| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: proposed turbojet engine comprises intake nozzle, compressor, combustion chamber, turbine, afterburner and jet nozzle. Outlet and inlet edges of the blade airfoil portion are formed by two parabolas, i.e. y1=K1X1/2, y2=2Ro+K2X1/2, tangential to circumference with radius RëÑ2Ro and center located at lëÑ(2/3)L, where L is the projection of airfoil section length on coordinate X. Angle of attack and inclination = (7- 15). Radius Ro makes (1/5 -1/10)L. Circumference radius R equals (2 - 3)Ro. Projection of airfoil section L makes (0.05 - 0.15) m, that of the center of circumference with radius R equals lëÑ(2/3)L. Factors K1 and K2 are calculated from the formulas, i.e. K1=y1A/X1/2Çè1A; K2=(Y2B-2Ro)/X1/2Çè2B, where points A and B are those whereat aforesaid parabolas y1 and y2 touch circumference with radius R. Point A is determined by making inclination angle = (7 - 15) cross the perpendicular re-established from point lëÑ(2/3)L, point B is the end of R-radius circumference diametre put aside from point A. Profiles of blade pressure surface and its back are formed by intersection of parabolas y3=K3X1/2, y4=2RÇÇèo+K4X1/2, where factors K3 and K4 are selected from the following magnitudes, i.e. K3=(1 - 3), K4=(0.4 - 0.8) K3. Front edge of airfoil section is rounded to radius of RÇëÑRÇÇèo. Airfoil section end is radially bent along radius RëÑRo through angle = (45 - 60). ^ EFFECT: higher efficiency. ^ 3 cl, 7 dwg |
