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对转压气机(CRC)由于其独特的气动和结构优势而被认为是进一步提高航空发动机推重比的重要技术途径之一。在小扰动理论的基础上发展了对转压气机旋转失速的小扰动分析方法,并以实验室对转压气机为研究对象,采用小扰动理论和计算流体力学(CFD)数值模拟两种方法对不同转速匹配工况下的最先失速级位置进行了相应的研究,为对转压气机失速边界的预估探索一种快速有效的方法。研究结果表明:①旋转失速的小扰动分析方法可以较好地预估对转压气机失速边界和最先失速级位置;②小扰动分析方法和CFD计算结果均显示:转速匹配方案对对转压气机最先失速级位置存在明显的影响。当转速比大于或等于0.9时,转子2为最先失速级;当转速比小于0.9时,转子1为最先失速级;③由于小扰动分析方法进行了大量的简化,因而使得预估值同实际值之间存在相应的误差。同时,由于对转压气机级间存在较强的非定常性,进而使得相对误差进一步增大。
Due to its unique aerodynamic and structural advantages, rotary compressor (CRC) is considered as one of the important technical ways to further improve the thrust-weight ratio of aeroengines. Based on the theory of small disturbance, a small disturbance analysis method is developed for the rotating stall of a rotary compressor. Taking the laboratory compressor as the research object, small disturbance theory and computational fluid dynamics (CFD) numerical simulation Corresponding research is made on the position of the first stalling stall under different speed matching conditions, which is a fast and effective method for estimating the stalling boundary of the turbo compressor. The results show that: (1) The small disturbance analysis method of rotating stall can predict the stalling stall and the position of the first stalling stage better; (2) The small disturbance analysis and CFD calculation show that the speed matching scheme There is a significant effect on the position of the machine at the first stall level. When the speed ratio is greater than or equal to 0.9, the rotor 2 is the first stalling stage; when the speed ratio is less than 0.9, the rotor 1 is the stalling stage; ③ Because of the large simplification of the small disturbance analysis method, There is a corresponding error between the actual values. At the same time, the relative error is further increased due to the strong unsteadiness of the compressor stage.