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基于哈尔滨工业大学自主开发的带冷气叶片气动网格自动生成技术,通过Ansys公司下的CFX软件,对国产某型民用航空发动机高压涡轮第一级动叶进行设计。设计中采用了一种新型控制二次流发展的叶形,使用特殊前缘参数化设计方法。具体操作为叶片根部叶形前缘前伸,前缘修小圆,在前缘吸力面位置局部内凹,并沿叶高一定范围内进行光滑过渡,即形成根部区域修型,其他区域不变的新叶形。研究表明:采用此方法能够有效的降低由于叶片前缘马蹄涡造成的通道涡等涡系的尺度及强度,从而减少气动损失。
Based on the self-developed aerodynamic grid automatic generation technology with air-cooled blades developed by Harbin Institute of Technology, the first-stage high-pressure turbine rotor blades of a domestic civil aircraft engine are designed by Ansys CFX software. The design uses a new type of control of secondary flow development of the leaf shape, the use of special leading edge parameterized design. The specific operation is that the leading edge of the leaf blade extends forward while the leading edge is rounded, and the concave portion is concavely positioned at the suction surface of the leading edge and smoothly transitions along a certain range of the leaf height to form the root area modification without changing other areas New leaf shape The results show that this method can effectively reduce the size and intensity of vortices such as channel vortices caused by the leading edge of horseshoe vortex, thus reducing the aerodynamic losses.