Abstract: In some instances, ice can form on the surface of a compressor airfoil. If the ice dislodges, it can impact and damage other compressor components. Aspects of the invention relate to systems for detecting the presence of ice or water on a compressor vane during engine operation. A ceramic insulating coating can be deposited on a portion of the surface of the vane. A heater and a thermocouple can be provided near the outermost surface of the coating such that the thermocouple can sense heat from the heater. The heater and the thermocouple can be provided within the coating. The presence of water film and/or ice on the coating surface can be detected by taking a thermocouple measurement following a heater pulse. The presence of a water film or ice results in a delay in the temperature rise detected by the thermocouple.

Abstract: Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Abstract: A generator monitoring system and method includes a plurality of sensors (12) disposed within a generator enclosure (18) to sense health conditions of a generator (10) housed within the enclosure. The sensors are interconnected to provide a single communication path (14) for allowing communication with the plurality of sensors. A monitoring device (16) outside the generator enclosure receives health condition information from each of the plurality of sensors via the single communication path. A sensor may be disposed within the generator enclosure to detect particulates emitted from a monitored portion (e.g., 52) of the generator housed within the enclosure. A sensor may be disposed proximate a bus bar connection (130) of the generator to sense a health condition of the bus bar connection and generate corresponding health condition information provided to the monitoring device.

Abstract: A method for measuring the differential emissivity between two sites on the surface of a body and the temperature of the two sites. The method includes a plurality of measurements of the infrared radiation arising from each of the two sites under a number of different conditions. Some of the measurements include irradiation by external infrared radiation at a known wavelength and intensity. The infrared radiation arising from each of the sites may include emitted radiation, reflected ambient radiation, and reflected external radiation. Additionally, the temperature determined using the method described can be used to calibrate infrared imaging devices used to inspect the entire body.

Abstract: In some instances, ice can form on the surface of a compressor airfoil. If the ice dislodges, it can impact and damage other compressor components. Aspects of the invention relate to systems for detecting the presence of ice or water on a compressor vane during engine operation. A ceramic insulating coating can be deposited on a portion of the surface of the vane. A heater and a thermocouple can be provided near the outermost surface of the coating such that the thermocouple can sense heat from the heater. The heater and the thermocouple can be provided within the coating. The presence of water film and/or ice on the coating surface can be detected by taking a thermocouple measurement following a heater pulse. The presence of a water film or ice results in a delay in the temperature rise detected by the thermocouple.

Abstract: Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Abstract: The claimed invention provides a blade vibration measuring system comprising a blade, a transmitter, a target with parallel edges located on the blade shroud and a receiver. The present invention also provides a blade adapted for measuring torsional blade vibration. Furthermore, the claimed invention provides a method for monitoring torsional blade vibration.

Abstract: Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Abstract: A system (10) for imaging a rotating turbine blade (20) includes an image projector (12) receiving a moving image of the rotating blade and projecting a movement-compensated image. The system also includes an image receptor (14) for receiving the movement-compensated image. A sensor (16) is provided for generating information (28) indicative of a velocity of the rotating turbine blade and a processor (18) generates a drive signal (30) responsive to the information for controlling a position of the image projector. The image projector is controlled to receive the moving image at a desired angular position and to project the movement-compensated image to the image receptor so that the movement-compensated image appears stationary relative to the image receptor.

Abstract: An optical inspection system is for visually inspecting the blades of a turbine at turning gear operation. The inspection system includes an imager for capturing images of the blades, an optical passage coupled to the imager and structured to provide maximum viewing area of the blades through an inspection port in the turbine and an illuminating assembly adapted to illuminate the blades while the imager captures images thereof. A method wherein the captured blade images are inspected for blade defects, is also disclosed.

Abstract: The present invention provides a flange-mounted condition monitor (30) that can be mounted to an access flange (21) on an access opening (20) on the housing (13) of a generator (10). The condition monitor (30) forms an integral part of the generator (10) and eliminates the need for complex systems of pipes and valves for transferring hydrogen samples from the generator (10) to the condition monitor (30). The flange-mounted condition monitor (30) provides greater sensitivity to overheat conditions, significantly reducing the risk of dangerous hydrogen leaks and eliminating costs associated with installing and maintaining a remote condition monitor and also reducing or eliminating the false alarms associated with water that collects in the piping of a remote condition monitor.

Abstract: A system (10) for imaging a combustion turbine engine airfoil includes a camera (12) and a positioner (24). The positioner may be controlled to dispose the camera within an inner turbine casing of the engine at a first position for acquiring a first image. The camera may then be moved to a second position for acquiring a second image. A storage device (30) stores the first and second images, and a processor (32) accesses the storage device to generate a composite image from the first and second images. For use when the airfoil is rotating, the system may also include a sensor (40) for generating a position signal (41) responsive to a detected angular position of an airfoil. The system may further include a trigger device (42), responsive to the position signal, for triggering the camera to acquire an image when the airfoil is proximate the camera.

