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

Claim 10:
11. 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 flow path segment made of ceramic matrix composite materials and arranged to define a primary gas path of the turbine section, the flow path segment including a segment wall that extends axially between a forward end and an aft end spaced apart from the forward end to define a portion of the primary gas path, a first attachment that extends radially outward away from the segment wall and toward the case, and a second attachment located axially forward of the first attachment, 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, the mounting system including a first mount configured to engage the first attachment of the flow path segment and a second mount located axially forward of the first attachment and configured to engage the second attachment of the flow path segment,
wherein the second mount is located radially outward of the primary gas path so that the second mount is shielded from hot combustion products flowing through the primary gas path during use of the turbine section in the gas turbine engine and the second attachment and the second 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,
wherein the turbine section further comprises a turbine vane that extends radially inward from the flow path segment axially between the first and second attachments of the flow path segment, and wherein the mounting system further includes a third mount located axially between the first and second mounts of the mounting system and configured to engage the turbine vane, 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.