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Compressor Instability with Integral Methods Episode 2 Part 6

Tham khảo tài liệu 'compressor instability with integral methods episode 2 part 6', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Index A Airfoil characteristics argument for 99 Angle of attack 75 Axial compressor distorted inlet flow propagation in prediction of 77-79 results compressor characteristics 96-98 inlet distorted velocity coefficient 87-88 inlet incident angle 88-91 lift and drag coefficients 86 propagation of distortion level 91-95 theoretical formulation 79-86 Axial compressor propagation of inlet flow distortion in using integral method 1-3 numerical method equations 11 4th-order Runge-Kutta Equations 11-12 results 13-17 asymptotic behavior results 17-20 compressor performance and characteristic 23-26 critical distortion line 22-23 mass flow rate 20-22 theoretical formulation 3-4 distorted region 7-8 entire region 9-10 forces 5-7 integral equations 10-11 undistorted region 8 velocity and pressure 4-5 C CFD codes 78 Chebyshev curve fitting 101-106 Complex flows numerical simulation of 78 Compression system 77 Compressor characteristics 96-98 performance 57-58 three dimensional flows in 41 Critical distortion line 3 35-39 application of 45-46 D Dimensionless velocity components 43 Distorted inlet flow 43 Distorted inlet flow propagation in axial compressor prediction of 77-79 results airfoil characteristics argument for 99 compressor characteristics 96-98 inlet distorted velocity coefficient 87-88 inlet incident angle 88-91 lift and drag coefficients 86 propagation of distortion level 91-95 theoretical formulation 79-86 Distortion level 87 Drag-to-lift ratio 64-68 F Flaming of refueling leakage near inlet and stall prediction of in-flight compressor 41-42 compressor characteristics 50-51 inlet distorted region size 0 effects 53-55 rotor blade speed ơ effects 52-53 computational domain 43-45 critical distortion line application of 45-46 inlet flow condition 42-43 Flow non-uniformities 2 Force field 79 Fortran Program critical distortion line 35-40 integral method 28-34 132 Index G Gas turbine engine 57 Greitzer s B-parameter model 107 108 110 Greitzer s instability flow model .