Various embodiments include approaches for monitoring turbomachine components. In various particular embodiments, a system 2 for monitoring a component 6 within a turbomachine 4 includes: a borescope probe 22 sized to pass through an opening 14 in the turbomachine 4, the borescope probe 22 for detecting a symbolic data array 18 on the component 6 within the turbomachine 4; and at least one computing device 24 operably coupled to the borescope probe 22, the at least one computing device 24 configured to: obtain image data 30 about the symbolic data array 18 from the borescope probe 22; evaluate the image data 30 to determine whether the image data is compatible with a symbolic data array analysis program 28; and analyze the image data 30 using the symbolic data array analysis program 28 in response to determining the image data 30 is compatible with the symbolic data array analysis program 28.

Turbomachine component monitoring system and method

A boroscope has a first end and a second end, and the first end of the boroscope has an optical fiber and light source. A working head is attached to the first end of the boroscope. The working head has an electrical motor, and a tool is attached to and is arranged to be driven by the electrical motor. The boroscope carries a cable extending from the electrical motor to the second end of the boroscope.

Boroscope and a method of processing a component within an assembled apparatus using a boroscope

A machine comprises an enclosure; a plurality of parts within the enclosure; and a visual conduit for providing a view inside of the enclosure for detection of visible signs of failure of the machine. The concept of a visual conduit encompasses a broad variety of devices including cameras inside the enclosure that provide images of the interior of the enclosure and alternatively selective transparency or translucence of the enclosure relative to at least some of the parts of the machine housed within the enclosure.

Sensor for imaging inside equipment

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

System and Method for In Situ Repair of Gas Turbine Engine Casing Clearance

Methods for material build-up on a tip of a blade of a gas turbine engine are provided. The method can include inserting a material supply adjacent to the tip and directing a laser onto the interface of the material supply and the tip such that the material supply melts and attaches to the tip. Methods are also provided for remotely stopping a crack in a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; supplying a new material to the fillable area to fill the defect; and directing a laser to the new material within the fillable area to fuse the new material to the component within the defect.

In situ gas turbine prevention of crack growth progression via laser welding

An apparatus for supporting a tool in an assembled apparatus. The apparatus includes a support structure, the support structure having a central member and a plurality of support members pivotally mounted on the central member. The support members are movable between a non-deployed position in which the support members extend a minimum distance from the central member and a deployed position in which the support members extend a maximum distance from the central member.

Method of supporting a tool and an apparatus for supporting a tool in an assembled apparatus

Apparatus for supporting a tool 106 in an assembled apparatus 10 comprises a support structure 60 including a plurality of support members 82, 84 pivotally mounted on a central member 76 between deployed and non-deployed positions respectively closer and further from the central member 76. The assembled apparatus 10 may be a gas turbine engine. The support members 82, 84 may have grips or tensioners 90, 92 at their ends or they may be cams (382, 384 fig. 10). The tool 106 is supported in an assembled apparatus 10 by inserting a support structure 60 through a first aperture 52, 56 in a casing 50, 54 of the apparatus 10 with a first end 62 of the support structure 60 outside the casing 50, 54 and a second end 64 of the support structure 60 inside the casing 50, 54, securing the first end 62 of the support structure 60 to the casing 50, 54 for example at a boss, abutting a first portion 78 of the support structure 60 to at least one surface within the casing 50, 54 such as an inner platform of a stator vane or an outer surface of a rotor, inserting the tool 106 through the first aperture 52, 56 or a second aperture 53, 57 in the casing 50, 54 and securing the tool 106 to a second portion 102 of the support structure 60 within the casing 50, 54 for example by means of a magnet. The pivotally mounted support members 82, 84 permit insertion of the support structure 60 through the first aperture 52, 56 and then clamping of the support structure 60 to the casing 54. The tool 106 may be a borescope, a conduit, a light source, a cutter, a grinder, a laser, a welding torch or a spray deposition gun. Several tools may be inserted through several apertures in the casing 50, 54 and secured to several support structures 60.

Support for a tool in an assembled apparatus

A method of supporting a tool (106) in an assembled apparatus (10) comprises the steps of (a) inserting a support structure (60) through a first aperture (52,56) in a casing (50,54) of the apparatus (10), a first end (62) of the support structure (60) being outside the casing (50,54) and a second end (64) of the support structure (60) being inside the casing (50,54), (b) securing the first end (60) of the support structure (60) to the casing (50,54), (c) arranging a first portion (78) of the support structure (60) to abut at least one surface within the casing (50,54), (d) inserting a tool (106) through the first aperture (52,56) or a second aperture (53,57) in the casing (50,54), and (e) securing the tool (106) to a second portion (102) of the support structure (60) within the casing (50,54).

A method of supporting a tool in an assembled apparatus

An apparatus for supporting a tool in an assembled apparatus

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Method of supporting a tool and an apparatus for supporting a tool in an assembled apparatus

Support for a tool in an assembled apparatus

A method of supporting a tool in an assembled apparatus

An apparatus for supporting a tool in an assembled apparatus