Aircraft turbine rear structures
AssigneeGKN Aerospace Sweden AB
InventorFredrik Wallin
Life of this patent
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Abstract
A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.
Claims21
-26. (canceled)
A turbine rear structure for a gas turbine engine comprising:
- a central hub;
- a circumferential outer ring coaxial with the central hub;
- a plurality of guide vanes extending radially between the central hub and the circumferential outer ring;
- and
- an intermediate guide vane positioned in a space defined between adjacent guide vanes, wherein the intermediate guide vane is positioned closer to one of the guide vanes than the other guide vane.
The turbine rear structure of claim 38, wherein the intermediate guide vane has a chord length and wherein a leading edge of the intermediate guide vane is displaced axially from the region of maximum negative pressure by a distance of twenty-five percent plus or minus fifteen percent of the chord length.
A method of manufacturing a turbine rear structure comprising:
- (A) forming a central hub and a circumferential outer ring,
- (B) connecting a plurality of a guide vanes to extend radially between the central hub and the circumferential outer ring;
- (C) positioning an intermediate guide vane between adjacent guide vanes, wherein the intermediate guide vane is located asymmetrically with respect to the adjacent guide vanes.
Dependencies are inferred from the claim text.