Tham khảo tài liệu 'compressor instability with integral methods episode 1 part 4', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Chapter 2 Stall Prediction of In-flight Compressor due to Flaming of Refueling Leakage near Inlet In this chapter the critical distortion line and the integral method explained in Chap. 1 are extended further to investigate more practical applications about the propagation of strong distortion at inlet of an axial compressor. The practical applications such as the inlet conditions of flaming of leakage fuel during mid-air refueling process are implemented to show the details of the numerical methodology used in analysis of the axial flow compressor behavior and the propagation of inlet distortion. From the viewpoint of compressor efficiency the propagation of inlet flow distortion is further described by compressor critical performance and its critical characteristic. The simulated results present a useful physical insight to the significant effects of inlet parameters on the distortion extension velocity and compressor characteristics. The distortion level flow angle and the size of distortion area at compressor inlet and the rotor blade speed are found being the major parameters affecting the mass flow rate of engine. Introduction The inlet flow distortion may cause the rotating stall surge or a combination of both. An inlet distortion is often encountered when the real flow is associated with some degree of angle of attack to the engine nacelle. Take-off landing and gust encounter are some typical examples of such situation. On the other hand the inlet distortion can also occur when the leakage of fuel enters the compressor and consumes part of the mass during the air to air refueling. Since a severe inlet distortion may lead to a stall of fan blade and fatal loss of engine power the evaluation of inlet distortion effects is very important in the engine safety problem. If such evaluation can be measured quantitatively the designer may be able to design the compressor stage with a minimum effect of inlet distortion 3 4 and 5 . With the rapid development in .
