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为提高多级轴流压气机气动性能,采用轴流压气机叶片全三维粘性反问题求解方法,对多级轴流压气机反问题级间气动匹配设计方法进行了研究。以压气机级出口旋流角为设计目标,叶片表面载荷分布为设计对象,通过动量矩守恒方程,建立起叶片出口旋流角与叶片表面载荷分布的关系,从而实现计算过程中载荷的自动调整,修正气流在叶片出口旋流角分布。为了让压气机每一级都工作在设计给定的进口条件下,对上游级静子叶片进行反问题改型设计,使得其出口旋流角分布满足设计给定值。为了验证方法的有效性,采用四级高压压气机作为算例,对其初始设计进行反问题匹配改型设计。通过计算,修正了三个级间位置的旋流角分布,改善了下游级进口工作条件。气流在改型后压气机内部流动更加符合设计意图,级与级之间流动匹配更好。与原型相比,总压比和绝热效率分别提高了2.8%和1.3%,验证了方法的有效性。
In order to improve the aerodynamic performance of multistage axial-flow compressor, a three-dimensional viscous viscous inverse problem solving method of axial-flow compressor blades is adopted to study the aerodynamic matching design method of multistage axial-flow compressor inverse problems. Taking the outlet angle of the compressor stage as the design goal and the load distribution on the blade surface as the object of design, the relationship between the swirl angle of blade outlet and the load distribution on the blade surface is established by the momentum moment conservation equation to realize the automatic adjustment of the load during the calculation , Corrected airflow distribution at the blade swirl angle. In order to let the compressor work at each level of the design given the inlet conditions, the upstream stage stator blade retrofitting design problems, making the outlet swirl angle distribution to meet the design given value. In order to verify the effectiveness of the method, a four-stage high-pressure compressor is used as an example to reverse-match the initial design of the original design. Through the calculation, the distribution of the swirling angle at the three levels is corrected, and the working conditions of the downstream import are improved. Air flow in the modified compressor flow more in line with the design intent, level and level of flow between the better. Compared with the prototype, the total pressure ratio and the adiabatic efficiency increased by 2.8% and 1.3% respectively, which proves the effectiveness of the method.