Abstract: A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on a machine and coupled to a laser system.

Abstract: A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on a machine and coupled to a laser system.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on an automated machine and coupled to a laser system.

Abstract: A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Abstract: An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.

Abstract: A system is provided for performing an operation on a component of an engine. The component includes a first side positioned within an interior of the engine. The system includes a first robotic arm defining a first distal end and including a first utility member positioned at the first distal end, the first robotic arm moveable to the interior of the engine to a location operably adjacent to the first side of the component; and a second robotic arm defining a second distal end and including a second utility member positioned at the second distal end, the second robotic arm also moveable to the interior of the engine to facilitate the first and second utility members performing the operation on the component of the engine.

Abstract: A system for performing ultrasonic procedures within a turbomachine. The system includes a bladder and a probe assembly. The bladder includes a bladder body for positioning within the turbomachine. Further, the bladder is inflatable to at least partially define an ultrasonic tank within the turbomachine for containing a fluid medium. The probe assembly includes an extension member and ultrasonic transmitter coupled to or positioned within the extension member. The extension member is insertable into the ultrasonic tank for positioning the ultrasonic transmitter within the ultrasonic tank.

Abstract: An engine assembly includes an engine including a component and defining an opening and an interior, the component including a first side and an opposite second side, the second side positioned within the interior of the engine. The engine assembly also includes an inspection tool having a first member including at least one of a receiver or a transmitter and directed at the first side of the component. The inspection tool also includes a second member including the other of the receiver or the transmitter and positioned at least partially within the interior of the engine and directed at the second side of the component to communicate a signal with the first member through the component, the second member being a robotic arm extending through the opening of the engine.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on an automated machine and coupled to a laser system.

Abstract: A system for performing ultrasonic procedures within a turbomachine. The system includes a bladder and a probe assembly. The bladder includes a bladder body for positioning within the turbomachine. Further, the bladder is inflatable to at least partially define an ultrasonic tank within the turbomachine for containing a fluid medium. The probe assembly includes an extension member and ultrasonic transmitter coupled to or positioned within the extension member. The extension member is insertable into the ultrasonic tank for positioning the ultrasonic transmitter within the ultrasonic tank.

Abstract: A system is provided for performing an operation on a component of an engine. The component includes a first side positioned within an interior of the engine. The system includes a first robotic arm defining a first distal end and including a first utility member positioned at the first distal end, the first robotic arm moveable to the interior of the engine to a location operably adjacent to the first side of the component; and a second robotic arm defining a second distal end and including a second utility member positioned at the second distal end, the second robotic arm also moveable to the interior of the engine to facilitate the first and second utility members performing the operation on the component of the engine.

Abstract: An engine assembly includes an engine including a component and defining an opening and an interior, the component including a first side and an opposite second side, the second side positioned within the interior of the engine. The engine assembly also includes an inspection tool having a first member including at least one of a receiver or a transmitter and directed at the first side of the component. The inspection tool also includes a second member including the other of the receiver or the transmitter and positioned at least partially within the interior of the engine and directed at the second side of the component to communicate a signal with the first member through the component, the second member being a robotic arm extending through the opening of the engine.

Abstract: A system for compensating for a relative motion between a probe and an apparatus. The system includes a probe assembly, a sensor, and a computer. The probe assembly includes an actuator pack positioned exterior to the apparatus and a probe insertable into the apparatus. The probe includes a first end coupled to the actuator pack, a second end, and an elongated body extending therebetween. The sensor senses data indicative of a relative motion between the apparatus and the probe assembly. The computer is operably coupled with the sensor and the probe assembly to move the probe of the probe assembly in response to the sensor sensing the data indicative of the relative motion between the apparatus and the probe assembly.

Abstract: The example embodiments are directed to a device and method for matching together aircraft status reports. In one example, the method includes detecting, via a user interface, a selection of an aircraft from among a plurality of aircraft that have provided aircraft status reports, determining a group of aircraft status reports, from among the received status reports, which were generated by the respective aircraft during a flight of the respective aircraft, based on metadata of the received aircraft status reports, and displaying, via the user interface, the group of aircraft status reports determined to be provided by the respective aircraft during the flight. By linking together status reports from an entire flight, analysis may be performed on data from across an entire flight instead of an individual status report thereby improving flight data analysis and subsequent actions taken based on that analysis.

Abstract: The example embodiments are directed to a device and method for matching together aircraft status reports. In one example, the method includes detecting, via a user interface, a selection of an aircraft from among a plurality of aircraft that have provided aircraft status reports, determining a group of aircraft status reports, from among the received status reports, which were generated by the respective aircraft during a flight of the respective aircraft, based on metadata of the received aircraft status reports, and displaying, via the user interface, the group of aircraft status reports determined to be provided by the respective aircraft during the flight. By linking together status reports from an entire flight, analysis may be performed on data from across an entire flight instead of an individual status report thereby improving flight data analysis and subsequent actions taken based on that analysis.

Abstract: A system for collecting and storing performance data for an engine is provided. The system includes one or more sensors configured to generate sensor data signals representative of one or more engine data performance parameters. The system further includes a data sampling component, a data quantizing component, a data storage sampling rate component, a data encoding component and a data storage component. The data sampling component is configured to sample the sensor data signals at a data sampling rate. The data quantizing component is configured to generate quantized data samples corresponding to the sampled sensor data signals. The data storage sampling rate component is configured to determine a data storage sampling rate for the quantized data samples, based on an analysis of at least a subset of the quantized data samples.

Abstract: A method for estimating a trend in exhaust gas temperature in a turbine engine includes sampling exhaust gas temperature and a plurality of variables associated with the exhaust gas temperature over a set of observation times for a turbine engine to acquire exhaust gas temperature data. A trend in the exhaust gas temperature for the specific turbine engine is identified by removing the effect of the plurality of variables on the exhaust gas temperature data.

Abstract: A system for collecting and storing performance data for an engine is provided. The system includes one or more sensors configured to generate sensor data signals representative of one or more engine data performance parameters. The system further includes a data sampling component, a data quantizing component, a data storage sampling rate component, a data encoding component and a data storage component. The data sampling component is configured to sample the sensor data signals at a data sampling rate. The data quantizing component is configured to generate quantized data samples corresponding to the sampled sensor data signals. The data storage sampling rate component is configured to determine a data storage sampling rate for the quantized data samples, based on an analysis of at least a subset of the quantized data samples.