,倒角半径是影响转子性能的主要因素;倒角的存在不仅使得叶片根部马蹄涡的分布发生改变,且影响了出口通道涡的强度和尺度。此外倒角存在改变了叶根处的压力分布,使得前缘来流附面层有所增厚,导致根部的做功能力及转子性能下降。
[Abstract]:In order to obtain the influence of blade root chamfering on the aerodynamic characteristics of transonic axial compressor, the machining technology and aerodynamic effect are fully considered. The chamfer geometry is determined by two parameters: the chamfer radius and the minimum angle. The influence of chamfer parameters on blade geometry is studied based on Rotor37. The variation of rotor aerodynamic characteristics is analyzed in detail from the aspects of overall performance and internal flow field details, and the influence of chamfer parameters on aerodynamic performance is obtained. The results show that the change of rotor aerodynamic performance is relative to the minimum angle. Chamfer radius is the main factor affecting rotor performance. The existence of chamfer not only changes the distribution of the horseshoe vortex at the root of the blade, but also affects the intensity and scale of the vortex at the outlet channel. In addition, the chamfer changes the pressure distribution at the root of the blade. The leading edge flow boundary layer is thickened, which leads to the decrease of the work ability of the root and the performance of the rotor.
【作者单位】： 西北工业大学动力与能源学院;先进航空发动机协同创新中心;
【基金】：国家自然科学基金资助项目(51236006,51476132)
【分类号】：V231.3
【正文快照】： 0前言1作为航空发动机的核心部件,压气机的性能对整台发动机的气动性能、可靠性以及经济性的影响至关重要。叶片是构成压气机的基本单元,由相邻叶片构成的通道内的流动情况决定了压气机的性能。受到结构强度与加工工艺限制,叶片实体与设计叶片之间通常存在一定的偏差,例如叶片，

本文编号：1435194