Abstract: An apparatus and method for displaying digital content onto a vehicle, the apparatus including a foam apparatus, a sensor configured to detect vehicle dimension data, at least a processor and a memory communicatively connected to the at least a processor, wherein the memory contains instructions configuring the at least a processor to receive the vehicle dimension data, calculate a concentration requirement based on the vehicle dimension data, transmit the concentration requirement to the foam apparatus, wherein the foam apparatus is configured to disperse foam onto the vehicle based on the concentration requirement, and a display device including a digital content projector, wherein the display device is configured to display a plurality of digital content onto the foam dispersed onto the vehicle.

Abstract: A modular biometric station system is used to form one or more modular biometric stations with cohesive form factors. Such biometric stations include a core unit, one or more end caps, and one or more modules. The modules may be configured to communicably and electrically couple to one or more of the end caps. The end caps may be configured to communicably and electrically couple to the core unit and/or one or more of the modules and may communicably and electrically couple one or more of the modules to the core unit. The core unit, end caps, and/or the modules may be able to communicably interact when coupled together. The core unit, end caps, and modules may all share a form factor. The core unit may include hardware and/or software that satisfies common requirements, and the modules may include peripherals and/or other components that can be coupled to the core unit to adapt the modular biometric station to a variety of different needs of different applications.

Abstract: A turbine engine is provided and includes an aerodynamic element disposed to aerodynamically interact with a flow of working fluid and contour features disposed on the aerodynamic element in alignment in at least one dimension. The contour features are proximate to one another and configured to encourage counter-rotating vortex flow generation oriented substantially perpendicularly with respect to a main flow direction along the aerodynamic element.

Abstract: The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine. For example, in one embodiment, a gas turbine engine may include a combustor having a combustion flow. The gas turbine engine also may include one or more airfoils forming a first stage nozzle or s transition nozzle disposed downstream of the combustor. Moreover, the gas turbine engine may include a flow disruption surface positioned about a trailing edge of the one or more airfoils to promote mixing of the combustion flow.

Abstract: An aerodynamic element of a turbine engine is provided and includes leading and trailing edges defined with respect to a predominant direction of a flow of working fluid through a pathway defined through the turbine engine, suction and pressure sides oppositely extending from the leading edge to the trailing edge and at least first and second contour features proximate to the leading edge on the suction side. The first and second contour features are substantially aligned along a spanwise dimension of the aerodynamic element.

Abstract: A turbine engine is provided and includes an aerodynamic element disposed to aerodynamically interact with a flow of working fluid and contour features disposed on the aerodynamic element in alignment in at least one dimension. The contour features are proximate to one another and configured to encourage counter-rotating vortex flow generation oriented substantially perpendicularly with respect to a main flow direction along the aerodynamic element.

Abstract: A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.

Abstract: A turning strut for use in a diffuser of a turbine engine has a leading edge with first and second opposing surfaces depending therefrom that terminate at a trailing edge. Slots extend through the turning strut and reduce in volume from the first surface to the second surface. During turn down operation of the turbine engine, exhaust flow impacts the leading edge at a deviated swirl angle. This results in exhaust flow at the first surface being at a higher pressure than at the second surface, which causes exhaust flow to be induced through the slots. The reduction in slot volume causes exhaust flow through the slots to accelerate. This exhaust flow from the slots is combined with exhaust flow at the second surface. Thusly, momentum of exhaust flow at the second surface is increased to maintain the second laminar boundary layer at the second surface.

Abstract: A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.

Abstract: An ophthalmic camera (10) comprising a camera (12) having a lens (18) aligned with a second lens (16) and at least one illumination means (14). The illumination means (14) is capable of movement relative to the camera lens (18) so that the beam of light emitted by the illumination means (14) is able to be focused by the second lens (16) through the pupil onto the fundus. In another embodiment, the ophthalmic camera comprises a camera (52), an illumination means (54) and a beamsplitter (58). The camera (52) and the beamsplitter (58) from an alignment axis X and the illumination means (54) together with the beam splitter (58) form an illumination axis Y perpendicular to the alignment axis X.

Abstract: Provided is an ophthalmic camera comprising: a camera having a camera lens; at least one illumination means; and an ophthalmic lens. The centres of the ophthalmic lens and camera lens are aligned to form an alignment axis. The at least one illumination means is capable of linear movement along a radial axis of the camera lens and pivotal movement about the radial plane incorporating radial axis and alignment axis. In such a manner, the circle of light emitted by the at least one illumination means is constantly directed to the centre of the ophthalmic lens.

Abstract: First stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0.05 span to 0.95 span convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.150 inches in directions normal to the surface of the airfoil.