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为了在压气机通流设计阶段考虑叶片弯掠效应,开发了基于流线曲率法的通流设计程序,提出一种基于四次多项式的任意中弧线叶片造型方法,并推导了任意回转面上的中弧线表达式。以此方法为基础,采用通流设计与叶片造型相互迭代的方式开展大流量跨声速风扇设计研究。此风扇级的设计点为巡航状态,设计流量为155kg/s、压比为1.54。研究结果表明:在设计状态,此风扇级的总压比为1.545,转子和级效率分别为0.939、0.916;在设计转速下,失速裕度为17%,转子和级最高效率分别为0.945、0.923;在起飞状态,流量接近440kg/s,效率与巡航状态相当,压比高于巡航状态。
In order to consider the blade swept effect in the design stage of the compressor flow, a flow-through design procedure based on the flow curvature method is developed. A method for modeling the mid-arc blade based on the fourth degree polynomial is proposed. Arc curve expression. Based on this method, the design of large-flow transonic fan is studied by means of iterative flow between the through-flow design and the blade modeling. This fan-level design point for the cruise state, the design flow of 155kg / s, pressure ratio of 1.54. The results show that the overall pressure ratio of this fan stage is 1.545 and the rotor and stage efficiencies are 0.939 and 0.916, respectively. At design speed, the stall margin is 17% and the maximum rotor and stage efficiencies are 0.945 and 0.923, respectively ; At take-off condition, the flow rate is close to 440kg / s, the efficiency is equal to the cruising condition, and the pressure ratio is higher than the cruising condition.