A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.

A method of motoring a gas turbine engine is provided. The method comprises: determining a first speed to motor a gas turbine engine for cooling; motoring a gas turbine engine at the first speed; detecting a gap parameter of a gas turbine engine; detecting a speed parameter of the gas turbine engine; detecting a vibration parameter of the gas turbine engine; and motoring the gas turbine at a second speed in response to at least one gap parameter, speed parameter, and vibration parameter.

A system for identifying timeframes for borescope inspections for a gas turbine engine, having: monitoring systems monitor engine conditions, derive engine condition information and communicate such information to processors; feature interpreter module electronically communicates (i) with processors to process engine condition information, and (ii) feature interpreter information to processors, such information defines a probability of a FOD event; accumulator module electronically communicates (i) with processors to processes feature interpreter information, stored information since a last borescope inspection, and (ii) accumulator information to processors, such information defines an accumulated probability of a FOD event; and predictor and inspection planner module electronically communicates (i) with processors to processes accumulator information and stored information defines a threshold limits for a probability of a FOD event, and (ii) predictor and inspection planner information to processors, such information identifies a timeframe for a next borescope inspections predicted to occur before a FOD event.

A system and method for monitoring a gap size of a gap between a seal holder and an adjacent disk in a compressor section of a gas turbine. An imaging device is used to generate at least one image of the gap, wherein a calibration image of the gap is generated when the gas turbine is in a cold state to provide a calibration gap size. An operational image of the gap is also generated when the gas turbine is in operation to provide an operational gap size. In addition, an enclosure that houses the imaging device is attached to an access port formed in the compressor section to provide a view of the gap for the imaging device. Wear is detected in a hook section of the compressor section when the operational gap size is less than the calibration gap size.

Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

A dry gas seal for sealing the shaft of a turbomachinery, provided with means for the continuous health monitoring of the dry gas seal comprising one or more sensors adapted to measure strains and/or loads induced to the primary ring of the dry gas seal and/or strains induced to one or more of the elastic elements coupled to the primary ring and/or adapted to measure displacements of the primary ring or of an element coupled to the primary ring, for an early detection of failure of the seal, thus enabling main failures early detection capability and proactive maintenance actions.

A system and method for monitoring a gap size of a gap between a seal holder and an adjacent disk in a compressor section of a gas turbine. An imaging device is used to generate at least one image of the gap, wherein a calibration image of the gap is generated when the gas turbine is in a cold state to provide a calibration gap size. An operational image of the gap is also generated when the gas turbine is in operation to provide an operational gap size. In addition, an enclosure that houses the imaging device is attached to an access port formed in the compressor section to provide a view of the gap for the imaging device. Wear is detected in a hook section of the compressor section when the operational gap size is less than the calibration gap size.

A turbine system may include several air lines that extend from a compressor to a turbine, and the air lines may have valves. Additionally, the turbine system may also include several sensors that are coupled to the valves, several actuators that are coupled to the valves, and a controller that can send a command to set a valve position of one of the valves based at least partially on a valve position of another valve.

A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.

A support assembly for a gas turbine engine includes a control ring that extends about a circumferential axis. A plurality of first supports has a cavity that receives the control ring. A plurality of cover plates are attached to the first plurality of supports and enclose the cavity.