A sports simulation system includes a projectile tracking apparatus having a display surface on which a visually apparent three-dimensional sports scene is presented The projectile tracking apparatus captures images of a projectile tracking region disposed in front of the display surface to detect a launched projectile traveling through the projectile tracking region towards the display surface A projectile launch area sensing unit captures images of the projectile launch area At least one processing stage communicates with the projectile tracking apparatus and the projectile launch area sensing unit and is responsive to the data received therefrom to determine the three-dimensional positions, velocity, acceleration and spin of a detected projectile traveling through the projectile tracking region The determined three-dimensional positions, velocity, acceleration and spin are used by the at least one processing stage to calculate a trajectory of the launched projectile into the visually apparent three-dimensional sports scene Updated image data is generated by the at least one processing stage that includes a simulation of the launched projectile into the visually apparent three-dimensional sports scene following the calculated trajectory A projection unit coupled to the at least one processing stage receives the image data from the at least one processing stage and presents the visually apparent three-dimensional sports scene, including the simulation, on the display surface

Sports simulation system

Apparatus and methods are provided for converting methane in a feed stream to acetylene. A hydrocarbon stream is introduced into a supersonic reactor and pyrolyzed to convert at least a portion of the methane to acetylene. The reactor effluent stream may be treated to convert acetylene to another hydrocarbon process.

Methane conversion apparatus and process using a supersonic flow reactor

Disclosed is a method for manufacturing an article (1), particularly a prototype of a product or component, a tool prototype or spare part, by using selected laser melting. Specifically, for the application onto the article (1) of a layer (13) or portion of a second metallic material, which is different from the material of the first metallic powder (4), a tape (12), sheet (14), foil or three-dimensional pre-form (18) of a second material is applied to the article (1) and is heated by means of a focused laser or electron beam (6) to a specified temperature such that the tape (12), sheet (14), foil or pre-form, respectively, are molten by the or electron laser beam (6), wherein the focused beam (6) is applied to a given area corresponding to a selected cross-sectional area of the model of the article (1) under formation of a new layer or part made of second material integral with the article (1).

Method to apply multiple materials with selective laser melting on a 3d article

An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate directly with at least one cooling fluid supply contained within a turbine engine component, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate is covered with an actively cooled bond coat layer, it will reduce the cooling requirement for the substrate, thus allowing the engine to run at higher operating temperature without the need for additional cooling air, achieving a better engine performance. In one form, the component includes a substrate having at least one substrate channel with a first and second end. At least one micro channel is in fluid communication with a plenum which in turn is in fluid communication with at least one substrate channel through an exit orifice in the substrate channel which is at a first end of the substrate channel. A second end of the substrate channel is in communication with a cooling fluid supply, for example, cooling circuits contained within the turbine engine component. The micro channel is located between the substrate surface and the outer gas flow path surface of the component.

Directly cooled thermal barrier coating system

A component is provided and includes a substrate comprising an outer and an inner surface, where the inner surface defines at least one hollow, interior space. The component defines one or more grooves, where each groove extends at least partially along the outer surface of the substrate and has a base and a top. The base is wider than the top, such that each groove comprises a re-entrant shaped groove. One or more access holes are formed through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. Each access hole has an exit diameter D that exceeds the opening width d of the top of the respective groove. The diameter D is an effective diameter based on the area enclosed. The component further includes at least one coating disposed over at least a portion of the surface of the substrate, wherein the groove(s) and the coating together define one or more re-entrant shaped channels for cooling the component. A method for manufacturing the component is also provided. A method for manufacturing a component is also provided, where the groove and the access hole(s) are machined as a single continuous process, such that the groove and the access hole(s) form a continuous cooling passage.

Components with cooling channels and methods of manufacture

A method of forming an internal channel within an article, such as a cooling channel in an air-cooled blade, vane, shroud, combustor or duct of a gas turbine engine. The method generally entails forming a substrate to have a groove recessed in its surface. A solid member is then placed in the groove, with the solid member being sized and configured to only partially fill the groove so that a void remains in the groove. The void is then filled with a particulate material so that the groove is completely filled. A layer is then deposited on the surface of the substrate and over the solid member and the particulate material in the groove, after which at least the solid member is removed from the groove to form the channel in the substrate beneath the layer.

Method of forming hollow channels within a component

Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least one insert onto the airfoil such that the at least one deficit of material is substantially eliminated.

Airfoils with improved strength and manufacture and repair thereof

A method of repairing cracks, imperfections, and the like in a cast article. A frusto-conical aperture is created in the article in the location of the crack or imperfection. A mating tapered plug is prepared such that the tapered plug can fit into the aperture so that the sloped side walls of the tapered plug evenly and unilaterally rest on frusto-conical sides of the aperture. The tapered plug is disposed into the aperture, and bonding material is applied between the surfaces of the tapered plug and the aperture, before or after insertion of the tapered plug into the aperture. The article is thereafter heated such that the bonding material joins the surfaces of the tapered plug and the aperture. The outer end of the tapered plug thereafter is polished so that such outer end is approximately level with the article's outer side in a refinement of the invention, the plug member may be pushed into the aperture such that a controlled interference fit is produced.

Method for repairing superralloy castings using a metallurgically bonded tapered plug

A method for forming an exterior surface of a high-temperature component, such as a blade or vane of a gas turbine engine. The method entails forming a shell by a powder metallurgy technique that yields an airfoil whose composition can be readily tailored for the particular service conditions of the component. The method generally entails providing a pair of inner and outer mold members that form a cavity therebetween. One or more powders and any desired reinforcement material are then placed in the cavity and then consolidated at an elevated temperature and pressure in a non-oxidizing atmosphere. Thereafter, at least the outer mold member is removed to expose the consolidated powder structure. By appropriately shaping the mold members to tailor the shape of the cavity, the consolidated powder structure has the desired shape for the exterior shell of a component, such that subsequent processing of the component does not require substantially altering the configuration of the exterior shell. The airfoil can be produced as a free-standing article or produced directly on a mandrel that subsequently forms the interior structure of the component. In one embodiment, an airfoil is configured to have double walls through which cooling air flows.

Method of forming high-temperature components and components formed thereby

A melt guide is provided for enclosing a bottom of an electroslag refining crucible containing a melt of electroslag refined metal. A base plate is sized to have a perimeter to engage the crucible bottom for attachment thereto. The base plate includes an upper surface for defining with the crucible a reservoir for receiving the melt, and a lower surface spaced therebelow. A central drain extends through the base plate for draining by gravity the melt from the reservoir. A plurality of circumferentially spaced apart slots extend radially outwardly from the drain toward the base plate perimeter and extend vertically through the base plate. Induction heating coils are mounted below the base plate lower surface for heating the melt through the slots. The base plate may take various forms including a flat plate, with or without a cooperating and removable insert.

Paul Leonard Dupree

Papers

Method of forming hollow channels within a component

Airfoils with improved strength and manufacture and repair thereof

Method for repairing superralloy castings using a metallurgically bonded tapered plug

Method of forming high-temperature components and components formed thereby

Electroslag apparatus and guide