Tham khảo tài liệu 'compressor instability with integral methods episode 1 part 6', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Chapter 3 Parametric Study of Inlet Distortion Propagation in Compressor with Integral Approach and Taguchi Method As mentioned and discussed in previous chapters the integral method can successful to describe the qualitative trend of distorted inlet flow propagation in the axial compressors. Generally integral method is applied to the problems of distorted inlet flow and the relationships and the effects that some of the key parameters would have on the propagation of inlet distortion flow were predicted in qualitative trend as illustrated in Chap. 1. In this chapter a Taguchi s quality control method 12 will be adopted to justify the integral method and its research results. The results from Taguchi s quality control method indicate that the influence of major parameters on the inlet distortion propagation can be ranked as the most one of the ratio of drag-to-lift coefficient then the inlet distorted velocity coefficient and the least one of inlet flow angle. This conclusion is different from that in Kim et al. s research reason being the later was carried out using only several cases with integral method. In comparison when Taguchi quality control method is used the prediction of degrees of influence by the parameters on the distortion propagation is more reasonable and accurate. Introduction The gas turbine engine has contributed greatly to the advancement of current flight capabilities in terms of aircraft performance and range. The propulsive power of the gas turbine has increased since World War II through higher cycle pressure ratios and turbine inlet temperature. The compressor is a key component to this evolution. In general it is more difficult to attain high efficiency on the compressor stages. Compressors must achieve high efficiency in blade rows in diffusing flow fields. However stable operation of the engine depends on the range of stable operation of the compressor and the blade row stall characteristics determine the limit of stable operation.
