Combustor tile with monolithic inserts

1. A combustor for a gas turbine engine, the combustor comprising:

an annular shroud comprising metal, the annular shroud defining an inward surface and including a first support hole and a second support hole therethough;

a liner the made of ceramic matrix composite material, the liner tile having a first section and a protruding section protruding from the first section, an outer surface of the liner tile spaced from the inward surface along the first section and contacting the inward surface in the protruding section, the liner tile is one of a plurality of liner tiles forming an annular liner to shield hot combustion gases produced in the combustor, the liner tile disposed adjacent the annular shroud;

a first connecting member comprising ceramic material and having a first base element and a first stem, the first base element embedded in, and entirely surrounded by, the ceramic matrix composite material within the protruding section of the liner tile during construction of the liner tile to form an integrated structure with the liner tile and the first connecting member, a distal end of the first stem configured to pass through the first support hole of an annular shroud;

a second connecting member comprising the ceramic material and having a second base element and a second stem, the second base element embedded in, and entirely surrounded by, the ceramic matrix composite material of the liner tile, the first connecting member and the second connecting member, a distal end of the second stem configured to pass through the second support hole of the annular shroud; and

a retaining member configured to mate with the distal end of the first stem to retain the liner tile adjacent the annular shroud,

wherein the first and second support holes are shaped to permit lateral movement of the first and second stems of the first and second stems in use to limit structural stresses caused by thermal expansion of the annular shroud and the liner tile caused by the hot combustion gases, and

wherein in a respective cross-sectional plane the first and second support hole each have a short axis and a long axis, the long axis of the first support hole oriented differently than the long axis of the second support hole to permit movement of the first and second stems radially and axially relative to each other.

2. The combustor of claim 1 , wherein the first connecting member comprises between 50% and 100% by weight of ceramic material.

3. The combustor of claim 2 , wherein the first connecting member comprises between 80% and 100% by weight of ceramic material.

4. An annular assembly for a gas turbine engine, the annular assembly comprising:

a supporting member forming an annular shroud comprising metal, the supporting member defining an inward surface and including a first support hole and a second support hole therethrough;

a liner the made of ceramic matrix composite material, the liner the having a first section and a protuding section protuding from the first section, an outer surface of the liner tile spaced from the inward surface along the first section and contacting the inward surface in the protruding section, the liner tile is one of a plurality of liner tiles forming an annular liner to shield hot combustion gases produced by the gas turbine engine, the liner the disposed adjacent the supporting member;

a first connecting member comprising ceramic material and having a first base element and a first stem, the first base element embedded in, and entirely surrounded by, the ceramic matrix composite material within the protruding section of the liner the during construction of the liner file to form an integrated structure with the liner the and the first connecting member, a distal end of the first stern configured to pass through the first support hole of the supporting member;

a second connecting member comprising the ceramic material and having a second base element and a second stem, the second base element embedded in, and entirely surrounded by, the ceramic matrix composite material of the liner the during construction of the liner tile to form the integrated structure with the liner tile, the first connecting member and the second connecting member, a distal end of the second stem configured to pass through the second support hole of the annular shroud; and

a retaining member configured to mate with the distal end of the first stem to retain the liner the adjacent the supporting member,

wherein the first and second support holes are shaped to permit lateral movement of the first and second stems to limit structural stresses caused by thermal expansion of the supporting member and the liner the caused by the hot combustion gases, and

wherein in a respective cross-sectional plane the first and second support holes each have a short axis and a long axis, the long axis of the first support hole oriented differently than the long axis of the second support hole to permit movement of the first and second stems radially and axially relative to each other.

5. The annular assembly of claim 4 , wherein the annular liner is positioned in one of a combustion chamber, a turbine assembly, and an exhaust assembly, of the gas turbine engine.

6. An annular assembly as in claim 4 , wherein the first connecting member is sized and configured to maintain the outer surface of the liner tile spaced from the inward surface along the first section at a distance.

7. An annular assembly as in claim 6 , wherein a thickness of the first base element of the first connecting member is structured to control the distance.

8. An annular assembly as in claim 6 , wherein a thickness of the first base element of the first connecting member is structured to control the distance, wherein the thickness is variable.

9. An annular assembly as in claim 4 , wherein the long axis of the first support hole is oriented along a circumference of the annular shroud.

10. An annular assembly as in claim 4 , wherein the liner tile comprises a blade track segment, and the supporting member is connected to an annular blade track carrier of the gas turbine engine.

11. A method of making an annular assembly for a gas turbine engine, the method comprising:

laying a first layer of fibers in a tool;

positioning a first base element of a first connecting member on the first layer of fibers, the first connecting member comprising ceramic material and including a first stem connected to and extending from the first base element;

positioning a second base element of a second connecting member on the first layer of fibers, the second connecting member comprising the ceramic material and including a second stem connected to and extending from the second base element;

laying a second layer of fibers over the first layer, the first base element, and the second base element, the second layer of fibers entirely surrounding the first base element and the second base element;

infiltrating the first layer of fibers and the second layer of fibers with a ceramic matrix to form a ceramic matrix composite material;

densifying the ceramic matrix composite material to form an integrated structure comprising a liner tile integrated with the first base element of the first connecting member and the second base element of the second connecting member, the liner tile having a first section and a protruding section protruding from the first section, the first base element embedded in, and entirely surrounded by, the ceramic matrix composite material within the protruding section of the liner tile;

inserting a distal end of the first stem through a first support hole of a supporting member comprising metal, the supporting member forming an annular shroud and defining an inward surface and;

securing a retaining member on the distal end of the stem to retain the integrated structure adjacent the supporting member, an outer surface of the liner tile being spaced from the inward surface along the first section and contacting the inward surface in the protruding section; and

forming an annular liner with a plurality of liner tiles for hot combustion gases produced by the gas turbine engine, the liner tile being one of the plurality of liner tiles

wherein the first and second support holes are shaped to permit lateral movement of the first and second stems to limit structural stresses caused by thermal expansion of the annular liner during operation of the gas turbine engine, and

wherein in a respective cross-sectional plane the first and second support holes have a short axis and a long axis, the long axis of the first support hole oriented differently than the long axis of the second support hole to permit movement of the first and second stems radially and axially relative to each other.

12. The method of claim 11 , wherein the annular liner is positioned in one of a combustion chamber, a turbine assembly, and an exhaust assembly, of the gas turbine engine.