CN103180700B - For monitoring the system of the high-temperature area paid close attention in turbogenerator - Google Patents
For monitoring the system of the high-temperature area paid close attention in turbogenerator Download PDFInfo
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- CN103180700B CN103180700B CN201180050604.1A CN201180050604A CN103180700B CN 103180700 B CN103180700 B CN 103180700B CN 201180050604 A CN201180050604 A CN 201180050604A CN 103180700 B CN103180700 B CN 103180700B
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Abstract
One is provided to be used for monitoring the system (8) of the high-temperature area paid close attention in turbogenerator (10).This system includes that the inner-cooled being arranged in the path of the working gas of turbine fixes machine leaf (12).Monitoring mouth (14) it is provided with in fixing machine leaf.Monitoring instrument (16) is operatively connectable to the monitoring mouth of fixing machine leaf to provide the visual field of interest region.
Description
This application claims priority from U.S. provisional patent application No.61/405377, filed on 21/10/2010, which is incorporated herein by reference. The present application is related to U.S. patent application No.13/274766 (attorney docket No. 2011P23076 US) entitled "METHOD FOR MONITORING a HIGH TEMPERATURE region of interest in a TURBINE ENGINE," filed concurrently with the present application and incorporated herein by reference.
Technical Field
Aspects of the present invention relate to turbine engines and, more particularly, to a system for monitoring a high temperature region of interest, such as may be performed with monitoring instruments disposed within the interior of stationary blades of a turbine.
Background
The assignee of the present invention has successfully demonstrated an apparatus and technique for online monitoring of rotating and/or stationary components of a turbine engine. See, For example, the apparatus and techniques described in U.S. patent 7690840 entitled "Method and apparatus For Measuring on-line Failure Of Turbine Thermal barrier components," the entire contents Of which are incorporated herein by reference.
In view of the geometric and thermal constraints that may arise in the context of limited access space in a turbine engine, the thermal and/or spatial view provided by known devices is generally limited to regions located radially inward relative to the cylindrical structure of the turbine. For example, obtaining thermal and/or spatial observations of radially outwardly located regions has not been possible or is greatly limited in size and/or angle of incidence.
In addition, because known devices are disposed in areas spaced from the high temperatures and/or pressures typically present in the path of the working gas of the turbine, such devices involve relatively long optical paths, which typically require relatively more optical elements (e.g., relay optics). Long optical paths may force designers to use optical elements that involve optical compromises that may be needed in the context of such long optical paths, e.g., may involve the use of optical elements with lower reflective characteristics. For example, optical elements with higher reflection characteristics may not be suitable in long optical paths involving a large number of such elements, but may be suitable in short optical paths involving a smaller number of optical elements. These considerations may somewhat impair the ability of the designer to customize the optical design to address other tradeoffs, for example, impairing the ability of the designer to use more rugged optical materials that may have higher reflection characteristics.
Accordingly, in view of the foregoing considerations, there is also a need for improved apparatus and/or techniques that may be used to monitor high temperature regions of interest in turbine engines.
Drawings
Aspects of the invention are explained in the following description with reference to the following drawings:
FIG. 1 partially illustrates a schematic diagram of an exemplary embodiment of a system that may be used to monitor a high temperature region of interest in a turbine engine, according to aspects of the present technique.
Fig. 2-4 depict respective cross-sectional views of various exemplary embodiments of stationary vanes including monitoring instruments (scopes) operatively connected to viewing ports of the stationary vanes to provide a field of view of a region of interest, in accordance with aspects of the present invention.
FIG. 5 is a cross-sectional view of an exemplary embodiment of a shroud assembly that may be connected to secure a viewing instrument in a vane.
FIG. 6 is a cross-sectional view of an exemplary embodiment of a twist-lock assembly that may be connected to secure a scope in a leaf.
FIG. 7 is a cross-sectional view of an exemplary embodiment of a scope that may be made, for example, from a fiber optic bundle.
Detailed Description
FIG. 1 partially depicts a schematic diagram of an exemplary embodiment of a system 8 that may be used for online monitoring of a high temperature region of interest 20 in a turbine generator 10, the system 8 may be used in land, marine, or aerospace applications. Those skilled in the art will appreciate that the turbine 10 may include a plurality of internally cooled (e.g., air cooled) stationary blades that may be disposed in the path of the working gas of the turbine, and that the stationary blades are therefore subjected to relatively high temperatures, e.g., temperatures on the order of thousands of degrees Fahrenheit, such as temperatures of about 2800 degrees Fahrenheit or higher.
