Mounting apparatus for low-ductility turbine shroud
A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
1. A shroud apparatus for a gas turbine engine, comprising:
an annular metallic hanger;
a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the outer wall having a mounting hole, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and
a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction, wherein the retainer includes a central portion with a pair of opposed arms extending laterally outward therefrom wherein the central portion is raised above the arms in the radial direction defining a clamping surface, the clamping surface exposed through the mounting hole, and a radially-aligned bore extending through the central portion, the radially-aligned bore configured to accept a fastener.
2. The apparatus of claim 1 wherein the distal end of each arm includes a concave-curved contact pad.
3. The apparatus of claim 1 wherein a surface of the retainer is clamped against the hanger, and the outer wall of the shroud segment is trapped between the hanger and a portion of the retainer.
4. The apparatus of claim 3 wherein a spring is clamped between the hanger and the retainer and resiliently bears against the shroud segment so as to urge it radially inboard against the retainer.
5. The apparatus of claim 1 wherein the inner wall extends axially forward past the forward wall to define a forward overhang and the inner wall extends axially aft past the aft wall to define an aft overhang.
6. The apparatus of claim 1 wherein the hanger is surrounded and carried by an annular turbine case.
7. The apparatus of claim 6 wherein the hanger includes axially-spaced-apart forward and aft hooks which are received by forward and aft rails of the turbine case, respectively.
8. The apparatus of claim 1 further comprising a hollow impingement baffle disposed inside the shroud segment.
9. The apparatus of claim 8 wherein a coolant feed passage extends through the hanger and connects to the interior of the impingement baffle.
10. The apparatus of claim 1 wherein the shroud segment comprises a ceramic matrix composite material.
11. The apparatus of claim 1 wherein an annular ring of shroud segments are arranged in an annular array within the casing.
12. The apparatus of claim 1 further including a transition wall disposed between the forward and outer walls and extending at acute angles to both the forward and outer walls.
13. A shroud apparatus for a gas turbine engine, comprising:
an annular metallic hanger including an arcuate body and axially-spaced-apart forward and aft inner legs extending radially inward from the body, the forward inner leg including an arcuate forward bearing surface and the aft inner leg including an arcuate aft bearing surface, the forward inner lea having a coolant feed passage for flowing air through;
a shroud segment disposed inboard of the hanger, comprising low-ductility material, having a transfer passage for flowing air through, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a hollow impingement baffle disposed inside the shroud segment, the baffle having impingement holes for flowing air through;
wherein the shroud segment is mounted relative to the hanger such that the forward bearing surface bears against the forward wall and the aft bearing surface bears against the aft wall, such that the shroud segment and the hanger cooperatively define a plenum therebetween; and wherein during operation of the gas turbine engine, air flows through the coolant feed passage, then the air flows through the transfer passage, and then the air flows through the impingement holes, and after flowing through the impingement holes, the air pressurizes the plenum.
14. The shroud apparatus of claim 13 further comprising a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
15. The shroud apparatus of claim 13 wherein the aft inner leg resiliently loads the shroud segment axially forward against the forward bearing surface of the hanger.