Abstract: A method for monitoring damage of a slewing ring bearing of a wind turbine includes arranging at least one optical fiber sensor adjacent to or at least partially on at least one of an inner race or an outer race of the slewing ring bearing. Further, the method includes receiving, via a controller, signals from the at least one optical fiber sensor indicative of one or more changes associated with the slewing ring bearing. The method also includes comparing, via the controller, the one or more changes associated with the slewing ring bearing to a damage threshold. Moreover, the method includes implementing, via the controller, a control action when the one or more changes exceeds the damage threshold to prevent or minimize further damage from occurring to the slewing ring bearing.

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine centerline. An airfoil is located in one of the fan section, the compressor section, or the turbine section. The airfoil defines an interior and extends between a leading edge and a trailing edge defining a chord-wise direction, and extending between a root and a tip defining a span-wise direction. At least one stiffener is located within the interior, having a deformation threshold, and including at least one crush initiator formed on the at least one stiffener. The crush initiator determines deformation geometry of the at least one stiffener in response to a force acting on the at least one stiffener exceeding the deformation threshold.

Abstract: A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.

Abstract: A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.

Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

Abstract: A method for monitoring damage of a slewing ring bearing of a wind turbine includes arranging at least one optical fiber sensor adjacent to or at least partially on at least one of an inner race or an outer race of the slewing ring bearing. Further, the method includes receiving, via a controller, signals from the at least one optical fiber sensor indicative of one or more changes associated with the slewing ring bearing. The method also includes comparing, via the controller, the one or more changes associated with the slewing ring bearing to a damage threshold. Moreover, the method includes implementing, via the controller, a control action when the one or more changes exceeds the damage threshold to prevent or minimize further damage from occurring to the slewing ring bearing.

Abstract: A method for detecting a failure condition in one or more components of a wind turbine is provided. The method includes actuating, via a controller, an impact device to generate a vibration having a vibration frequency and a vibration magnitude in the one or more components. The method further includes receiving data indicative of the vibration frequency and the vibration magnitude from a sensor communicatively coupled to the controller. The method further includes determining, via the controller, whether the data indicative of the vibration frequency and/or the vibration magnitude is outside of a predetermined vibration range for the one or more components.

Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.

Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

Abstract: A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.

Abstract: A method for detecting a failure condition in one or more components of a wind turbine is provided. The method includes actuating, via a controller, an impact device to generate a vibration having a vibration frequency and a vibration magnitude in the one or more components. The method further includes receiving data indicative of the vibration frequency and the vibration magnitude from a sensor communicatively coupled to the controller. The method further includes determining, via the controller, whether the data indicative of the vibration frequency and/or the vibration magnitude is outside of a predetermined vibration range for the one or more components.

Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.

Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.

Abstract: A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.

Abstract: A gas turbine engine includes a compressor section and a turbine section arranged in serial flow order. A shaft is provided rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. A bearing is also provided supporting rotation of the shaft, with a support element in turn supporting the bearing. The gas turbine engine also includes a superelastic member formed of a shape memory alloy supporting at least one of the support element or the bearing. The superelastic member is installed in a pre-stressed condition to enhance a dampening function of the superelastic member.

Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.

Abstract: A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.

Abstract: A support assembly for a load-bearing unit, a gas turbine engine including the support assembly, and a method of operation of the support assembly are provided. The support assembly includes a support element, a damper, and a variable stiffness member. The support element supports the load-bearing unit. The damper supports the support element and is configured to provide dampening of the load-bearing unit. The variable stiffness member is positioned between the damper and the load-bearing unit. The variable stiffness member is configured to provide a serial dampening of the load-bearing unit with the damper. The variable stiffness member includes a shape memory alloy.