Abstract: Systems and methods for automatic feedback control are provided. According to one embodiment of the disclosure, a method for automatic feedback control may commence with receiving high-level control references by a low-level controller communicatively coupled to a high-level controller via the network connection. The method may further include generating, by the low-level controller, low-level control references for a hardware asset based at least in part on the high-level control references. The method may continue with transferring control of the hardware asset to the low-level controller in response to a loss of the network connection. The method may further include adjusting the low-level control references by a low-level control mechanism associated with the low-level controller in response to the loss of the network connection.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

Abstract: Systems and methods for automatic feedback control are provided. According to one embodiment of the disclosure, a method for automatic feedback control may commence with receiving high-level control references by a low-level controller communicatively coupled to a high-level controller via the network connection. The method may further include generating, by the low-level controller, low-level control references for a hardware asset based at least in part on the high-level control references. The method may continue with transferring control of the hardware asset to the low-level controller in response to a loss of the network connection. The method may further include adjusting the low-level control references by a low-level control mechanism associated with the low-level controller in response to the loss of the network connection.

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

Abstract: In order to allow better introduction of forces into the box section of an aircraft engine attachment pylon, the subject matter herein discloses a pylon including a primary structure forming a box section on the outside of which a body of the engine attachment is arranged, the latter also being equipped with shackles that are articulated on the body and can be articulated on the engine. According to the disclosure herein, the body has, at at least one of its ends, a one-piece fitting including a first joining portion on which one of the shackles can be articulated, and also a second joining portion that is fixed to the box section and passes into the latter.

Abstract: A protective assembly and structural element for an aircraft comprising a portion of an attachment pylon primary structure is provided. The attachment pylon primary structure portion is at least partially covered by a protective assembly comprising a layer forming a firewall and a thermally insulating layer, the thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion. The protective assembly is attached to the pylon primary structure by fasteners axially arranged in pairs, one of each pair extending through the protective assembly and the other of each pair extending through the pylon primary structure.

Abstract: In order to decrease the overall mass of an assembly for an aircraft, including an engine attachment pylon and an engine attachment, the pylon according to the disclosure herein has a primary structure forming a box section equipped with internal transverse stiffening ribs, one of which is produced in one piece with at least a part of the body of the engine attachment.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

Abstract: A subsea friction welding apparatus comprises a chuck for supporting and retaining a weld item prior to welding the weld item to a work-piece, said chuck comprises a plurality of jaws having an internal profile to grip a corresponding profiled surface on the weld item and means for radially expanding the internal profile of the jaws of the chuck, said means actuable by axial insertion of the weld item into the chuck thereby avoiding relative rotation of the chuck and the weld item during insertion of the weld item into the chuck. In operation of the method, a supply of weld items and a weld head are deployed to a subsea location and the weld items are loaded via ROV into the weld head at the subsea location.

Abstract: A subsea friction welding apparatus comprises a chuck for supporting and retaining a weld item prior to welding the weld item to a work-piece, said chuck comprises a plurality of jaws having an internal profile to grip a corresponding profiled surface on the weld item and means for radially expanding the internal profile of the jaws of the chuck, said means actuable by axial insertion of the weld item into the chuck thereby avoiding relative rotation of the chuck and the weld item during insertion of the weld item into the chuck. In operation of the method, a supply of weld items and a weld head are deployed to a subsea location and the weld items are loaded via ROV into the weld head at the subsea location.

Abstract: The subject application involves a method of controlling operation of a gas turbine. The method includes determining a first temperature associated with a portion of the gas turbine during operation of said gas turbine, and sensing an operational parameter of the gas turbine during operation of the gas turbine. An ambient pressure in an ambient environment of the gas turbine is also sensed, and the operational parameter corrected using the ambient pressure sensed in the ambient environment of the gas turbine to establish a corrected operational parameter. A threshold temperature is determined based at least in part on the corrected operational parameter, and a backup routine is initiated to limit operation of the gas turbine when the temperature associated with the gas turbine is greater than or equal to the threshold temperature.

Abstract: In order to allow better introduction of forces into the box section of an aircraft engine attachment pylon, the subject matter herein discloses a pylon including a primary structure forming a box section on the outside of which a body of the engine attachment is arranged, the latter also being equipped with shackles that are articulated on the body and can be articulated on the engine. According to the disclosure herein, the body has, at at least one of its ends, a one-piece fitting including a first joining portion on which one of the shackles can be articulated, and also a second joining portion that is fixed to the box section and passes into the latter.

Abstract: The disclosure herein relates to a structural element for an aircraft comprising a portion of an attachment pylon primary structure. According to the disclosure herein, the attachment pylon primary structure portion is at least partially covered by a protective assembly comprising a layer forming a firewall and a thermally insulating layer, thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion.

Abstract: In order to decrease the overall mass of an assembly for an aircraft, including an engine attachment pylon and an engine attachment, the pylon according to the disclosure herein has a primary structure forming a box section equipped with internal transverse stiffening ribs, one of which is produced in one piece with at least a part of the body of the engine attachment.

Abstract: Systems and methods for providing stepping actuations in a power generation unit are disclosed. Certain embodiments herein may relate to manipulating actuators to produce a desired output in a power generation unit without disrupting production by the power generation output, such as megawatt and/or steam production. A model may be generated that includes one or more inputs and associated outputs in a power generation unit. The model may be leveraged to determine an actuator to adjust to create a desired output, as well as one or more different actuators to adjust to offset an otherwise negative impact on power generation unit production while maintaining the desired output.

Abstract: Embodiments of the invention can provide systems and methods for modifying the operation and/or performance of a gas turbine. According to one embodiment, a method for modifying the performance of a gas turbine comprising one or more combustors can be provided. The method can include measuring a gas exhaust temperature for the gas turbine and estimating a heat transfer rate for the gas turbine based at least in part on the gas exhaust temperature. After estimating the heat transfer rate, the method can continue by estimating a transiently accurate combustion reference temperature and using this parameter to control the one or more combustors of the gas turbine. In doing so, the performance of the gas turbine can be modified to ensure reliable and consistent operation.

Abstract: Embodiments of the invention can provide systems and methods for modifying the operation and/or performance of a gas turbine. According to one embodiment, a method for modifying the performance of a gas turbine comprising one or more combustors can be provided. The method can include measuring a gas exhaust temperature for the gas turbine and estimating a heat transfer rate for the gas turbine based at least in part on the gas exhaust temperature. After estimating the heat transfer rate, the method can continue by estimating a transiently accurate combustion reference temperature and using this parameter to control the one or more combustors of the gas turbine. In doing so, the performance of the gas turbine can be modified to ensure reliable and consistent operation.

Abstract: The subject application involves a method of controlling operation of a gas turbine. The method includes determining a first temperature associated with a portion of the gas turbine during operation of said gas turbine, and sensing an operational parameter of the gas turbine during operation of the gas turbine. An ambient pressure in an ambient environment of the gas turbine is also sensed, and the operational parameter corrected using the ambient pressure sensed in the ambient environment of the gas turbine to establish a corrected operational parameter. A threshold temperature is determined based at least in part on the corrected operational parameter, and a backup routine is initiated to limit operation of the gas turbine when the temperature associated with the gas turbine is greater than or equal to the threshold temperature.