Siemens Energy, Inc.

Siemens Power Generation, Inc.

James P Williams

Clifford Hatcher

Joshua DeAscanis

Forrest R Ruhge

Dennis H Lemieux

Robert G Shannon

Jan P Smed

David W Fox

Vinay Jonnalagadda

Ramesh Subramanian

Anand A Kulkarni

Paul John Zombo

David J Mitchell

Cora Schillig

Edward R Roesch

David Letter

Mahmood K Silieti

David J Meek

Alejandro Bancalari

Sankar Nellian

Bulent Acar

Turbine blade-tip clearance is measured in a fully assembled turbine casing by mounting a probe tip of a non-contact displacement probe in an inspection port of a vane cavity at a known distance relative to the inner circumferential surface of the corresponding ring segment. The displacement probe generates displacement samples that are indicative of probe tip distance from the turbine blade tip. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing. A data processing system correlates the distance data with localized blade-tip clearance gap. In some embodiments, blade rotational position data are collected by a rotational position sensor. In those embodiments, the data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference.

Contactless, blade-tip clearance measurement for turbines

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

Fastener-removal method and assembly including a washer member () integral with a fastener-removal member () are provided. A fastener () may be disposed in a through hole () in the washer member. The fastener-removal member is arranged to receive a mechanical force effective to remove the fastener. Embodiments of the disclosed assembly are effective for quick removal of relatively high-strength fasteners, as may be used in combustion turbine engines, without having to directly apply torque to structures of the fastener, such as the head of a fastener, and thus reducing the possibility of damage to the fastener during servicing operations of the turbine engine involving fastener removal.

Fastener-removal method and assembly including a fastener-removal member integrally constructed with a washer member

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

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

A method and a system for inspection of gas turbine are presented. An inspection tool is attached on a track which is permanently positioned on site with respect to the gas turbine. The inspection tool includes an extendible shaft with a proximal end attached on the track and a distal end carrying a sensor. The inspection tool moves along the track for accessing an inspection port of the gas turbine by the shaft. A control system is coupled to the inspection tool for controlling the inspection tool for the inspection of the gas turbine. The method and system enable an automated engine inspection which allows for the engine to have been inspected and reviewed by an engineer without having to send the engineer on site.

Gas turbine inspection apparatus and method and system for inspecting a gas turbine

An optical probe () includes an inner tube (), and a light-redirecting element () disposed at a distal end () of the inner tube. The light-redirecting element is supported at the distal end by an affixing structure () not attached to an optically-working surface () of the light-redirecting element.

Optical probe with improved affixing structure for supporting a light-redirecting element

A standardized inspection port system with common inspection port bodies and port plugs are incorporated in plural inspection locations within a gas turbine engine casing to facilitate internal engine inspection. The inspection ports preferably have identical internal diameter, stub flange dimensions and axial length from the gas turbine casing inspection seat to the stub flange for standardized mounting of inspection instruments at different locations about the turbine. The inspection port system components are preferably axially and radially aligned along the turbine casing for establishing a common reference position along all turbine blade/vane rows. The port plug incorporates a magnetically attractive pole piece for concentration or redirection of an attractive magnetic field circuit generated by an inspection port plug service tool during plug insertion or retrieval. Magnetic attraction to a service tool enhances controlled plug guidance and reduces likelihood of inadvertent plug loss within the turbine casing.

Standardized gas turbine inspection port system

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

An optical probe () including one or more optical elements (), and an inner tube () to house the optical elements. The inner tube may be made up of at least two cooperating inner tube sections () separable from one another along a longitudinal axis of the inner tube.

Optical probe having an inner tube with separable tube sections to house optical elements

In an optical probe () having an inner tube () arranged to house one or more optical elements (), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections () separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections () are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.

Methods regarding optical probe having an inner tube with separable tube sections to house optical elements

A telemetry system for use in a combustion turbine engine () having a compressor (), a combustor and a turbine () and includes a sensor () in connection with a turbine blade () or vane (). A transmitter assembly () includes a telemetry transmitter circuit/transceiver may be affixed on a turbine blade () or seal plate () proximate the turbine blade with a first connecting material () deposited on the turbine blade () for routing electronic data signals, indicative of a condition of the turbine blade (), from the sensor () to the telemetry transmitter circuit/transceiver. An induction power system for powering the telemetry transmitter circuit/transceiver may include a rotating data antenna () affixed to the seal plate () with an electrical connection () between the telemetry transmitting circuit/transceiver for routing electronic data signals from the telemetry transmitter circuit/transceiver to the rotating data antenna ().

Wireless telemetry system for a turbine engine

The monitoring system for a gas turbine engine including a viewing tube assembly having an inner end and an outer end. The inner end is located adjacent to a hot gas flow path within the gas turbine engine and the outer end is located adjacent to an outer casing of the gas turbine engine. An aperture wall is located at the inner end of the viewing tube assembly and an optical element is located within the viewing tube assembly adjacent to the inner end and is spaced from the aperture wall to define a cooling and purge chamber therebetween. An aperture is defined in the aperture wall for passage of light from the hot gas flow path to the optical element. Swirl passages are defined in the viewing tube assembly between the aperture wall and the optical element for passage of cooling air from a location outside the viewing tube assembly into the chamber, wherein swirl passages effect a swirling movement of air in a circumferential direction within the chamber.

Optical monitoring system for a turbine engine

An inspection system formed at least from a viewing tube for inspecting aspects of a turbine engine during operation of the turbine engine. An outer housing of the viewing tube may be positioned within a turbine engine using at least one bearing configured to fit into an indentation of a support housing to form a ball and socket joint enabling the viewing tube to move during operation as a result of vibrations and other movements. The viewing tube may also include one or more lenses positioned within the viewing tube for viewing the turbine components. The lenses may be kept free of contamination by maintaining a higher pressure in the viewing tube than a pressure outside of the viewing tube and enabling gases to pass through an aperture in a cap at a viewing end of the viewing tube.

Growing community of inventors

Orlando, FL, United States of America

James P Williams