Patent ID: 11879362
Assignee: ROLLS-ROYCE CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A turbine section for use with a gas turbine engine, the turbine section comprising:
a case that extends circumferentially at least partway around an axis of the gas turbine engine,
a plurality of flow path components arranged to define a primary gas path of the turbine section, the plurality of flow path components including a turbine vane, a turbine blade located axially aft of the turbine vane and configured to rotate about the axis of the gas turbine engine, and a flow path segment made of ceramic matrix composite materials and formed to include a segment wall that extends axially between a forward end located axially forward of the turbine vane and an aft end spaced apart axially from the forward end and located axially aft of the turbine blade to define a portion of the primary gas path, a blade track attachment that extends radially outward away from the segment wall and toward the case near the aft end of the segment wall, and a forward attachment spaced apart from the blade track attachment and located axially forward of the blade track attachment near the forward end, and the turbine vane extending radially inward from the flow path segment axially between the blade track attachment and the forward attachment of the flow path segment, and
a mounting system made of metallic materials and configured to couple the flow path segment to the case to support the flow path segment radially relative to the axis of the gas turbine engine, the mounting system including a blade track mount that engages the blade track attachment of the flow path segment, a forward mount that engages the forward attachment of the flow path segment, and a vane mount that engages the turbine vane axially between the blade track mount and the forward mount,
wherein the forward mount is located radially outward of the primary gas path so that the forward mount is shielded from hot combustion products flowing through the primary gas path during use of the turbine section in the gas turbine engine,
wherein the forward attachment and the forward mount are free for axial movement relative to each other to accommodate different rates of thermal expansion experienced by the ceramic matrix composite materials of the flow path segment and the metallic materials of the mounting system, and
wherein the flow path segment and the turbine vane are free for radial movement relative to each other to accommodate different rates of thermal expansion experienced by the ceramic matrix composite materials of the flow path segment and the metallic materials of the mounting system.