摘要
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 performance of multistage axial compressor, a new aerodynamic match- ing design method for multistage axial compressor is developed based on the three-dimensional viscous inverse method. The swirl of the compressor stage exit is chosen as the design objective and the design variable is the blade pressure loading distribution on the blade surface. The relationship between blade exit swirl and blade sur- face pressure loading distribution is established based on the angular momentum conservation. The blade pres- sure loading is automatically adjusted during the computation process to modify the blade exit swirl. In order to en- sure that each stage of compressor is working under the specified inlet operation condition, the stator of upstream stage is redesigned using the inverse design method. The exit swirl of upstream stage is adjusted to satisfy the de- sign value. In order to validate the effectiveness of present method, an aerodynamic matching design using in- verse method is carried out on a 4 stage high-pressure axial compressor original design configuration, which is used as the test case. The exit swirl on three axial positions between stages is modified to improve the inlet opera- tion condition of downstream stage. The flow in the compressor blade passage satisfies the design intent and matches better between stages. Compared with original design, the total pressure ratio and adiabatic efficiency of compressor is improved by 2.8% and 1.3%, which demonstrated the effectiveness and accuracy of present method.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2017年第9期1987-1994,共8页
Journal of Propulsion Technology
关键词
气动匹配
反问题设计方法
多级轴流压气机
载荷分布
Aerodynamic matching
Inverse method
Muhistage axial compressor
Pressure loading dis-tribution
