For the embodiment of vanes based on FIG

For the embodiment of vanes based on FIG

3 , both border 38, 39 become each in essence right and each organized in an airplane normal to axis 47. The trailing edge 39 is, with regards to the industry leading 38, vertically shifted in FIG. 3 (out from the drawing covering, in other words. trailing advantage 39 lies above industry leading 38). As illustrated in FIG. 3 , the trailing sides 38 is horizontally moved (to the left inside design layer). In addition, the trailing edge 39 are rotated clockwise by about 20 degrees according to the innovative 38.

The sucking part 31 (experiencing left in FIG. 3 ) and the pressure side 32 (experiencing to the right in FIG. 3 ) stretch through the leading edge 38 downstream on trailing advantage 39. The sucking side 31 is basically concavely shaped in the direction of the axis 47 and the pressure area 32 is basically convexly shaped in the direction of the axis 47. Toward the main sides 38, the sucking part 31 of vane 3 based on FIG. 3(a) is basically level or somewhat concavely formed plus the suction area 31 of vane 3 in accordance with FIG. 3(b) was concavely molded, whereas the pressure area 32 of vane 3 relating to FIG. 3(a) is essentially level or somewhat convexly shaped and also the pressure area 32 of vane 3 per FIG. 3(b) is basically convexly designed. The trailing sides 39 is essentially direct and rotated, for example. they runs, with increasing R, inside way in which the pressure side 32 faces. The release stream angle I± improves with improving distance roentgen.

The vanes 3 in FIG. 3 cause the fuel flow on the stress area 32 to get pushed toward the minimum distance Rmin, therefore filling the inner an element of the annulus, whilst the fuel flow on sucking part 31 is actually driven radially outwardly toward the maximum radius Rmax, thereby filling the outer an element of the annulus. …