Abstract: A process of fabricating at least one channel in a ceramic-containing material comprising providing at least one ceramic-containing material having a first major surface, a second major surface opposite the first major surface, at least one first side surface, and at least one second side surface adjacent the first side surface; removing at least a portion of material from the first major surface or the second major surface of the ceramic-containing material and form one or more structural features; providing at least one metal cover plate; disposing the metal cover plate adjacent the ceramic-containing material and covering the structural features; and, securing together the ceramic-containing material and the metal cover plate.

Abstract: A cover plate retention system for a gaspath component of a turbine engine is disclosed, wherein the gaspath component has a hot side configured for exposure to a hot gaspath of the turbine engine and an opposing non-gaspath side. The cover plate retention system includes a cavity having an opening disposed on the non-gaspath side of the gaspath component, the opening having a pair of parallel side walls, a first end wall, and a second end wall. A top rail is disposed at a top of the first end wall and extends therefrom along a major portion of the top of each of the parallel side walls. A bottom rail is disposed a fixed or specified distance below the top rail on the first end wall and extends therefrom along at least the major portion of each of the parallel side walls to form a three-sided cover plate retention slot.

Abstract: The disclosure describes methods and devices for retaining and sealing cover plates or impingement plates for CMC components. One or more spring members are used to retain the cover plate or impingement plate in position to cover/seal cooling cavities within the interior of CMC components. The spring members include a contact region that contacts the cover plate or impingement plate, and an end section that contacts a restraining member.

Abstract: A process of fabricating at least one channel in a ceramic-containing material comprising providing at least one ceramic-containing material having a first major surface, a second major surface opposite the first major surface, at least one first side surface, and at least one second side surface adjacent the at least one first side surface; removing at least a portion of material from at least one of the first major surface or the second major surface of the at least one ceramic-containing material and form one or more channels comprising at least one heat augmentation feature; providing at least one metal cover plate; disposing the at least one metal cover plate adjacent the at least one ceramic-containing material and covering the one or more channels and the at least one heat augmentation feature; and securing together the at least one ceramic-containing material and the at least one metal cover plate.

Abstract: The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A cover plate is positioned within a cooling cavity in the CMC component wherein the cover plate is angled to vary the depth of the cooling cavity between the cover plate and a bottom wall of the cavity. The angled cooling plate can be used to vary the flux of cooling air within the cooling cavity and thereby achieve a desired cooling performance within the cooling cavity.

Abstract: A CMC component is provided with at least one cooling cavity, defined by side walls and a cavity bottom wall, and a cover plate the covers the at least one cooling cavity opening. The cover plate has one or more cooling air inlets to permit cooling air to flow from a region above the cover plate into the cooling cavity. The cover plate further has one or more walls extending downward from an inner surface of the cover plate to the cavity bottom wall thereby dividing the cooling cavity into a plurality of cooling channels or cooling subcavities, and/or creating a circuitous cooling pathway within the cooling cavity.

Abstract: The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A contoured cover plate is positioned within a cooling cavity in the CMC component, the cooling cavity being defined by side walls and a cavity bottom wall. The cover plate comprises an edge region around the perimeter of the cover plate and a central recessed region which extends into the cooling cavity, the central recessed region is defined by side walls and a bottom wall wherein each side wall of the central recessed region is spaced from a corresponding cavity side wall and the bottom wall of the central recessed region is spaced from the cavity bottom wall. The central recessed region has a plurality of cooling air inlets to permit cooling air to flow from a region above the cover plate into the cooling cavity.

Abstract: The disclosure describes methods and devices for directing cooling air to cool CMC components. A baffle member or splash plate is used to direct the flow of cooling air towards an outer radial surface of a CMC component into a one or more cooling cavities provided within the interior of the CMC component. The splash plate provides an efficient distribution of cooling air into the one or more cooling cavities and aids in the cooling of the component to reduce the formation of thermal stresses induced by the thermal differential between the outer radial surface (cold side) and inner radial surface (hot side) of the component.

Abstract: The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A cover plate is positioned within a cooling cavity in the CMC component wherein the cover plate is angled to vary the depth of the cooling cavity between the cover plate and a bottom wall of the cavity. The angled cooling plate can be used to vary the flux of cooling air within the cooling cavity and thereby achieve a desired cooling performance within the cooling cavity.

