Abstract: Component retention assemblies and flowpath assemblies are provided. An exemplary retention assembly comprises a flange attached to a support structure, a retention ring received in a flange groove, and an attachment bracket comprising a component of a gas turbine engine. A first segment of the attachment bracket is axially disposed between the flange and a support structure first portion, and a second segment of the attachment bracket is radially disposed between the flange and a support structure second portion. The flange axially loads and the retention ring radially loads the attachment bracket into the support structure. An exemplary flowpath assembly comprises a retention assembly including a flange attached to a casing, a retention ring, and a CMC attachment bracket comprising a plurality of CMC components. The flange axially loads the attachment bracket into an axial stop, and the retention ring radially loads the attachment bracket into the casing.

Abstract: Retention assemblies and retention assembly cooling methods are provided. An exemplary retention assembly comprises an annular baffle, an annular attachment bracket comprising a gas turbine engine component, and first and second cooling passages defined by the baffle and attachment bracket. The first cooling passage is configured to receive a first airflow and the second cooling passage is configured to receive a second airflow. The first airflow has a lower pressure than the second airflow. An exemplary method comprises flowing a first airflow to a first cooling passage defined by a baffle and an attachment bracket of a retention assembly, and flowing a second airflow to a second cooling passage defined by the baffle and the attachment bracket. The second cooling passage is separate from the first cooling passage. The first airflow cools radially outward structures of the retention assembly, and the attachment bracket comprises a CMC component.

Abstract: Component retention assemblies and flowpath assemblies are provided. An exemplary retention assembly comprises a flange attached to a support structure, a retention ring received in a flange groove, and an attachment bracket comprising a component of a gas turbine engine. A first segment of the attachment bracket is axially disposed between the flange and a support structure first portion, and a second segment of the attachment bracket is radially disposed between the flange and a support structure second portion. The flange axially loads and the retention ring radially loads the attachment bracket into the support structure. An exemplary flowpath assembly comprises a retention assembly including a flange attached to a casing, a retention ring, and a CMC attachment bracket comprising a plurality of CMC components. The flange axially loads the attachment bracket into an axial stop, and the retention ring radially loads the attachment bracket into the casing.

Abstract: Combustor assemblies are provided. An exemplary combustor assembly comprises an annular ceramic matrix composite (CMC) inner liner including an inner liner flange, an annular CMC outer liner including an outer liner flange, and an annular CMC combustor dome comprising a plurality of tiles positioned circumferentially adjacent one another. Each tile has a first end radially opposite a second end. The CMC inner liner, outer liner, and combustor dome form a combustor, and the CMC combustor dome is positioned at a combustor forward end. The combustor assembly also comprises a support structure for supporting the combustor and including an annular frame having a frame channel defining a groove and an inner and outer support flanges. The first end of each tile is disposed within the frame channel groove. The inner liner flange is secured to the inner support flange and the outer liner flange is secured to the outer support flange.

Abstract: Combustor assemblies and methods for assembling combustor assemblies are provided. For example, a combustor assembly comprises an annular inner liner and an annular outer linear, each extending generally along an axial direction. The outer liner includes an outer flange extending forward from its upstream end. The combustor assembly also comprises a combustor dome extending between an inner liner upstream end and the outer liner upstream end and including an inner flange extending forward from a radially outermost end of the combustor dome. The inner liner, outer liner, and combustor dome define a combustion chamber therebetween, and the combustor dome and a portion of the outer liner together define an annular cavity of the combustion chamber. The inner and outer flanges define an airflow opening therebetween, and a chute member is positioned within the airflow opening to define an air chute for providing a flow of air to the annular cavity.

Abstract: Methods for adhering a substrate onto a surface of a ceramic component are provided. The method may include applying a first bond coating onto an attachment surface of the substrate, applying a first alumina coating onto the first bond coating on the attachment surface of the substrate, applying a second bond coating onto an outer surface of the ceramic component, applying a second alumina coating onto the second bond coating on the attachment surface of the substrate, applying a cement onto at least one of the first alumina coating and the second alumina coating, and adhering the attachment surface of the substrate onto the outer surface of the ceramic component. Connections between a metal substrate and a ceramic matrix composite component are also provided.

Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.

Abstract: Methods for assembling flow path structures having one or more unitary components are provided. For example, one method for assembling a flow path assembly of a gas turbine engine comprises stacking axially adjacent components within a generally annular outer wall of the flow path assembly. The flow path assembly defines a flow path through a combustion section and at least a portion of a turbine section of the gas turbine engine. The outer wall defines an outer boundary of the flow path, and the axially adjacent components defining at least a portion of an inner boundary of the flow path. The outer wall is a unitary outer wall that includes a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of the turbine section. The combustor and turbine portions are integrally formed as a single unitary structure.

Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.

Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Abstract: A shroud retention system may include a shroud hanger having an outer hanger wall that defines a clip groove including a narrow groove portion and an enlarged groove portion, with the enlarged groove portion defining a radial height that is greater than a radial height of the narrow groove portion. The system may also include a shroud segment having a shroud wall and a retention clip configured to couple the shroud segment to the shroud hanger. The retention clip may include an inner rail, an outer rail and a clip wall extending radially between the inner and outer rails. The inner rail may be configured to extend along an inner surface of the shroud wall. The outer rail may include a narrow rail portion configured to be received within the narrow groove portion and an enlarged rail portion configured to be received within the enlarged groove portion.

Abstract: A shroud retention system may include a shroud hanger having an outer hanger wall that defines a clip groove including a narrow groove portion and an enlarged groove portion, with the enlarged groove portion defining a radial height that is greater than a radial height of the narrow groove portion. The system may also include a shroud segment having a shroud wall and a retention clip configured to couple the shroud segment to the shroud hanger. The retention clip may include an inner rail, an outer rail and a clip wall extending radially between the inner and outer rails. The inner rail may be configured to extend along an inner surface of the shroud wall. The outer rail may include a narrow rail portion configured to be received within the narrow groove portion and an enlarged rail portion configured to be received within the enlarged groove portion.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface.

Abstract: A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.

Abstract: A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface.

Abstract: A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.

Abstract: A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.