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, the turbine support case includes an axially extending first flange segment and a radially extending second flange segment;

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, the aft leg mounted to the second flange segment;

a shield member having a central channel;

a shroud retaining ring disposed in the central channel; and

a cover coupled with the turbine support case;

wherein the shield member is disposed between the shroud retaining ring and the shroud;

wherein a portion of the shield member is disposed between the forward leg and the aft leg; and

wherein the shroud is mounted to the cover and the turbine support case.

2 . The gas turbine engine of claim 1 , wherein the shroud is configured to permit radial movement of the shroud relative to the cover and the turbine support case.

3 . The gas turbine engine of claim 1 , wherein the shroud is configured to accommodate disparate thermal expansion of the shroud relative to the cover and the turbine support case.

4 . The gas turbine engine of claim 1 , wherein the aft leg of each shroud segment is mounted to the second flange segment by a first locating pin extending between the aft leg and the second flange segment.

5 . The gas turbine engine of claim 4 , wherein the first locating pin is received within a first pin aperture disposed within the aft leg.

6 . The gas turbine engine of claim 5 , wherein the first pin aperture and the first locating pin are configured to allow travel of the first locating pin within the first pin aperture.

7 . The gas turbine engine of claim 1 , wherein the forward leg of each shroud segment is mounted to the cover; and

wherein the cover includes a central member and an aft flange, and the aft flange extends outwardly from the central member; and

wherein the forward leg of each shroud segment is mounted to the central member of the cover by a second locating pin extending between the forward leg and the central member.

8 . The gas turbine engine of claim 7 , wherein the second locating pin is received within a second pin aperture disposed within the forward leg.

9 . The gas turbine engine of claim 8 , wherein the second pin aperture and the second locating pin are configured to allow travel of the second locating pin within the second pin aperture.

10 . The gas turbine engine of claim 1 , wherein the shield member includes a forward flange and an aft flange, and the central channel includes a first side wall, a second side wall, and a base wall that extends between the first and second side walls;

wherein the forward flange extends axially outward from the first side wall, and the aft flange extends axially outward from the second side wall; and

wherein the forward flange is in contact with the forward leg of each shroud segment and the aft flange is in contact with the aft leg of each shroud segment.

11 . The gas turbine engine of claim 10 , wherein the shroud retaining ring is configured to apply a radially inward force to the shield member, and the shield member is configured to transfer the radially inward force to the forward and aft legs of the shroud segments.

12 . The gas turbine engine of claim 1 , wherein the cover includes a central member and an aft flange, wherein the aft flange extends outwardly from the central member to a distal end;

wherein the turbine support case includes an axially extending first flange segment and a radially extending second flange segment, and a stop rib extends outwardly from the first flange segment; and

wherein axial movement of the shroud retaining ring is constrained by the aft flange of the cover and the stop rib of the first flange segment.

13 . The gas turbine engine of claim 1 , wherein the shield member and the cover with the turbine support case define a first annular region, and the turbine support case includes a plurality of apertures that form fluid communication between an outer radial region disposed radially outside of the turbine support case and the first annular region; and

wherein the shield member and the shroud define a second annular region separated from the first annular region.

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

15 . A rotor stage shroud assembly for a gas turbine engine, the gas turbine engine having a turbine support case and turbine section that includes a rotor stage having 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 shield member having a forward flange, an aft flange, and a central channel, wherein the forward flange extends axially outward from the central channel, and the aft flange extends axially outward from the central channel, and the forward flange is in contact with the forward leg of each shroud segment and the aft flange is in contact with the aft leg of each shroud segment;

a shroud retaining ring disposed in the central channel; and

a cover configured to be coupled with the turbine support case;

wherein the shield member is disposed between the shroud retaining ring and the shroud, the central channel of the shield member is disposed between the forward leg and the aft leg, and the shroud is configured for mounting to the cover and configured for mounting to the turbine support case.

16 . The rotor stage shroud assembly of claim 15 , wherein the shroud retaining ring is configured to apply a radially inward force to the shield member, and the shield member is configured to transfer the radially inward force to the forward and aft legs of the shroud segments.

17 . The rotor stage shroud assembly of claim 16 , wherein the shield member is formed from sheet metal.

18 . The rotor stage shroud assembly of claim 15 , wherein the shield member and the cover with the turbine support case define a first annular region; and

wherein the shield member and the shroud define a second annular region separated from the first annular region.

19 . The rotor stage shroud assembly of claim 18 , wherein the shroud segments comprise a ceramic matrix composite material.