Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

Abstract: A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing. Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.

Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

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: The system described here includes a unique and versatile evaluation method or process invented by the present author. For the sake of this description we will call any entity capable of performing the process an evaluator. The evaluator is an essential part of the system described here. Sometimes such an evaluator is referred to as a visualizer and the evaluation process is referred to as visualization. This is because the process can be set to enable an evaluator to use available data to synthesize evaluative conclusions that appear to consider a subject, including information about both the subject itself as well as other aspects of this subject's environment to alert evaluator and subject of that which warrants attention.

Abstract: A method of forming a passage in a turbine component includes: using an additive manufacturing process to form a first support structure on a first surface of the turbine component; forming a second support structure on a second surface of the turbine component, the second support structure being spaced apart from the first support structure; and forming a passage in the turbine component between the first and second support structures.

Abstract: An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Abstract: An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a porous section having a porosity permitting a volume of fluid, such as air, to pass through the porous section.

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: Account data (e.g., balance information) for accounts at a plurality of financial institutions (or government agencies) is stored (and updated) in a central database system and accessed using a personal identifier, such as a social security number. Risk data may be generated for accounts based on the account data. The account data and risk data are accessed in response to either an account search request (e.g., from a government entity and relating to a benefits program or a subpoena) or an account verification request (e.g. from a mortgage company and relating to a mortgage application).

Abstract: An apparatus and method for cooling an engine component includes a wall. The wall can include multiple layers. The layers can be different materials and define an interior for the engine component. The layers can include shaped features to define a serial cooling air flow path for providing a flow from the interior to an exterior of the engine.

Abstract: A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.

Abstract: A system for analyzing a fluid includes an integrated fluid-electric cabinet having a fluid compartment and an electronic compartment. The fluid compartment and an electronic compartment are separated from one another by a partition wall. The partition wall includes opposed first and second surfaces. A flow cell assembly is disposed in the fluid compartment and is configured to be mounted on the first surface side of the partition wall. A probe head assembly is disposed in the electronic compartment and is mounted on the opposed second surface side of the partitioned wall. Both of the flow cell assembly and the probe head assembly are configured to be in electro-magnetic communication with one another for elemental analysis of the fluid such that the probe head assembly utilizes an X-ray source to analyze the fluid in a static mode or in flow mode through the flow cell assembly.

Abstract: Uniform subject and object oriented data structure adopted in computing device to efficiently store, distribute and process data in a variety of applications. Said data structure comprised of multiple complementary subparts that together and independently facilitate communication (of inputs and outputs) through one or more defined interfaces to facilitate secure access and coordination between given individual subject(s) and other real (physical or metaphysical) entities. Methods are also disclosed that work in tandem with the data structure and interface components to enable and require a single or given human user or other individual personal subject (belonging to a secure AFFIRM network) to maintain exclusive (private) self-control over at least one virtual domain that represents themselves (their actions and their relationships).

Abstract: A stand-alone ice making appliance is provided. The stand-alone ice making appliance may include an outer casing, a water tank, a pump, an ice maker, and a container. The outer casing may define an internal cavity that includes a primary opening. The water tank may define a storage volume to receive water. The pump may be in fluid communication with the storage volume of the water tank to actively flow water therefrom. The ice maker may in fluid communication with the storage volume of the water tank to receive water therefrom. The container may be disposed within the internal cavity. The container may include an insulated sidewall positioned across the primary opening and at least partially defining a storage volume to receive ice from the ice maker.

Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.

Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.

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.