| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide an improved type turbine improving performances of a gas turbine engine with selectively corresponding to high temperature of combustion gas and low temperature streak. <P>SOLUTION: A duplex turbine nozzle (20) includes a row of different first and second vanes (36, 38) alternating circumferentially between radially outer and inner bands (40, 42) in vane doublets (34) having axial splitlines (44) therebetween. The vanes (36, 38) have opposite pressure and suction sides surfaces (46, 48) spaced apart in each doublet (34) to define an inboard flow passage (54) therebetween, and corresponding outboard flow passages (56) between the doublets (34). The vanes (36, 38) have different patterns of film cooling holes (62) with larger cooling flow density along the outboard passages (56) than along the inboard passages (54). <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
