Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.

Abstract: An engine component for a gas turbine engine which generates a hot combustion gas flow adjacent a hot surface and provides a cooling fluid flow adjacent a cooling surface comprises a wall separating the hot combustion gas flow and the cooling fluid flow. At least one concavity is provided in the cooling surface and at least one film hole is provided in the cooling surface providing the cooling fluid flow to the hot surface. An inlet for the film hole is spaced from the at least one concavity, located upstream of the at least one concavity and in alignment with the at least one concavity relative to the cooling fluid flow.

Abstract: An engine component for a gas turbine engine can generate a hot combustion gas flow and provide a cooling fluid flow. A wall can separate the hot combustion gas flow from the cooling fluid flow. Multiple film holes can be disposed in the wall, having an inlet adjacent the cooling fluid flow and an outlet at the hot combustion gas flow such that the cooling fluid flow can be provided to the hot combustion gas flow. The film holes further comprise inlets, such that the inlets can be arranged with the inlets having at least one of a different orientation relative to one another or are non-aligned with each other relative to the cooling fluid flow.

Abstract: A method of forming a passage in a turbine component that includes using an additive manufacturing process to form a first support structure on a first surface of the turbine component; and forming a passage through the first support structure and the turbine component.

Abstract: A method of forming an overhanging structure at a discharge end of a cooling hole that passes through a component. The method includes the step of using an additive manufacturing process to fuse material to a face to build up an edge of the discharge end of the cooling hole to form an overhanging tab.

Abstract: A method of forming a structure in a turbine component having a seal slot, the slot including walls defining an opening therebetween, the method includes the step of using an additive manufacturing process to form a neck structure on a wall so as to reduce a size of the opening.

Abstract: A method of forming a cooling hole structure on a turbine component. The turbine component has a component wall with inner and outer surfaces. A bore passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of: A) forming a recess communicating with the bore and the outer surface; and B) using an additive manufacturing process to form an exit region in the recess.

Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

Abstract: A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.

Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.

Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The hot combustion gas flow defines an upstream direction and a downstream direction relative to the hot surface. The substrate also defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage comprises a metering section; and a diffusing section, with the diffusing section including a shelf, a first outer lobe and a second outer lobe.

Abstract: A component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one hollow, interior space. The outer surface of the substrate defines a pressure side wall and a suction side wall. The pressure and suction side walls are joined together at a leading edge and at a trailing edge of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge of the component. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer surface of the substrate. The coating comprises at least a structural coating, where the structural coating extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge of the component.

Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

Abstract: A component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one hollow, interior space. The outer surface of the substrate defines a pressure side wall and a suction side wall. The pressure and suction side walls are joined together at a leading edge and at a trailing edge of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge of the component. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer surface of the substrate. The coating comprises at least a structural coating, where the structural coating extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge of the component.

Abstract: A manufacturing method includes providing a substrate with an outer surface and at least one interior space, selectively deposited a coating on a portion of the substrate to form a selectively deposited coating having one or more grooves formed therein. The method further includes processing at least a portion of the surface of the selectively deposited coating to plastically deform the selectively deposited coating in the vicinity of the top of a respective groove. An additional coating is applied over at least a portion of the surface of the selectively deposited coating. A component is disclosed and includes a substrate, a selectively deposited coating disposed on at least a portion of the substrate, and defining one or more grooves therein, and an additional coating disposed over the selectively deposited coating. The substrate, the selectively deposited coating and the additional coating defining one or more channels for cooling the component.

Abstract: A temperature measurement system includes a plurality of filaments. The plurality of filaments are configured to emit thermal radiation in a relatively broad and substantially continuous wavelength band at least partially representative of a temperature of the plurality of filaments. A first and second portion of the filaments has a differing first and a second diameter and/or emissivity, respectively. The system also includes a detector array configured to generate electrical signals at least partially representative of the thermal radiation received from the filaments. The system further includes a controller communicatively coupled to the detector array configured to transform the first electrical signals to a first temperature indication at least partially as a function of the first diameter and/or first emissivity and transform the second electrical signals to a second temperature indication at least partially as a function of the second diameter and/or emissivity.

Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.