Abstract: Methods, systems, and devices for solid axle testing are provided.

Abstract: The disclosure relates generally to recession resistant gas turbine engine articles that comprise a silicon containing substrate, and related coatings and methods. The present disclosure is directed, inter alia, to an engine article comprising a silicon substrate which is coated with a chemically stable porous oxide layer. The present disclosure also relates to articles comprising a substrate and a bond coat on top comprising a two phase layer of interconnected silicon and interconnected oxide, followed by a layer of silicon. The present disclosure further relates to a recession resistant article comprising an oxide in a silicon containing substrate, such that components of the silicon containing substrate is interconnected with oxides dispersed in the substrate and form the bulk of the recession resistant silicon containing article.

Abstract: Ta containing alpha/near alpha Ti alloys are disclosed. The alloys include Ta. The alloys retain higher percentage amounts of room temperature dynamic modulus at elevated temperatures.

Abstract: The disclosure relates generally to recession resistant gas turbine engine articles that comprise a silicon containing substrate, and related coatings and methods. The present disclosure is directed, inter alia, to an engine article comprising a silicon substrate which is coated with a chemically stable porous oxide layer. The present disclosure also relates to articles comprising a substrate and a bond coat on top comprising a two phase layer of interconnected silicon and interconnected oxide, followed by a layer of silicon. The present disclosure further relates to a recession resistant article comprising an oxide in a silicon containing substrate, such that components of the silicon containing substrate is interconnected with oxides dispersed in the substrate and form the bulk of the recession resistant silicon containing article.

Abstract: A coating system and a method of forming the coating system capable of enabling components to survive in high temperatures environments, such as the hostile thermal environment of a gas turbine. The coating system is formed of a ceramic powder having powder particles each having an inner core formed of a first material and an outer region formed of a second material on the surface of the inner core. The inner core has a lower thermal conductivity than the outer region and the outer region has improved erosion resistance relative to the inner core.

Abstract: Processes and systems for forming a coating system on a component. The process of forming the coating system on the component includes placing an apparatus in a location that promotes coating particles in flight to be redirected towards a surface on the component. The surface is obstructed by portions of the component limiting line-of-sight from a source of the coating particles to the surface. The coating particles are then deposited onto the surface of the component. The coating particles initially travel in a direction of initial particle travel and are redirected by the apparatus towards the surface on the component at a direction of final particle travel relative to the surface. The line-of-site from the source of the coating particles is at an angle of less than 30 degrees relative to the surface of the component and the direction of final particle travel is at an angle of 30 degrees or more relative to the surface of the component.

Abstract: A method of forming cooling channels in a component is provided. The component has a substrate having outer and inner surfaces. The inner surface defines at least one interior space, and a core is disposed within each interior space. The method includes forming at least one access hole in the substrate, while the core is disposed within the respective interior space, removing the core from the respective interior space, and forming at least one groove in the outer substrate surface (before or after the core is removed). Each access hole connects the groove in fluid communication with the respective interior space. The method further includes disposing a coating over at least a portion of the outer substrate surface, where the coating includes at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels configured to convey a coolant from the respective interior space(s) for cooling 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 portable imaging system is presented. The system includes at least a display panel. Further, the system includes a control panel, where the display panel and the control panel include a seamless form factor of a single unit box, and where the seamless form factor is configured to aid in cleaning the system.

Abstract: A layered arrangement, a hot-gas path component, and a process of producing a layered arrangement are disclosed. The layered arrangement includes a substrate layer, a ceramic matrix composite layer, and a non-metal spacer between the substrate layer and the ceramic matrix composite layer configured to define one or more pockets. The hot-gas-path component includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer. The ceramic spacer is mechanically secured to one or both of the substrate layer and the ceramic matrix composite layer, and the ceramic spacer is bonded to the substrate layer or the ceramic matrix composite layer. The process includes securing a non-metal spacer between a substrate layer and a ceramic matrix composite layer of the layered arrangement.

Abstract: Active clearance control ejector systems and methods are disclosed. An example system may include an air ejector; an entrance pipe arranged to supply compressor bleed air to the air ejector; an inlet duct arranged to supply fan bypass air to the air ejector; and a supply pipe arranged to receive ejector outlet air from the air ejector and supply the ejector outlet air to an active clearance control system. The ejector outlet air may include a mixture of the compressor bleed air and the fan bypass air. The air ejector may include a venturi arranged to conduct the compressor bleed air therethrough, thereby drawing the fan bypass air into the air ejector.

Abstract: A thermal barrier coating system for metal components in a gas turbine engine having an ultra low thermal conductivity and high erosion resistance, comprising an oxidation-resistant bond coat formed from an aluminum rich material such as MCrAlY and a thermal insulating ceramic layer over the bond coat comprising a zirconium or hafnium oxide lattice structure (ZrO2 or HfO2) and an oxide stabilizer compound comprising one or more of the compounds ytterbium oxide (Yb2O3), yttria oxide (Y2O3), hafnium oxide (HfO2), lanthanum Oxide (La2O3), tantalum oxide (Ta2O5) or zirconium oxide (ZrO2). The invention includes a new method of forming the ceramic-based thermal barrier coatings using a liquid-based suspension containing microparticles comprised of at least one of the above compounds ranging in size between about 0.1 and 5 microns. The coatings form a tortuous path of ceramic interfaces that increase the coating toughness while preserving the ultra low thermal conductivity.

Abstract: Methods of casting a component including one or more surface cooling channels. The method including casting a ceramic core into a flexible mold of a core section and casting a ceramic shell in at least two sections into respective flexible molds of a first shell section and a second shell section. A ceramic casting vessel is subsequently formed by assembling the ceramic core within the ceramic shell sections. A metal substrate material is cast into the ceramic casting vessel. Removal of the ceramic casting vessel reveals a substrate of the component having defined therein the interior passageway, the one or more cooling passages in fluidic communication with the interior passageway and one or more surface grooves in fluidic communication with the one or more cooling passages.

Abstract: Embodiments of the present disclosure are directed toward systems including a tip shroud insert having a retained portion configured to be retained within a pocket of a turbomachine blade and an exposed portion configured to form a dynamic seal with a stationary structural component surrounding the turbomachine blade.

Abstract: A system and methods for applying a ceramic coating to a component that includes first applying a coating material to a first portion of a component. A removal agent is then applied to a second portion of the component that has an overspray byproduct thereon, and then the ceramic coating material is applied to at least the second portion of the component.

Abstract: A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.

Abstract: A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.

Abstract: Dampers for fan spinners of aircraft engines are disclosed. An example fan module for a gas turbine engine may include a fan disk; fan blades mounted to the fan disk and extending radially therefrom; a fan spinner operatively coupled to the fan disk at an axially upstream position; and/or one or more elastic vibration dampers operatively interposing the fan spinner and the fan disk. The elastic vibration dampers may be disposed circumferentially around an interface between the fan spinner and the fan disk and may be compressed axially and/or radially.

Abstract: A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine.

Abstract: A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.