Siemens Energy, Inc.

Siemens Corporation

Forrest R Ruhge

Clifford Hatcher

Joshua DeAscanis

Robert G Shannon

James P Williams

Yakup Genc

Richard Michael Hatley

Dennis H Lemieux

Himanshu Bhatnagar

David Letter

Alejandro Bancalari

David J Meek

John E Junkin

Mark L Kamphaus

William D Clark

Ian T Doran

Jr Clifford Hatcher

A system for performing acoustic thermography inspection of a turbine blade while the blade is in place in an assembled turbine. The system includes an acoustic thermography stack with a cap and a frame that the acoustic thermography stack is slidably mounted to, said frame including an end frame portion that allows the blade to be clamped between the cap and the end frame portion. The system also includes an air cylinder that provides force to move the acoustic thermography stack up and down a rail of the frame such that the turbine blade may be clamped between the cap and the end frame portion and then excited using the acoustic thermography stack, and a casing that encases the air cylinder, a portion of the acoustic thermography stack and a portion of the frame.

Portable acoustic thermography of in situ L-O blades

A laser measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one laser device for emitting a laser beam that impinges on a blade surface of each blade in a row of blade assemblies. The laser beam is also transmitted through a space between adjacent blades to impinge on corresponding internal surfaces of the gas turbine. Further, the system includes a photon detector for detecting a first time period in which first laser energy is reflected from each blade surface and a second time period in which second laser energy is reflected from each internal surface and transmitted through each space. The system also includes a controller for detecting a change in at least one second time period to indicate that a distance between consecutive blades has changed and that at least one locked blade assembly is locked.

Laser measurement system for detecting turbine blade lockup

Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency.

System and method for controlling ice formation on gas turbine inlet guide vanes

An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies. The system also includes a video device for imaging the blades as the blades rotate about the center axis. Further, the system includes a controller for controlling operation of the light source and video device. The controller detects a pixel intensity associated with each blade and a spacing between each pixel intensity wherein a change in spacing between consecutive pixel intensities indicates that a distance between consecutive blades has changed relative to the first distance thereby indicating at least one locked blade assembly.

Optical measurement system for detecting turbine blade lockup

Non-destructive evaluation optical inspection systems include video cameras or other reflective-photonic optical instruments, such as laser profilometers or 3D white light laser dimensional scanners, which are incorporated in a camera head. The camera head is coupled to a distal end of a self-supporting and shape-retaining elongate deformable deployment tether. The deployment tether is bendable, for insertion through cavities of power generation machines and orientation of the camera head field of view on the internal area of interest. The deployment tether is capable of being deformed repeatedly, for inspection of different areas of interest. In some embodiments, interchangeable camera heads are selectively coupled to the deployment tether, so that a kit or family of different optical inspection instruments are available to carry out multiple types of inspections within a single or multiple types of power generation machinery.

Video inspection system with deformable, self-supporting deployment tether

A system and method include an acoustic thermography stack and a frame that the stack is slidably mounted to. The frame includes an end frame portion with a blade stop, and an air cylinder provides force to move the stack up and down a rail of the frame such that a turbine blade may be clamped between a cap of the stack and the blade stop. The clamped blade is excited using the stack, and an infrared camera is used to detect critical indications in the blade.

Hardware and method for implementation of in situ acoustic thermograph inspections

A camera scope inspection system with a flexible, tether mounted camera head that is maneuverable in confined internal cavities of power generation machinery. A camera head position sensing system inferentially determines the three dimension (3D) position of the camera head within the inspected machinery. Camera head position data are correlated with camera image data by a controller. In this manner correlated internal inspection image data and corresponding position data are available for future analysis and image tracking.

Flexible tether position tracking camera inspection system for visual inspection of off line industrial gas turbines and other power generation machinery

Turbine engine rotor corresponding thru-bolts and disc cavities are inspected with a camera inspection system that includes one or both of a thru-bolt male threads inspection apparatus and a rotor disc cavity inspection apparatus. The disc cavity inspection scope apparatus is insertable in one or more of the desired rotor disc cavities and orients an attached inspection camera field of view generally transverse to the circumferential wall in the rotor disc that defines the cavity. Preferably inspection scope apparatus insertion into the disc cavities is performed with a motion control system that monitors spatial position of the camera field of view relative to the recess circumferential wall. The plural camera cavity circumferential wall images are desirably combined to form a composite image of a desired portion of or the entire disc cavity circumferential surface, which aids their inspection evaluation and provides an archived composite image of the surface.

