Abstract: A seal monitoring apparatus is provided. The seal monitoring apparatus includes one or more pressure sensors and a controller in communication with the one or more pressure sensors. The one or more pressure sensors is mounted at a seal of a turbine to measure pressure on a first side of the seal and/or a second side of the seal. The controller is configured to receive pressure data from the one or more pressure sensors and determine a condition of the seal based at least in part on the pressure data. The controller is configured to output a signal upon determining a change in the condition of the seal.

Abstract: A seal monitoring apparatus is provided. The seal monitoring apparatus includes a temperature sensor and a controller in communication with the temperature sensor. The temperature sensor is mounted at a seal of a device. The controller is configured to receive measured temperature data from the temperature sensor and calculate expected temperature data for the seal based at least in part on operating conditions of the device. The controller is configured to determine a condition of the seal based at least in part on a temperature difference of the measured temperature data from the expected temperature data.

Abstract: Systems and methods for routing requests to a plurality of server clusters are disclosed, especially in a workflow management context. A first server cluster handles requests concerning a first software version and a second server cluster responds to requests concerning a second version of that same software. Upon receiving a request to change default routing of requests, a configuration of a gateway router is updated and subsequent requests concerning the first software are routed to the second server cluster while subsequent request concerning the second software remain routed to the first server cluster. A first graphical user interface (GUI) is provided to be used in defining a series of steps in a workflow and to creating a secondary GUI that will be used when performing the series of steps. Tools for automation and data extraction during the workflow are provided and workflow state is tracked until completion of the workflow.

Abstract: A seal assembly at a rotor-stator interface includes at least one non-contacting seal interface and at least one rub detection feature. The rub detection feature(s) is configured to generate a signal upon the rotor and the stator making contact at the rotor-stator interface and causing wear above a certain threshold at the rotor-stator interface. The seal assembly also includes at least one sensor arranged at the rotor-stator interface. The sensor is configured to sense the signal. The seal assembly further includes a controller communicatively coupled with the sensor(s). The controller is configured to receive the signal and estimate at least one of an amount and a location of the wear at the rotor-stator interface based on the signal.

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 flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

Abstract: A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

Abstract: A rotary machine seal assembly (200) includes seal segments (102) configured to circumferentially extend around a rotor (108) between a stator (106) and the rotor (108) of a rotary machine. One or more seal segments include a shoe plate (110, 410, 710, 910), a seal base (112, 412, 712, 912), and at least one intermediate member (114, 414, 714). The shoe plate is disposed along the rotor. The seal base is disposed radially outward of the shoe plate. At least one intermediate member is coupled to and disposed between the seal base and the shoe plate. The at least one intermediate member includes an actuator portion (302, 402, 702, 902) having first coefficient of thermal expansion and a constrictor portion (304, 404, 704, 904) having a different, second coefficient of thermal expansion.

Abstract: A system for use in servicing a machine. The system includes a tubular body including a longitudinal axis, a tip end, a dispensing nozzle defined at the tip end, and an interior channel in flow communication with the dispensing nozzle. The tubular body is configured to be flexible. An actuator is configured to selectively modify an orientation of the tubular body, and a reservoir is in flow communication with the interior channel. The reservoir is configured to supply a maintenance fluid to the tubular body for discharge from the dispensing nozzle.

Abstract: A system for use in servicing a machine. The system includes a tubular body including a longitudinal axis, a tip end, a dispensing nozzle defined at the tip end, and an interior channel in flow communication with the dispensing nozzle. The tubular body is configured to be flexible. An actuator is configured to selectively modify an orientation of the tubular body, and a reservoir is in flow communication with the interior channel. The reservoir is configured to supply a maintenance fluid to the tubular body for discharge from the dispensing nozzle.

Abstract: An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.

Abstract: A system for use in servicing a turbomachine, the system including a first tubular body including an interior channel, and a second tubular body. The first and second tubular bodies are bendable between a neutral shape and a biased shape. The bodies are bent when in the neutral shape. The second tubular body includes a tip end, and the second tubular body is translatable within the interior channel. The first tubular body and the second tubular body are rotatable to selectively orient the tip end in multiple degrees of freedom. The system also includes a steering cable extending from the tip end, wherein the steering cable biases the tip end for selective orientation in additional degrees of freedom.

Abstract: An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.

Abstract: An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body including: a first hinge; a second hinge, the first and second hinge members pivotally coupling adjacent segments of the plurality of segments together; and a cavity extending along the body of the segment, the cavity exiting the body at a plurality of exit locations, wherein at least one of the plurality of exit locations is disposed adjacent to the first hinge; and a selectively rigidizable strength member disposed within the cavity.

Abstract: An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body comprising: a first hinge; and a second hinge, the first hinge of a first segment being coupled to the second hinge of a second segment adjacent to the first segment through an interface, wherein the interface comprises a powder gap, a multi-modal interface, a compliance feature, a displace-to-lock configuration, an interference fit, or any combination thereof, wherein the insertion tool is configured to be selectively rigidizable using a strength member interfacing with the plurality of segments.

Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.

Abstract: A face seal assembly including a thermal fluid circuit, a turbomachine including the face seal assembly and a method of operating the turbomachine are disclosed. The face seal assembly includes a seal ring including a seal bearing face, at least one internal cavity including a cavity inlet and a cavity outlet. The face seal assembly further including a fluid inlet channel in fluid communication with the cavity inlet of the at least one internal cavity and a pressurized fluid and a fluid outlet port in fluid communication with the cavity outlet of the at least one internal cavity. The at least one internal cavity, the fluid inlet channel and the fluid outlet port define a thermal fluid circuit providing thermal management of the seal ring. In the turbomachine, the face seal assembly is disposed between a stationary component and a rotating component including a rotating component bearing face.

Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.