Abstract: The claimed invention provides a blade vibration measuring system comprising a blade, a transmitter, a target with non parallel edges located on the blade shroud and a receiver. The present invention also provides a blade adapted for measuring blade vibration. Furthermore, the claimed invention provides a method for monitoring blade vibration.

Abstract: A system (10) for imaging a rotating turbine blade (20) includes an image projector (12) receiving a moving image of the rotating blade and projecting a movement-compensated image. The system also includes an image receptor (14) for receiving the movement-compensated image. A sensor (16) is provided for generating information (28) indicative of a velocity of the rotating turbine blade and a processor (18) generates a drive signal (30) responsive to the information for controlling a position of the image projector. The image projector is controlled to receive the moving image at a desired angular position and to project the movement-compensated image to the image receptor so that the movement-compensated image appears stationary relative to the image receptor.

Abstract: A measurement device for measuring the wear of turbo-machine components to reduce the likelihood of component failure while a turbine-machine is at load. The measurement device is capable of measuring and calculating a distance between surfaces while the turbo-machine is at load. The distance may be compared with a measurement taken of the same location at another time to determine wear of a surface remote from the location of the measurement. The measurement device may be configured such that multiple measurements may be made on a single turbine engine by moving the measurement device from location to location.

Abstract: A system (90) for measuring the gap (16) between a rotating blade (14) and a stationary component (12) of a turbo-machine, including an eddy current coil (30) and an eddy current tester (91). The eddy current tester may excite the coil in a pulsed eddy current testing mode. The coil is positioned in a stationary portion (12) of a turbo-machine traversed by a rotating blade and the eddy current tester is coupled to the eddy current coil to provide an indication responsive to a distance between the blade and the stationary portion as the blade traverses the position. The coil may be mounted in a frangible ceramic pill (70) movably disposed in a housing (74). The coil is positioned near the turbine blade, the coil is excited with a voltage step function (120), and the response (122) of the coil to the step function is detected and processed to determine the proximity of the blade.

Abstract: A system (10) for imaging a combustion turbine engine airfoil includes a camera (12) and a positioner (24). The positioner may be controlled to dispose the camera within an inner turbine casing of the engine at a first position for acquiring a first image. The camera may then be moved to a second position for acquiring a second image. A storage device (30) stores the first and second images, and a processor (32) accesses the storage device to generate a composite image from the first and second images. For use when the airfoil is rotating, the system may also include a sensor (40) for generating a position signal (41) responsive to a detected angular position of an airfoil. The system may further include a trigger device (42), responsive to the position signal, for triggering the camera to acquire an image when the airfoil is proximate the camera.

Abstract: The present invention provides a configuration where all optical parts of a monitoring system are contained within a seal and within the generator itself. Non-optical preamplifier functions may also be placed within the seal. In this configuration there is an electrical rather than optical feed-through at the generator wall, which is hermetically sealed, unlike a fiber optic feed-through. The fiber optic light source and detector for each sensor is located in the seal on the generator side of the hermetic electrical feed-through. Electrical power and the sensor's converted electrical vibration signals pass through the electrical feed-through to preamplifier circuitry on the outside of the seal where direct electrical connection is then made to a main chassis unit.

Abstract: The present invention provides a configuration where all optical parts of a monitoring system are contained within a seal and within the generator itself. Non-optical preamplifier functions may also be placed within the seal. In this configuration there is an electrical rather than optical feed-through at the generator wall, which is hermetically sealed, unlike a fiber optic feed-through. The fiber optic light source and detector for each sensor is located in the seal on the generator side of the hermetic electrical feed-through. Electrical power and the sensor's converted electrical vibration signals pass through the electrical feed-through to preamplifier circuitry on the outside of the seal where direct electrical connection is then made to a main chassis unit.

Abstract: The present invention provides a flange-mounted condition monitor (30) that can be mounted to an access flange (21) on an access opening (20) on the housing (13) of a generator (10). The condition monitor (30) forms an integral part of the generator (10) and eliminates the need for complex systems of pipes and valves for transferring hydrogen samples from the generator (10) to the condition monitor (30). The flange-mounted condition monitor (30) provides greater sensitivity to overheat conditions, significantly reducing the risk of dangerous hydrogen leaks and eliminating costs associated with installing and maintaining a remote condition monitor and also reducing or eliminating the false alarms associated with water that collects in the piping of a remote condition monitor.