Method for inspecting a turbine engine rotor with a rotor disc cavity inspection apparatus

An acoustic measurement system for detecting locked blade assemblies in a gas turbine having a plurality of blade assemblies. The system includes at least one acoustic sensor for detecting acoustic energy generated as a result of movement of the blade assemblies during a turning gear operation. In addition, the system includes a housing for holding the acoustic sensor, wherein the housing is mounted to an outer diffuser of the gas turbine. The housing also includes a rotatable joint for enabling rotation of the acoustic sensor. Further, the system includes a data acquisition unit that detects an absence of acoustic energy wherein the absence of acoustic energy is indicative of locked blade assemblies. The blade assemblies are locked due to wedging of a sealing pin between the blade assemblies. The acoustic energy is detected in a frequency range of approximately 0.9 kHz to 10 kHz.

Acoustic measurement system for detecting turbine blade lockup

A method of generating a comprehensive image () of interior surfaces () of machine components such as a gas turbine combustor basket () and transition duct () by digitally stitching together multiple photographs () thereof, and analyzing the comprehensive image by contouring (A-B) of colors and shadings thereon, and quantifying and tracking aspects of the contours (A, B, C) over time for indications of degradation () of the interior surfaces. A scope () may be inserted into a port () in the combustor with a camera () in a rotatable end () of the scope for obtaining a circumferential set () of photos at each axial position along a length of the combustor and transition duct. A 3D surface scanning device () in the scope may define the geometry of the interior surface for 3D photographic modeling thereof providing a virtual walk-through inspection.

Internal inspection of machinery by stitched surface imaging

Turbine engine casing interiors are visually inspected in a fully assembled turbine casing by mounting an optical camera on a turbine blade that captures optical images, such as of the casing abradable surface. Optical images are recorded as the blade circumferentially sweeps the turbine casing when the turbine is operated in turning gear mode or manually rotated. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the captured optical images and rotational position data about the turbine casing circumference. This method and apparatus provide an accurate and cost effective solution for accessing a turbine casing interior.

In-situ blade-mounted optical camera inspected systems for turbine engines

Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a contact or non-contact displacement probe on a turbine blade that generates data indicative of probe distance from the turbine casing that circumferentially surrounds the blade. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. An optical camera inspection system may be coupled to a turbine blade to obtain visual inspection information within the turbine casing. This method and apparatus provide an accurate and cost effective solution for accessing turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

Situ blade mounted tip gap measurement for turbines

Turbine engine rotor corresponding thru-bolts and disc cavities are inspected with a camera inspection system that includes one or both of a thru-bolt male threads inspection apparatus and a rotor disc cavity inspection apparatus. The thru-bolts threads inspection apparatus engages the male threads and advances along the bolt threads pattern, selectively capturing camera images at desired spatial positions along the threads pattern. The plural camera threads images are desirably combined to form a composite image of a desired portion of or the entire thru-bolt male threads profiles, which aids their inspection evaluation and provides an archived composite image of the profiles.

Method for inspecting a turbine engine rotor with a thru bolt threads inspection apparatus

A method of inspecting a component located on a rotor rotating about an axis internal to a turbine. An elongated probe is provided defining a probe length and having a one-dimensional pixel array formed by a plurality of pixels extending single file along the probe length. The probe is positioned through an access port in a casing of the turbine. The rotor is rotated to move the component past the pixel array, and energy emitted from an image area defined by a line extending along the component is received at the pixel array. An intensity-based signal from each pixel in the pixel array is conveyed to a processor to convert the intensity-based signals to an intensity-based line image, and a succession of the intensity-based line images are converted into a cohesive two-dimensional digital image of the component.

Linear array to image rotating turbine components

An on-line optical inspection and monitoring system is externally mounted to existing man way service access within the combustor housing. A replacement man way cover having an optical window is mounted to the combustor housing. One or more optical cameras are oriented so that the camera field of view (FOV) is directed through the man way cover optical window. The camera FOV is moved to plural positions within the combustion section, such as under control of an automated motion control system, and images are captured. Multiple images are combined to form a composite image, which may include an image of an entire transition within the combustion section. Visual images and/or infrared (IR) thermal images may be captured. Thermal image information is correlated with component temperature. Image information is utilized to determine vibration characteristics of the imaged components.

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Orlando, FL, United States of America

Forrest R Ruhge