Turbine servicing device

A turbine servicing device includes a base member mountable proximate an inlet of a section of a turbine system. Also included is a retaining component operatively coupled to the base member. Further included is a rod having a first end and a second end, the rod in a slidable and pivotable relationship with the retaining component. Yet further included is a machining device operatively coupled to the rod proximate the second end and configured to polish a portion of a turbine component.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to turbine systems, and more particularly to a turbine servicing device, as well as a method of servicing a turbine system.

During operation of a section of a turbine system, components within that turbine system, such as rotor blades and stator vanes, typically are subjected to harsh operating conditions which may damage those components. In order to service components such as these, disassembly of at least a portion of the turbine system is required. Currently, in the case of servicing components within a compressor section, for example, a top half of a compressor case is removed to provide access to the components in need of service. Unfortunately, disassembly and subsequent reassembly is both costly and time consuming. Attempts to service these components without disassembly are typically limited by spatial constraints and repair device capabilities.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of the invention, a turbine servicing device includes a base member mountable proximate an inlet of a section of a turbine system. Also included is a retaining component operatively coupled to the base member. Further included is a rod having a first end and a second end, the rod in a slidable and pivotable relationship with the retaining component. Yet further included is a machining device operatively coupled to the rod proximate the second end and configured to polish a portion of a turbine component.

According to another aspect of the invention, a method of servicing a turbine is provided. The method includes mounting a base member of a turbine servicing device proximate an inlet of a section of a turbine system. The method also includes extending a rod into the section of the turbine system, wherein the rod is controllably retained in a sliding a pivotable manner by a retaining component operatively coupled to the base member. The method further includes polishing a portion of a turbine component disposed within the section of the turbine system with a machining device operatively coupled to the rod.

DETAILED DESCRIPTION OF THE INVENTION

Referring toFIG. 1, a turbine system is schematically illustrated and generally referred to with numeral10. The turbine system10, in the case of a gas turbine system, includes a compressor section12, a combustor section14, a turbine section16, a shaft18and a fuel nozzle20. It is to be appreciated that one embodiment of the gas turbine system10may include a plurality of compressor sections12, combustor sections14, turbine sections16, shafts18and fuel nozzles20. The compressor section12and the turbine section16are coupled by the shaft18. The shaft18may be a single shaft or a plurality of shaft segments coupled together to form the shaft18.

Referring now toFIG. 2, a partial, cut-away view illustrates an inlet22of the compressor section12. Although illustrated and described herein as a compressor of a gas turbine system, it is to be understood that the embodiments described herein can be applied to steam turbine systems as well and to other sections of the turbine system10. The inlet22generally refers to a region configured to route an incoming airflow to the compressor section12and comprises a compressor bell mouth24. Half of the compressor bell mouth24has been removed to illustrate various vanes and blades disposed at an interior region of the compressor section12, relative to a compressor section casing26. The compressor bell mouth24includes an outer surface28and an inner surface30, with the incoming airflow passing between these two surfaces. Typically, a plurality of support members32are operatively coupled to the outer surface28and the inner surface30for support.

Referring toFIG. 3, a plurality of inlet guide vanes (IGVs)34are arranged in a circumferentially spaced manner in what is referred to as a stage. Downstream of one or more stages of the plurality of IGVs34are a plurality of rotor blades and a plurality of stator vanes. The stator vanes are generally fixed to a stator or a compressor section casing26, while the rotor blades are connected to the shaft18. The plurality of IGVs34is generally fixed as well, but may pitch around a radial axis to vary the direction or amount of incoming flow. The plurality of IGVs34is followed by a first stage of rotor blades36, which is in turn followed by a first stage of stator vanes38. Disposed downstream of the first stage of stator vanes38is a second stage of rotor blades40, which is followed by a second stage of stator vanes42. It can be appreciated that the compressor section12may include varying numbers of stages of rotor blades and stator vanes, depending on the particular application.

Referring now toFIGS. 4 and 5, in conjunction withFIGS. 2 and 3, a turbine servicing device50is illustrated. The turbine servicing device50includes a base member52removably mountable to the inlet22of the compressor section12directly or proximate to the inlet22. The inlet22, and more particularly the compressor bell mouth24, is typically formed of a metallic material. In one embodiment, the base member52comprises a magnetic material for magnetically attaching the base member52to the metallic material of the inlet22. It is contemplated that the turbine servicing device50comprises more than one base member configured to mount to the inlet22.