According to aspects of the present disclosure, the blade 12 may be configured to include a monitoring port 141And houses a monitoring instrument 16 therein, the monitoring instrument 16 being operatively connected to the monitoring port 141For example, to provide a field of view 18 away from a region of interest 20 of the blade 12. It is to be appreciated that aspects of the present invention are not limited to a single monitoring port 14 configured in the blade 121. For example, as monitoring port 142And 143May be configured in the blade 12 to provide a field of view away from other areas of interest of the blade 12, respectively. Exemplary turbine components that may be disposed in the area of interest 20 may include stationary ring segments (not shown) disposed by tips of corresponding rotating blades (not shown). As can be appreciated by those skilled in the art, Thermal Barrier Coatings (TBC) on these ring segments can experience accelerated wear and scuffing because they are subjected to high velocity, high temperature gases under high pressure conditions and/or hard contact with the blade tip.
In an exemplary embodiment, the system 8 includes a data acquisition device 22, the data acquisition device 22 being coupled to the monitoring instrument 16 for acquiring data from the area of interest. In one exemplary embodiment, the data acquisition device 22 may be an Infrared (IR) imaging device, such as an IR camera, coupled to the monitoring instrument 16 to acquire imaging data of the area of interest. In an exemplary embodiment, the processor 23 may be operatively coupled to process imaging data from the IR imaging device 22 to generate an image (spatial and/or thermal image) of the region of interest. For the reader who wants to obtain full background information about exemplary techniques for processing imaging data from an IR camera, reference is made to us patent 7690840. It will be appreciated that the monitoring instrument 16, the data acquisition device 22, and the processor 23 need not be limited to monitoring, acquisition, and processing of imaging data, respectively, as it is contemplated that the monitoring instrument 16, the data acquisition device 22, and the processor 23 may alternatively be adapted (e.g., based on the needs of a given application) for monitoring, acquisition, and processing of non-imaging data, which may include pyrometry data, spectroscopy data, chemical composition data, vibrational data, acoustic data, optical data, and the like, for example. The following exemplary description focuses on an exemplary imaging application, and the monitoring instrument 16 may be referred to as a scope. However, as noted above, such exemplary illustrations should not be construed in a limiting sense.
In one exemplary embodiment, the IR camera 22 may have a visual axis 24 that generally faces away from the region of interest 20. For example, the visual axis 24 may face radially inward with respect to the axis of rotation of the turbine, which facilitates monitoring a region radially inward of the turbine, but may not be implemented to monitor a region outward of the turbine, such as region 20. Accordingly, in accordance with aspects of the present invention, the viewing instrument 16 may be configured with a prism or mirror assembly suitably positioned to provide a reverse view (e.g., obliquely facing away) in a radially inward direction with respect to the visual axis 24 of the IR camera so that the region of interest 20 falls within the visual axis of the IR camera. It will be appreciated that the viewing instrument 16 may be adapted to a repositionable inner blade 12, e.g., an inner blade rotatable about an axis 24 and/or radially movable along the axis 24, to monitor alternative regions of interest, e.g., via the monitoring port 141、142And 143The process is carried out.
In one exemplary application, the monitoring instrument 16 may be configured to measure and/or observe various chemical and/or physical indicators, such as may be obtained from a region of interest, which may be located upstream of the first row of blades, such as may provide a view toward the combustion chamber. These indicators may be used to determine characteristics of the combustion flow. Exemplary indicators may be flow characteristics, chemical composition, chemical reaction kinetics, and the like. Another exemplary application where a system embodying aspects of the present invention may be feasible may be the monitoring of tip clearance.
It will be appreciated that data acquired from two or more monitoring instruments may be processed to generate stereo (e.g., parallax) or 3D measurements or imaging from a region of interest, e.g., imaging data from the dual viewing instrument 16 may be used for stereo imaging of the region of interest.
It will be appreciated that in one exemplary embodiment, such dual scopes may be arranged in close proximity to one another (conceptually similar to the side-by-side range of binoculars) and may provide partially overlapping fields of view of the regions of interest. It will be appreciated that two or more scopes need not be arranged in close proximity to one another. For example, two or more scopes may be arranged at precisely predetermined spaced-apart locations to provide different perspectives of a given area of interest, which may then be processed to generate stereoscopic or 3D measurements or imaging of the area of interest.
