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US 2014/0178187 A1Published application
Staggered double row, slotted airfoil design for gas turbine exhaust frame
AssigneeGeneral Electric Company
InventorsKunal Upendra SAKEKAR, Moorthi SUBRAMANIYAN, Srinivasarao PAKKALA
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Abstract
A gas turbine exhaust frame includes an inner barrel and an outer barrel establishing an annular exhaust gas flow path therebetween. A plurality of airfoils extend radially between the inner barrel and the radially, outer barrel, the plurality of struts arranged in first and second axially-spaced and circumferentially-staggered rows.
Claims20
A gas turbine exhaust frame comprising:
- an inner substantially cylindrical wall;
- an outer substantially cylindrical wall establishing an annular exhaust gas flow path therebetween;
- and
- a plurality of airfoils extending radially between said inner wall and said outer wall, said plurality of airfoils arranged in first and second axially-spaced, circumferentially-staggered rows.
1 more element
A gas turbine exhaust diffuser comprising:
- a frame having an inner substantially cylindrical wall and an outer substantially cylindrical wall defining an annular exhaust gas flow channel;
- and
- a plurality of airfoils extending between said inner and outer walls, said plurality of airfoils arranged in first and second axially-spaced, circumferentially-staggered rows, wherein said first and second axially-spaced, circumferentially-staggered rows at least partially overlap in an axial direction.
A gas turbine exhaust diffuser comprising:
- a frame having an inner substantially cylindrical wall and an outer substantially cylindrical wall defining an annular exhaust gas flow channel;
- a plurality of airfoils extending between said inner and outer walls, said plurality of airfoils arranged in first and second annular, axially-spaced, and circumferentially-staggered rows;
- each of said plurality of airfoils having a leading edge and a trailing edge and a slot extending radially along and adjacent at least a portion of said leading edge, said slot having an inlet on one side of said airfoil extending angularly in a downstream direction to an outlet on an opposite side of said airfoil.
Dependencies are inferred from the claim text.