Operatively coupled to, or integrally formed with, the base member52is a platform54comprising at least one, but typically a plurality of apertures56for receiving a mechanical fastener for operatively coupling a retaining component58to the base member52. The plurality of apertures56provides positioning adjustability of the retaining component58. The retaining component58includes an opening60, typically in the form of a cylindrical opening for receiving a rod62therein. The rod62typically comprises a cylindrical geometry as well, however, it is contemplated that the opening60and the rod62comprise alternative geometries. Irrespective of the precise geometry of the opening60and the rod62, it is to be appreciated that the geometries of the opening60and the rod62substantially correspond to each other, such that the rod62is slidable within the opening60. In addition to a slidable relationship with the retaining component58, the rod62is pivotable, with respect to the base member52, as the retaining component58comprises a spherical bearing joint. The advantages of the slidable and pivotable nature of the rod62will be described in greater detail below.

The rod62includes a first end64, a second end68and a body portion70therebetween. Operatively coupled proximate the first end64of the rod62is a handle72configured to allow a user, such as a human operator, to interact with the rod62. In the case of a human operator, the user is able to grasp the handle72with a hand to control the rod62. The handle72effectively forms a joint between a human operator's hand and the rod62, which is of a rigid nature. The handle72may be shaped in numerous configurations and in the illustrated embodiment the handle72comprises a bulb-shaped member. Although described above as being controlled by a human operator, it is contemplated that an alternative control mechanism may be employed to control the turbine servicing device50, and more specifically the rod62. Irrespective of the precise control mechanism or user, the retaining component58is configured to provide unrestricted freedom of motion of the second end68of the rod62. Rather than merely allowing for a finite number of degrees of freedom of movement of the second end68of the rod62, the spherical bearing joint allows the second end68to pivot in an unrestricted manner. Additionally, the rod62is free to slide within the opening60along the body portion70of the rod62. It is to be appreciated that the sliding and pivoting movements may be performed simultaneously and in combination provide advantageous flexibility of movement of the second end68.

Operatively coupled proximate the second end68of the rod62is a machining device74configured to polish a portion of a turbine component, such as one of the plurality of rotor blades or stator vanes described above. In an exemplary embodiment, the machining device74comprises an air grinder configured to remove rolled material that has accumulated as a result of normal operation of the turbine component. The machining device74typically includes one or more attachment features, such as flapper disks and abrasive polishing pads. The attachment features are interchangeable to provide machining flexibility based on the component requiring servicing and the precise polishing to be conducted. It is to be appreciated that the polishing of the turbine component may be performed in various manners, including in an oscillating or rotational manner, for example. As employed herein, the term “polish” refers to smoothing a workpiece's surface to provide a relatively flat, continuous and defect-free surface. As described above, the machining device74is configured to provide such a surface that lacks a rough, unfinished surface.

In addition to the grinding or polishing device itself, it is contemplated that the turbine servicing device50may include additional components integral to, or located proximate to, the machining device74. Such components may include an optical device such as a boroscope that may be remotely located to monitor the servicing process. The boroscope may be fitted with an imaging or video device to identify regions in need of servicing. The imaging device may be a visual or infrared camera, a non-visual (e.g., X-ray, microwave, or eddy current) imaging device, or an ultrasonic imaging device. Additionally, multiple imaging devices may be deployed to provide a stereoscopic or 3D view of the desired area or to view various portions of the serviced region from various angles. A marking device is also contemplated to provide a user with markings that would enhance visual targets for the user. One or more light sources may also be included to aid in the inspection, marking and/or repair process. A distance measuring system can also be used to aid with the servicing process and with validation of servicing. Additionally, it is contemplated that a debris removal system, such as a vacuum, is included to facilitate removal of debris or particulate matter caused during the servicing process.

In operation, the base member52is secured proximate to the inlet22and at least a portion of the rod62, and more specifically the machining device74, is inserted into the compressor section12in a predominantly axial direction of the turbine system10. The machining device74is inserted through at least one stage of the plurality of IGVs34to reach the turbine component to be serviced, such as a rotor blade or stator vane located in one of the stages of the compressor section12. Navigating through the plurality of IGVs34and additional turbine components to reach and service the desired region is challenging based on tight spatial constraints, but the unrestricted degrees of freedom that the second end68of the rod62comprises allows a user to maneuver through such components and effectively service the component. It is contemplated that a user may insert an entire length of the rod62, including the handle72, into the compressor section12.

Referring to the flow diagram ofFIG. 6, in conjunction withFIGS. 1-5, a method of servicing a turbine100is provided. The turbine system10and more specifically the turbine servicing device50have been previously described and specific structural components need not be described in further detail. The method of servicing a turbine100includes mounting102a base member of the turbine servicing device proximate an inlet of a section of a turbine system. The method also includes extending104a rod into the section of the turbine system, where the rod is controllably retained in a sliding and pivotable manner by a retaining component operatively coupled to the base member. A portion of the turbine component is polished106with a machining device operatively coupled to the rod.