TURBOJET ENGINE Russian patent published in 2009 - IPC F01D5/14 F02K3/02 

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=K₁X^1/2, y₂=2R_o+K₂X^1/2, tangential to circumference with radius R≥2R_o and center located at l≥(2/3)L, where L is the projection of airfoil section length on coordinate X. Angle of attack and inclination α = (7°- 15°). Radius R_o makes (1/5 -1/10)L. Circumference radius R equals (2 - 3)R_o. Projection of airfoil section L makes (0.05 - 0.15) m, that of the center of circumference with radius R equals l≥(2/3)L. Factors K₁ and K₂ are calculated from the formulas, i.e. K₁=y_1A/X^1/2 _1A; K₂=(Y_2B-2R_o)/X^1/2 _2B, 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 α = (7° - 15°) cross the perpendicular re-established from point l≥(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=K₃X^1/2, y₄=2R^• _o+K₄X^1/2, 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 R^•≥R^• _o. Airfoil section end is radially bent along radius R≥R_o through angle β = (45° - 60°).

EFFECT: higher efficiency.

3 cl, 7 dwg