| 摘要 |
A turbine rear frame (34) includes a row of outlet guide vanes (36) extending between outer and inner bands (38,40). Each of the vanes (36) is bifurcated into a forward prow (44) integrally joined to an aft stern (46) by a septum (48) therebetween. The prow (44) and stern (46) collectively define the aerodynamic profile of each vane which is locally interrupted at the septum (48).
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