Abstract: Attachment pins are used to attach a ceramic matrix composite (CMC) component to a support structure, the attachment pins passing through openings in flange structures extending from a surface of the CMC component. The attachment pins are provided with a cooling air passageway extending in an axial direction, the cooling passageway having an inlet opening in a first end of the attachment pin for introduction of cooling air, and each attachment pin having one or more cooling air outlets extending radially from the cooling air passageway to provide for discharge of cooling air in a desired direction.

Abstract: A cover plate for enclosing a cooling cavity of a ceramic matrix composite (CMC) component of a turbine engine may include a base plate dimensioned to cover an open cooling cavity of the CMC component. The base plate has a first side facing the cooling cavity and at least one feature plate is attached to the first side of the base plate. At least one heat transfer augmentation feature is formed on the at least one feature plate and extends into the cooling cavity, wherein the at least one heat transfer augmentation feature is configured to cause turbulence in a cooling air flow within the cooling cavity. Thus, rather than forming complex heat transfer augmentation features on the cooling cavity of the CMC component itself, such features can be easily provided using metal plate or sheet material or separately-formed CMC elements on the cover plate.

Abstract: A cooling flow arrangement for a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component includes a hot side configured for exposure to a hot gas path of the turbine engine and an opposing cold side. At least one cavity is provided in the CMC component, the at least one cavity having an entrance disposed on the cold side that is configured for receiving a cooling flow. A seal is disposed adjacent the at least one cavity and the cold side of the CMC component and is configured to provide a seal between the CMC component and an upstream turbine component. At least one hole extends through the seal and is positioned to provide the cooling flow to the at least one cavity of the CMC component.

Abstract: An abradable coating/thermal barrier coating suitable for use with jet engine CMC components is described which comprises a material selected from hafnon, mixtures of hafnon and zircon, and rare earth disilicates (RE2Si2O7), wherein RE is Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. The coating has a porosity gradient wherein the porosity decreases in a radial direction. The porosity gradient provides a progressively increasing wear resistance to slow the rate of rub interaction. The porosity gradient also reduces the thermal gradient through the coating thereby reducing the formation of thermal stresses within the coating and any underlying CMC component.

Abstract: The disclosure describes a ceramic matrix composite (CMC) component having a cooling cavity. The CMC component has a base having a bottom inner surface and a top outer surface, in which the base is made from a plurality of ceramic fiber plies within a matrix. A cooling cavity is provided within the base in which the cooling cavity has an opening in the top outer surface of the base. A cover plate made from one or more ceramic fiber plies within a matrix is provided to close the opening of the cooling cavity. The cover plate is bonded to the base by simultaneous densification of the base and cooling cavity.

Abstract: The disclosure describes methods and devices for retaining and sealing cover plates or impingement plates for CMC components. One or more spring members are used to retain the cover plate or impingement plate in position to cover/seal cooling cavities within the interior of CMC components. The spring members include a contact region that contacts the cover plate or impingement plate, and an end section that contacts a restraining member.

Abstract: The incorporation of non-structural ceramic plies to a CMC component or preform is used to provide one or more passages allows for cooling air to pass between segregated cooling cavities. In various embodiments, this may include preforming additional layers of non-structural plies to allow for machining of one or more metered passages, or the incorporation of a pre-formed passage or passages into non-structural ply layups. The one or more passages may be machined and/or preformed and may include cylindrical, racetrack, slot, conical or similar geometries. The one or more passage may be used to pass cooling air between cavities separated by sealing features (W-seal, feather seal, etc.). Bypassing discrete sealing features is beneficial to control and/or meter cooling air flow between high-pressure and lower-pressure cavities.

Abstract: The incorporation of non-structural ceramic plies to a CMC component or preform is used to provide one or more passages allows for cooling air to pass between segregated cooling cavities. In various embodiments, this may include preforming additional layers of non-structural plies to allow for machining of one or more metered passages, or the incorporation of a pre-formed passage or passages into non-structural ply layups. The one or more passages may be machined and/or preformed and may include cylindrical, racetrack, slot, conical or similar geometries. The one or more passage may be used to pass cooling air between cavities separated by sealing features (W-seal, feather seal, etc.). Bypassing discrete sealing features is beneficial to control and/or meter cooling air flow between high-pressure and lower-pressure cavities.

Abstract: The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A cover plate is positioned within a cooling cavity in the CMC component wherein the cover plate is angled to vary the depth of the cooling cavity between the cover plate and a bottom wall of the cavity. The angled cooling plate can be used to vary the flux of cooling air within the cooling cavity and thereby achieve a desired cooling performance within the cooling cavity.

Abstract: An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.

Abstract: An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.