By Eddie Y.K. Ng, N. Y. Liu
This ebook brings jointly the short necessary techniques and advances within the box for the prediction of stall and surge difficulties within the compressor. The booklet comes in handy for individuals excited by the circulate research, layout and checking out of rotating equipment. for college students, it may be used as a really good subject of senior undergraduate or graduate research. The publication may also function self-study material.
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Additional resources for Compressor instability with integral methods
PRESSURE SI0=SITA1 SITA0=SITA1*PI/180. 001 AL1=ALFA(1,1) 10 CK1=Y(1)*ALFA(1,1) CK0=CK1+(1-CK1/ALFA(1,1))*ALFA(3,1) ! K1 ! *(FX1*FX2*FX3*FX4+FX5*FX6*FX7*FX8) ! *(FX1*FX2*FY1*FX4-FX5*FX6*FY2*FX8) ! * & ! * & ****** ! FY,0/U0**2 (FX01*FX02*FY01*FX04-FX05*FX06*FY02*FX08) END OF FORCE CALCULATION ******** ********************************************************** ****** CK2=CK1*(CK1-CK0)/(ALFA(1,I-1)-CK1)**2 ! *CK1*(CK1-CK0)**2/(ALFA(1,I-1)-CK1)**3 ! K3 ITERATIVE CONSTANTS ****** DO 100 K=1,5 100 A(K)=ALFA(K,I-1) F(1,I)=(FXU(I)-FX0U(I))/(CK3*A(1)) F(2,I)=FYU(I)/(GAMA*A(1)) 38 Chapter 1 Study on the Propagation of Inlet Flow Distortion F(3,I)=CK2*F(1,I) F(4,I)=FY0U(I)/(GAMA*A(3))-A(4)/A(3)*CK2*F(1,I) F(5,I)=(FXU(I)-F(1,I))/(GAMA**2*2) DO 101 K=1,5 101 RK(1,K,I)=DX*F(K,I) !
8 Fig. 6. 4 Results and Discussion 17 Case 1, case 2 and case 4 can be combined to a single case of “critical distortion line” that to be discussed in the next section. Case 3 is not necessary because the interest here is distorted inlet propagation. The affecting parameters should involve only that of the inlet conditions. The compressor should be considered as a given geometric domain. As to the asymptotic behavior situation, case 5, there is much further work to do, which will be mentioned next also.
2 Inlet Flow Condition As an example, consider a situation of air-to-air refueling when a leakage of fuel enters the engine nacelle together with the inlet air. Some of the smaller droplets of leakage fuel vaporize and form a vapor-air mixture. When this mixture reach the fan blade or first stage of compressor with temperature of about 15 °C (much higher value if past the IGV) during refueling, the mixture may well be within the range of flammability, especially for the more volatile wide-cut fuel.