| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a gas turbine engine assembly in which the formation of swirl flow along the leading edge of a stationary blade is minimized. <P>SOLUTION: This turbine engine nozzle assembly comprises an outer band 54 having a leading edge 70, a trailing edge 74, and a body 78 disposed therebetween, an inner band 56 having a leading edge 72, a trailing edge 76, and a body 80 disposed therebetween, and at least one stationary blade 52 extending between the outer and inner bands, and having a first side wall 60 and a second side wall 62 connected to each other at the leading edge 64 and the trailing edge 66. The leading edge of at least one stationary blade is positioned on the downstream side of the leading edges of the inner and outer bands. The turbine engine nozzle assembly further comprises a tip part fillet 170 extending between at least one stationary blade and at least one of the inner band and the outer band and structured adjacent to at least either of the inner and outer bands to minimize the formation of swirl flow along the tip part of the stationary blade. <P>COPYRIGHT: (C)2007,JPO&INPIT</p> |
