Claims
- 1. For a gas turbine engine that includes a compressor section having a plurality of rows of rotors and a plurality of rows of segmented stators, each of said rows of segmented stators having a plurality of circumferentially spaced vanes defining multi-stages of compression, a compressor outer case for supporting said rows of stators, at least one row of said rows of segmented stators having a fore edge and an aft edge, outer wall means disposed adjacent to said fore edge and said aft edge and being segmented to complement the segments of said segmented stators, said segmented outer wall means having a plurality of sets of hooks extending radially outward from said outer wall means and being spaced in a circumferential direction, two sets of said plurality of hooks with one each of said two sets of hooks being disposed at the opposite ends of said one row of segmented stators, a third set of hooks of said plurality sets of hooks being disposed intermediate said two sets of hooks, each set of hooks of said plurality of hooks including two axially spaced hooks, a plurality of floating lug-nuts each including a first pair and a second pair of radially extending pins fitting into slots formed in each of said two axially spaced hooks of each of said two sets of hooks, a third pair of radially extending pins fitting into slots formed in said third set of hooks, said first pair of pins and said second pair of pins being loosely fitted in the axial and circumferential direction in said slots and said third pair of pins being loosely fitted in the axial direction and tightly fitted in the circumferential direction in said slots and bolt means extending through an aperture formed in said outer case threadably engaging at least one of said lug-nuts for securing said segmented stators to said compressor outer case.
- 2. For a gas turbine engine as claimed in claim 1 wherein each of said axially spaced hooks of said hook sets includes a vertical portion and a horizontal portion defining a cavity, each of said plurality of lug-nuts includes an axial extending portion disposed in said cavity and extending to underlie said horizontal portion, said first pair of pins, said second pair of pins and said third pair of pins operatively connected to said hooks through said slots formed in said horizontal portion.
- 3. For a gas turbine engine as claimed in claim 2 wherein said horizontal portion of each of the axially spaced hooks in a set of hooks face each other, and each of said pins extend in said slots formed in each axially spaced hooks of said set of hooks that face each other.
- 4. For a gas turbine engine as claimed in claim 3 wherein said outer case includes a plurality of separate cases for supporting stages of said multi-stage compression, one case of said separate cases having a shoulder supporting said arcuate segmented stator vanes, said outer wall means having an edge portion complementing and adjacent to said shoulder defining therewith a gap for allowing axial thermal expansion of said one case of said separate cases.
- 5. For a gas turbine engine as claimed in claim 4 wherein said wall means includes a first annular wall supporting a first plurality of vanes in one of said rows, a second annular wall supporting a second plurality of vanes in another of said rows, and a third annular wall supporting a third plurality of vanes in a third of said rows, said first annular wall having a first side surface and said second annular wall having a second side surface complementing said first side surface, said third annular wall having a third side surface, said second annular wall having another side surface complementing said third side surface, said means for attaching said wall means including a weldment between said first side surface and said second side surface and an additional weldment between said another side surface and said third side surface.
- 6. For a gas turbine engine as claimed in claim 4 wherein said wall means includes a first annular wall supporting a first plurality of vanes in one of said rows, a second annular wall supporting a second plurality of vanes in another of said rows, and a third annular wall supporting a third plurality of vanes in a third of said rows, said first annular wall having a first side surface and said second annular wall having a second side surface complementing said first side surface and being disposed in side by side relationship, said third annular wall having a third side surface, said second annular wall having another side surface complementing said third side surface and being disposed in side by side relationship, said means for attaching said wall means includes complementing flange means radially extending from each of said first annular wall means, said second annular wall means and said third annular wall means, and securing means extending through complementing holes formed in said complementing flange means for attaching said first annular wall, said second annular wall and said third annular wall.
- 7. For a gas turbine engine as claimed in claim 1 wherein said bolt means includes a plurality of bolts each of which having a shank portion threaded at one end and a head portion, and said shank portion extending through a plurality of apertures formed in said outer case and threadably engaging said plurality of lug-nuts and said head portion bearing against said outer case.
Government Interests
This invention was made under a U.S. Government contract and the Government has rights herein.
US Referenced Citations (6)