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Compressor Instability with Integral Methods Episode 1 Part 7

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Tham khảo tài liệu 'compressor instability with integral methods episode 1 part 7', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Chapter 4 A Development of Novel Integral Method for Prediction of Distorted Inlet Flow Propagation in Axial Compressor Based on the original integral method and its applications mentioned and discussed in previous chapters an improved integral method is proposed and developed for the quantitative prediction of distorted inlet flow propagation through axial compressor. The novel integral method is formulated using more appropriate and practical airfoil characteristics with less assumption needed for derivation. The results indicate that the original integral method 6 underestimated the propagation of inlet flow distortion. The effects of inlet flow parameters on the propagation of inlet distortions as well as on the compressor performance and characteristic are simulated and analyzed. From the viewpoint of compressor efficiency the propagation of inlet flow distortion is further described using a compressor critical performance and its associated critical characteristic. The results present a realistic physical insight to an axial flow compressor behavior with a propagation of inlet distortion. 4.1 Introduction Compression system is an important component of the gas turbine engine and its performance strongly influences the performance of all other components. The operational envelopes of modern compressors also demand a challenging trade-off between safety and performance due to the inherent aerodynamic instabilities associated with compressor stall. Various dynamic events such as distorted inlet flow in axial compressor rotor blade tip clearance changes rapid changes in the operating conditions fuel throttling may cause the componentmismatch and instability problems including rotating stall or even surge oscillations in the mass flow rate or a combination of them which might result in catastrophic damage to the entire engine. Engines are thus constrained to operate below the surge line termed as a safe surge margin. Because the safe surge margin must accommodate