As can be appreciated from FIG. 1, in an exemplary embodiment, the IR camera 22 may be disposed within a plenum 26 defined by an inner casing 28 and an outer casing 30 of the turbine. In the exemplary embodiment, since the temperature in plenum 26, although much cooler than the region in which the high temperature working gas operates, may still be several hundred degrees Fahrenheit, for example about 850 degrees Fahrenheit or higher, IR camera 22 may include a water cooling system 32. It will be appreciated that the IR imaging device 22 need not be disposed in the plenum 26, as the IR imaging device 22 may be disposed in other areas, for example, outside of the turbine's casing 30, which may avoid the need for a water cooling system 32.
Those skilled in the art will appreciate that the viewing instrument 16 may be fixedly attached within the interior of the chassis 12 using any of a variety of exemplary mounting arrangements. For example, fig. 2 depicts a cross-sectional view of the blade 12, and the blade 12 may include a guide tube 33 configured to receive the distal end of the scope 16. Fig. 3 depicts another exemplary means for securing the viewing instrument 16, wherein the blade 12 includes a bracket 34, the bracket 34 being connected to a proximal end of the blade 12 to support a funnel 36, the funnel 36 being used to receive the viewing instrument 16 into the blade 12. As shown in FIG. 3, the viewing port 14 may include a restriction 21 (e.g., a boss) to restrict the flow of cooling air through the viewing port of the blade.
Fig. 4 depicts an exemplary embodiment in which the bracket 34 may be connected to a cap assembly 40, the cap assembly 40 may be arranged to secure the viewing instrument 16 in the blade 12 and provide an axial force to push the distal end of the housing of the viewing instrument 16 against the base plate 41.
As shown in further detail in fig. 5, in an exemplary embodiment, the cap assembly 40 may include an externally threaded cap 44, the externally threaded cap 44 being connected to the bracket 34 to receive an internally threaded cap 46, wherein the caps 44 and 46 may be arranged to provide a threaded connection between each other. A spring biasing element 48 may be disposed between flanges 50 configured in the viewing instrument 16 such that when the internally threaded cap 46 is tightened onto the externally threaded cap 44, the spring biasing element 28 provides an axial force to urge the distal end of the viewing instrument 16 against the base plate 41 (fig. 4).
In another exemplary embodiment, as shown in fig. 6, the carriage 34 may include a twist-lock assembly 52, the twist-lock assembly 52 may include a locking slot 54 for receiving a locking pin 56 configured in the scope 16 and may further include a spring-biased element 58, the spring-biased element 58 being arranged to provide an axial force to urge the distal end of the scope against the bottom plate. As can be appreciated from fig. 6, the carrier 32 may include a plurality of perforations 57 to reduce obstruction of the working gas passing through the blades.
It will be appreciated that the scope 16 need not be limited to a rigid optics implementation (similar in construction to a photographic telephoto lens), as it is contemplated that in one exemplary embodiment, as shown in FIG. 7, the scope 16 may include one or more fiber optic bundles 70 (similar in construction to a flexible medical endoscope) arranged to view IR emissions from the region of interest 20. It will be appreciated that this embodiment can provide flexibility in optical routing compared to rigid optics. For example, the optical coupling between the fiber optic bundle 60 and the IR camera 22 (FIG. 1) provides the designer with flexibility, for example, in terms of flexibility regarding the positioning of the IR camera 22.
In operation, a mechatronic system embodying aspects of the present invention may be configured to provide temperature mapping and/or spatial imaging of turbine components in a region of interest. In one exemplary embodiment, the IR data may be calibrated in terms of relative or absolute temperature to generate a temperature map of the turbine components in the region of interest. For example, this can allow for determining whether one or more regions of the turbine components may be undergoing thermal damage. As will be appreciated by those skilled in the art, such thermal damage may result in shortened life or damage to particular turbine components.
In operation, a mechatronic system embodying aspects of the present invention may be configured to monitor the temperature and condition of an area of interest in real time or near real time. Systems according to aspects of the present invention may be innovatively arranged to provide retroscopic-viewing (e.g., generally backward-viewing) of an area of interest. The system may be configured to monitor a region of interest under various operating conditions of the turbine (e.g., start-up, base load, and shut-down).
In one exemplary embodiment, the IR data may be processed to generate a spatial image of the turbine component in the region of interest. For example, spatial imaging is useful for visualization of one or more regions of these turbine components that may be undergoing physical damage. The spatial imaging is also useful for understanding operational issues related to turbine components that do not operate as desired. It will be appreciated that thermal mapping and spatial imaging may be used cooperatively in combination to obtain common knowledge regarding various characteristics of turbine components in a region of interest, such as operational performance, cause of life shortening or damage, manufacturing defects, service induced defects, and the like. It will be appreciated that the data collected by a monitoring instrument embodying aspects of the present invention may be collected at different wavelengths. These data may then be processed, for example, to generate a quantification of additional characteristics or temperature or other spectral measurements, such as may be used to generate a multispectral image and/or measurements from a given region of interest.
