Gas turbine engine with a rotor stage shroud

1 . A gas turbine engine having an axial centerline, the gas turbine engine comprising:

a compressor section;

a combustor section; and

a turbine section, wherein the turbine section includes a rotor stage and an annular shroud assembly, wherein the rotor stage includes a bladed rotor;

wherein the annular shroud assembly is disposed radially outside of the bladed rotor, and extends circumferentially around the bladed rotor, and is coupled with a turbine support case, wherein the annular shroud assembly comprises:

a shroud comprising a plurality of shroud segments that collectively form the shroud, wherein each shroud segment includes a ring portion, a forward leg, and an aft leg;

a shroud segment housing;

a cover; and

a plurality of shroud pins disposed to connect the shroud to the shroud segment housing and the cover;

wherein the shroud segment housing and the turbine support case are engaged with one another and are configured to permit relative movement therebetween; and

wherein the annular shroud assembly and the turbine support case are configured to permit radial movement between the annular shroud assembly and the entirety of the turbine support case.

2 . The gas turbine engine of claim 1 , wherein the annular shroud assembly is configured to accommodate disparate thermal expansion of the shroud relative to the turbine support case.

3 . The gas turbine engine of claim 1 , wherein the shroud segment housing and the turbine support case are configured to permit radial movement between the shroud segment housing and the turbine support case.

4 . The gas turbine engine of claim 3 , wherein the shroud segment housing and the turbine support case are configured with mating male and female elements that permit radial movement between the shroud segment housing and the turbine support case.

5 . The gas turbine engine of claim 4 , wherein the shroud segment housing includes a plurality of lugs and the turbine support case includes a plurality of slots configured to receive the lugs.

6 . The gas turbine engine of claim 5 , wherein the turbine support case includes a first flange segment that extends axially out from a radially extending second flange segment, wherein the slots are disposed in the second flange segment.

7 . The gas turbine engine of claim 1 , wherein each shroud pin of the plurality of shroud pins extends through the forward leg and the aft leg of one of the shroud segments of the plurality of shroud segments.

8 . The gas turbine engine of claim 7 , wherein the ring portion of each shroud segment of the plurality of shroud segments has an inner radial surface and an outer radial surface and the forward leg and the aft leg extend outwardly from the outer radial surface of the ring portion.

9 . The gas turbine engine of claim 7 , wherein the shroud segment housing includes a central member and a forward flange, and the plurality of shroud pins are engaged with the central member.

10 . The gas turbine engine of claim 9 , wherein the cover includes an axial segment and a radial segment, wherein the axial segment is connected to the radial segment and extends outwardly from the radial segment.

11 . The gas turbine engine of claim 10 , wherein a first end of each shroud pin of the plurality of shroud pins is engaged with the central member, and a second end of each shroud pin of the plurality of shroud pins is engaged with the radial segment.

12 . The gas turbine engine of claim 11 , wherein the forward flange is in contact with the axial segment.

13 . The gas turbine engine of claim 1 , wherein the annular shroud assembly further comprises a cover retaining ring engaged with the turbine support case.

14 . The gas turbine engine of claim 13 , wherein the turbine support case includes a first flange segment that extends axially out from a radially extending second flange segment, wherein the first flange segment includes a ring slot configured to receive the cover retaining ring; and

wherein axial movement of the annular shroud assembly is axially constrained by the second flange segment and the cover retaining ring.

15 . The gas turbine engine of claim 1 , wherein the turbine support case includes a first flange segment that extends axially out from a radially extending second flange segment, and the first flange segment includes a plurality of cooling apertures that provide fluid communication between a first region radially outside of the turbine support case and a second region radially inside of the turbine support case that is in fluid communication with the annular shroud assembly.

16 . The gas turbine engine of claim 1 , wherein the plurality of shroud segments comprise a ceramic matrix composite material.

17 . A rotor stage shroud assembly for a gas turbine engine, the gas turbine engine having a turbine support case and a turbine section that includes a rotor stage with a bladed rotor, wherein the turbine support case is disposed radially outside of the rotor stage, the shroud assembly comprising:

a shroud comprising a plurality of shroud segments that collectively form the shroud, wherein each shroud segment includes a ring portion, a forward leg, and an aft leg;

a shroud segment housing;

a cover; and

a plurality of shroud pins disposed to connect the shroud to the shroud segment housing and the cover;

wherein the shroud segment housing and the turbine support case are engaged with one another and are configured to permit relative movement therebetween; and

wherein the shroud segment housing is configured to permit radial movement between the shroud segment housing and the entirety of the turbine support case.

18 . The rotor stage shroud assembly of claim 17 , wherein the shroud segment housing includes a plurality of lugs configured to be received within slots disposed in the turbine support case.