Abstract: Systems and methods for rendering video with teleprompter script overlays are described. A video rendering system provides a user interface for displaying a script for use during the rendering of the video (e.g., while the user records and/or streams the video). The script is arranged such that it at least partially overlays the video feed and is positioned within the display of the user interface to produce a line of sight of a user corresponding to first region of a field of view of the video capture device. When a user's line of sight is fixed upon the script overlay (i.e., when the user is reading the script) and aligned with the first region of the field of view of the video capture device, a viewer of the video rendering is given a visual perception that the user is looking directly at the viewer (e.g., making eye contact).

Abstract: Systems and methods for rendering video with teleprompter script overlays are described. A video rendering system provides a user interface for displaying a script for use during the rendering of the video (e.g., while the user records and/or streams the video). The script is arranged such that it at least partially overlays the video feed and is positioned within the display of the user interface to produce a line of sight of a user corresponding to first region of a field of view of the video capture device. When a user's line of sight is fixed upon the script overlay (i.e., when the user is reading the script) and aligned with the first region of the field of view of the video capture device, a viewer of the video rendering is given a visual perception that the user is looking directly at the viewer (e.g., making eye contact).

Abstract: Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.

Abstract: Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.

Abstract: A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.