低压涡轮气动/声学一体化设计——总体参数优化

• 作 者: 谭洪川 乔渭阳 赵磊 王雷 陈云
• 机 构: 西北工业大学动力与能源学院,中航工业集团沈阳发动机设计研究所,
• 出 处: 推进技术
• 发表日期: 2012年04期
• 关键词: 低压涡轮 总体参数 单位推力 航空发动机 涡轮效率 马赫数 噪声 耗油率 气动设计 涵道比

低压涡轮是航空发动机的重要噪声源之一,同时也是影响发动机单位推力耗油率的重要部件之一。为适应新一代发动机高效、低噪的设计目标,提出了基于传统涡轮设计流程的低压涡轮气动/声学一体化设计思路,并以某一典型民用发动机6级低压涡轮的设计要求为例,对末级功分配、通道外径、涡轮出口马赫数、叶片数目等涡轮总体参数进行了优化探索。结果表明,文中提出的设计思路可以在涡轮设计的总体参数选取阶段对涡轮效率和噪声同时进行有效评估,以便合理地选取涡轮总体参数,是一种可行的高效、低噪涡轮设计方法。

Low-pressure turbine is one of the most important noise sources of aeroengine, and it is also one of the important components that affect the thrust fuel consumption of engine unit. In order to meet the high-efficiency and low-noise design goals of a new generation of engines, an integrated aerodynamic / acoustic design approach for low-pressure turbines based on the traditional turbine design process is proposed. Taking the design requirements of a typical low-pressure turbine for a typical civilian engine as an example, Level power distribution, channel diameter, turbine exit Mach number, the number of blades and other turbine parameters were optimized to explore. The results show that the design ideas proposed in this paper can evaluate turbine efficiency and noise effectively in the overall parameter selection phase of turbine design so that the overall turbine parameters can be selected reasonably. This is a feasible design method of high efficiency and low noise turbine.