Abstract: A seal assembly for a turbomachine includes a rotating component, a non-rotating component having a ring carrier, a face seal ring, and a joint disposed between the ring carrier and the non-rotating component. The non-rotating component is arranged with the rotating component at a sealing interface. The joint is capable of linear and tilt displacement to allow the non-rotating component to displace with respect to the rotating component. The sealing interface defines a gap between the face seal ring and the rotating component. The seal assembly also includes at least one damping element arranged with the ring carrier for maintaining the seal assembly centrally in a radial direction in the turbomachine. Further, the damping element(s) includes at least one mass element.

Abstract: A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.

Abstract: A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.

Abstract: A power transmission gearbox system for a turbomachine is provided. the power transmission gearbox system includes a drivetrain having one or more rotating components. The system further includes at least one static component interfacing with the one or more rotating components. The system further includes a sensor disposed on the at least one static component and configured to provide data indicative of strain in the static component. The system further includes a controller communicatively coupled to the sensor. the controller includes a processor and a memory. the processor is configured to perform a plurality of operations. The plurality of operations includes monitoring the data indicative of strain in the static component from the sensor. The operations further include determining, at least partially based on the data indicative of the strain in the static component, a torque in the one or more rotating components of the drivetrain.

Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.

Abstract: A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.

Abstract: A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.

Abstract: Methods and systems of electrochemically machining a component are provided. The method may include applying two or more potentials to a tool electrode comprising an array of two or more individual electrodes to generate two or more electric fields in between the tool electrode and a workpiece opposite of the tool electrode, wherein each of the two or more electric fields is generated by one of the array of two or more individual electrodes.

Abstract: An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142), wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).

Abstract: A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 298.17 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m2/m3 and 13,000 m2/m3.

Abstract: A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.

Abstract: A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 48 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m2/m3 and 13,000 m2/m3.

Abstract: A powered system that has an electric power system with a stator having plural poles with each pole having a conductive winding that may surround the corresponding pole and may be configured to generate a magnetic field, and a rotor that may be configured to rotate in response to the magnetic field generated by the stator. The at least one of the conductive windings may be insulated with an insulation material configured to conduct heat from the at least one conductive winding while operating at a temperature above 600° C.

Abstract: A system includes a first working fluid compressor configured to pressurize a working fluid, and a prime mover coupled to the first working fluid compressor and configured to provide a mechanical input into the first working fluid compressor. An exhaust assembly is coupled to the prime mover and is configured to receive exhaust heat from the prime mover, the exhaust assembly including a generator configured to generate electric current based on the exhaust heat received by the exhaust assembly. A second working fluid compressor includes an electric motor electrically and synchronously coupled to the generator and configured to pressurize the working fluid.

Abstract: A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

Abstract: A bearing system including a frequency independent damper assembly and a bearing pad assembly. The damper assembly includes a housing, a plunger, a moving central post and a support spring. The plunger is movable within a housing to define a first primary damper cavity and a second primary damper cavity. The moving central post has defined therein a fluid channel for a pressurized working fluid flow. The support spring includes a plurality of flexible elements coupled to the housing and disposed radially outward of the first and second primary damper cavities. The support spring defines first and second accumulator cavity. A flow-through channel couples the first accumulator cavity to the second accumulator cavity. In an embodiment, the flow-through channel may be disposed within the moving central post. The bearing pad assembly includes a bearing pad including a plurality of bearing pad orifices coupled to the fluid channel in the moving central post.

Abstract: A turbine blade includes an internal vibration damping system having a plurality of unit cells. Each unit cell includes: an impacting structure; and a cavity encapsulating the impacting structure. The cavity, which includes a first hemisphere and a second hemisphere, is disposed within a substrate, which forms an outer casing of the cavity. At least one fluid is disposed in each of the first and second hemispheres between the impacting structure and the outer casing.

Abstract: A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.

Abstract: A unit cell (26) for use in a damping system (24) includes: an impacting structure (34); a cavity (32) encapsulating the impacting structure (34), the cavity (32) including a first hemisphere (32A) and a second hemisphere (32B), the cavity (32) disposed within a substrate (28), the substrate (28) forming an outer casing of the cavity (32); and at least one fluid (36) disposed in each of the first and second hemispheres (32A, 32B) between the impacting structure (34) and the outer casing (28).

Abstract: A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.