Abstract: A sensor unit including a housing having cooling fins, and a cooling attachment which is mounted on the cooling fins and has a fluid inlet and a fluid outlet, so that a fluid is able to flow along the cooling fins, the placement of the cooling fins and the cooling attachment between the fluid inlet and the fluid outlet allowing a predefined temperature gradient to be adjusted on the housing.

Abstract: A fuel injector device includes a body having a leading edge and a trailing edge and defining a streamwise direction from the leading edge to the trailing edge. The fuel injector device body includes a first surface and a second surface opposite the first surface, each surface extending between and including the leading edge and the trailing edge, and the surfaces conjoining each other at the leading edge and the trailing edge. The trailing edge, when seen in the streamwise direction, undulates along a trailing edge mean line and, along its extent, deviates in opposite directions from the mean line and includes at least one inflection point along its extent.

Abstract: The invention refers to a transition piece of a combustor of a gas turbine including an impingement cooling zone, a sequential disposed liner having at least one cooling arrangement and a closing plate with respect to the sequential disposed liner. The sequential disposed liner has a cooling channel structure. The cooling channel structure forms a closed loop cooling scheme or a quasi-closed loop cooling scheme. The cooling channel structure is operatively connected to a cooling medium to cool at least one part of the sequential disposed liner.

Abstract: Various methods and systems for designing a restored smile are provided. One method includes receiving scan data of a patient's teeth, developing a digital model of the patient's teeth via a computing device, where the model represents the patient's teeth based upon the scan data, creating a dental treatment plan to restore one or more teeth from an initial condition to a successive condition, and wherein a final condition of the one or more is based on the one or more teeth having at least one planned additional restorative tooth structure provided therewith.

Abstract: Various methods and systems for designing a restored smile are provided. One method includes receiving scan data of a patient's teeth, developing a digital model of the patient's teeth via a computing device, where the model represents the patient's teeth based upon the scan data, creating a dental treatment plan to restore one or more teeth from an initial condition to a successive condition, and wherein a final condition of the one or more is based on the one or more teeth having at least one planned additional restorative tooth structure provided therewith.

Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

Abstract: An impingement cooled wall arrangement includes a flow diverter arranged in the cooling flow path between the cooled wall and a sleeve to divert a cross flow away from a second aperture. The flow diverter extends in downstream direction of the cross flow beyond the second aperture with a first leg extending along one side of the second aperture in downstream direction of the cross flow and a second leg extending along the other side of the second aperture. No impingement cooling aperture is arranged in a first convective cooling section of the wall between the upstream end and downstream end of the flow diverter outside the section shielded by the diverter.

Abstract: A component is disclosed, the component comprising a first material and a second material, wherein a second member made from the second material is embraced by a first member made from the first material. Further, a method is disclosed for manufacturing said component, the method comprising applying an additive manufacturing process, building up a first member from a first material by the additive manufacturing process, and adding a second member made from a second material during the additive manufacturing process and adding further first material to the first member thus embracing the second member.

Abstract: The present disclosure refers to an impingement cooling arrangement for cooling a duct wall of a duct guiding a hot gas flow. The impingement cooling arrangement includes an impingement sleeve which is at least partly disposed in a compressed air plenum, and spaced at a distance to the duct wall to form a cooling flow path between the duct wall and the impingement sleeve such that cooling air injected from the compressed air plenum through apertures in the sleeve impinges on the duct wall. At least one flow diverter is arranged in the cooling flow path to divert the cross flow away from at least one aperture. Besides the impingement cooling arrangement a gas turbine with such an arrangement as well as a method for cooling a duct wall are provided.

Abstract: A gas turbine combustor part of a gas turbine includes a wall, containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction. The near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air. The inlets open into a common feeding channel for cooling air supply, and the outlets open into a common discharge channel for cooling air discharge. The feeding channel and the discharge channel extend in the second direction.

Abstract: A method for providing swerve assistance for a motor vehicle, in which a threatening or imminent collision of the motor vehicle is detected, the driver is notified to steer the vehicle onto a collision-avoiding swerve trajectory, it is detected whether the driver heeds the warning and initiates a swerve maneuver, and if the driver initiates a swerve maneuver, a driver-independent implementation of a steering or braking intervention assisting in the steering onto the swerve trajectory takes place.