Tham khảo tài liệu 'compressor instability with integral methods episode 1 part 2', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Chapter 1 Study on the Propagation of Inlet Flow Distortion in Axial Compressor Using an Integral Method An integral method is presented in this chapter. The integral method is proposed by Kim et al. at 1996 aimed to describe the problems of distorted inlet flow propagation in axial compressors. In this method the detained blade rows are replaced by their equivalent force field and the Navier-Stokes equation can be simplified by using integral technique. Despite the great simplifications adopted in the integral method the multistage axial compressor with large inlet distortion including back flow can be analyzed and a qualitative trend of distortion propagation can be described successfully. The integral method provides the useful information about the performance of the axial compressor with inlet distortion which is meaningful to engineering application in the design and analysis of turbomachinery. In this chapter by applying the integral method the effects of the parameters of inlet distortions on the trend of downstream flow feature in compressor calculated numerically is described. Other than the ratio of drag-to-lift coefficients of the blade and the angle of flow the value of distorted inlet velocity is found to be another essential parameter to control the distortion propagation. Based on this calculation a critical distortion line and corresponding distortion propagation factor are proposed to express the effect of the two main inlet parameters the angle of flow and the distorted inlet velocity on the propagation of distortion. From the viewpoint of compressor efficiency the distortion propagation is further described by a compressor critical performance. The results present a useful physical insight of compressor axial behavior and asymptotic behavior of the propagation of inlet distortion and confirm the active role of compressor in determining the velocity distribution when compressor responds to an inlet flow distortion. Introduction In the .
