Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

Abstract: A wind blade is provided. The wind blade includes a body having an aerodynamic contour extended between a blade root and a blade tip. The wind blade also includes an extension tip sleeve arranged over the blade tip. The extension tip sleeve further includes a first portion having an extension blade and one or more structural ribs arranged on a pressure side of the wind blade. The extension tip sleeve also includes a second portion having a support structure located on a suction side of the wind blade. Furthermore, the wind blade includes a fairing having an airfoil shape for covering the one or more structural ribs, and the support structure of the extension tip sleeve.

Abstract: A wind blade is provided. The wind blade includes a body having an aerodynamic contour extended between a blade root and a blade tip. The wind blade also includes an extension tip sleeve arranged over the blade tip. The extension tip sleeve further includes a first portion having an extension blade and one or more structural ribs arranged on a pressure side of the wind blade. The extension tip sleeve also includes a second portion having a support structure located on a suction side of the wind blade. Furthermore, the wind blade includes a fairing having an airfoil shape for covering the one or more structural ribs, and the support structure of the extension tip sleeve.

Abstract: A wind turbine system is presented. The wind turbine system includes a blade comprising an airfoil and a sensing device disposed on a surface of the airfoil, wherein the sensing device generates signals that are representative of pressure deflection on the surface of the airfoil. The wind turbine system further comprises a processing subsystem that receives location details of the sensing device and a transfer function corresponding to the airfoil, determines a location of a stagnation point on the surface of the airfoil based upon the signals and the location details, and determine an angle of attack (AOA) on the surface of the airfoil based upon the location of the stagnation point and the transfer function.

Abstract: A blade is presented. The blade includes a proximal end and a distal end, and a pronounced camber running between the proximal end to the distal end, wherein the pronounced camber is located in proximity to a trailing edge and on a suction side of the blade, and an amplitude of the pronounced camber at a location varies between about 0.7% to about 1.4% of a chord's length of a cross-section of the blade at said location.

Abstract: A wind turbine system is presented. The wind turbine system includes a blade comprising an airfoil and a sensing device disposed on a surface of the airfoil, wherein the sensing device generates signals that are representative of pressure deflection on the surface of the airfoil. The wind turbine system further comprises a processing subsystem that receives location details of the sensing device and a transfer function corresponding to the airfoil, determines a location of a stagnation point on the surface of the airfoil based upon the signals and the location details, and determine an angle of attack (AOA) on the surface of the airfoil based upon the location of the stagnation point and the transfer function.

Abstract: A wind turbine includes a plurality of rotor blades for converting wind energy to rotational energy. The rotor blades have winglets that are configurable. A sensor senses a parameter and generates a sensed signal indicative of the parameter. A processor receives the sensed signal for generates an actuator signal in response thereto. An actuator is associated with each of the winglets for configuring the winglets in response to the actuator signal.

Abstract: A method of manipulating a boundary layer across a wind turbine rotor blade. The method includes coupling at least one vortex generator to the rotor blade. The vortex generator includes at least one sidewall that extends outwardly a radial distance from an outer surface of the rotor blade. The vortex generator is selectively positionable between a first position and a second position. A control system calculates a condition of the boundary layer. The vortex generator is positioned at one of the first position and the second position based on the calculated condition of the boundary layer for moving the vortex generator between the first position and the second position.

Abstract: A method of manipulating a boundary layer across a wind turbine rotor blade. The method includes coupling at least one vortex generator to the rotor blade. The vortex generator includes at least one sidewall that extends outwardly a radial distance from an outer surface of the rotor blade. The vortex generator is selectively positionable between a first position and a second position. A control system calculates a condition of the boundary layer. The vortex generator is positioned at one of the first position and the second position based on the calculated condition of the boundary layer for moving the vortex generator between the first position and the second position.