Exemplary aspects of the invention may include: thermal and/or spatial imaging for inspection of moving or static TBC coated components; the ability to make quantitative measurements without or with minimal disruption to the operation of the turbine; and the ability to make operational decisions substantially in real time so as to reduce risk and damage due to TBC failure. It will be appreciated that a system embodying aspects of the present invention is not limited to on-line operation and may be adapted for off-line operation, for example to allow non-destructive and non-contact quantitative measurements at various settings, for example to allow non-destructive and non-contact quantitative measurements of new, serviced and serviced components while the turbine is in an off-line mode.
In one exemplary online embodiment, data indicative of measurements and/or suitable for generating images of a region of interest may be periodically monitored and tracked under near real-time operation of the turbine. It is contemplated that a rapid analysis and determination system that may utilize experts and/or regulatory subsystems can be employed to analyze the collected data and make determinations regarding the operation of the turbine. The expert and/or supervisory subsystem may include predictive algorithms that may allow for prediction of available operating time upon detection of a particular fault condition. The expert and/or supervisory subsystem may be configured to allow an operator to change turbine operating conditions substantially in real time and/or interact with a supervisory controller to change turbine operating conditions substantially in real time.
While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only. Numerous variations, modifications, and alternatives can be implemented without departing from the invention. Accordingly, it is intended that the invention be limited only by the spirit and scope of the appended claims.
Claims (11)
1. A turbine engine, comprising:
an inner-cooled fixed blade;
at least one monitoring port disposed in the stationary vane; and
a monitoring instrument operatively associated with the at least one monitoring port of the stationary blade to provide a field of view of a region of interest,
wherein,
the turbine engine further includes a data acquisition device coupled to the monitoring instrument,
the monitoring instrument comprising a scope and the data acquisition device comprising an infrared imaging device coupled to the scope to acquire imaging data of a region of interest,
the scope fixedly attached within the interior of the stationary blade using a first mounting device, the first mounting device comprising a guide tube configured to receive a distal end of the scope,
the viewing instrument is also fixedly attached in the interior of the stationary blade using a second mounting device that includes a bracket connected to the proximal end of the stationary blade and a funnel supported by the bracket for receiving the viewing instrument into the stationary blade.
2. The turbine engine of claim 1, wherein the infrared imaging device comprises an infrared camera having a visual axis facing away from a region of interest, and the field of view of the viewing instrument is configured to provide a reverse view with respect to the visual axis of the infrared camera such that the region of interest is within the visual axis of the infrared camera.
3. The turbine engine of claim 1, wherein the bracket supports a shroud assembly for securing the monitoring instrument.
4. The turbine engine of claim 3, wherein the shroud assembly for securing the monitoring instrument includes a spring-biased element.
5. The turbine engine of claim 3, wherein the shroud assembly includes an externally threaded shroud coupled to the bracket and an internally threaded shroud received by the externally threaded shroud to provide a threaded connection therebetween.
6. The turbine engine of claim 3, wherein the monitoring port includes a restriction to restrict air flow through the monitoring port.
7. The turbine engine of claim 3, wherein the vanes are disposed in a path of a working gas of the turbine engine, and further wherein the carrier includes a plurality of perforations to reduce obstruction of the working gas.
8. The turbine engine of claim 1, wherein the infrared imaging device comprises an infrared camera disposed in a plenum defined by an inner casing and an outer casing of the turbine.
9. The turbine engine of claim 8, wherein the infrared camera includes a water cooling system.
10. The turbine engine of claim 1, wherein the infrared imaging device comprises an infrared camera disposed outside of a casing of the turbine.
11. The turbine engine of claim 1, wherein the viewing instrument comprises a fiber optic bundle.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US40537710P | 2010-10-21 | 2010-10-21 | |
| US61/405,377 | 2010-10-21 | ||
| US13/274,692 US9015002B2 (en) | 2010-10-21 | 2011-10-17 | System for monitoring a high-temperature region of interest in a turbine engine |
| US13/274,692 | 2011-10-17 | ||
| PCT/US2011/056650 WO2012054439A1 (en) | 2010-10-21 | 2011-10-18 | System for monitoring a high-temperature region of interest in a turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103180700A CN103180700A (en) | 2013-06-26 |
| CN103180700B true CN103180700B (en) | 2016-12-14 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| GB2358059A (en) * | 2000-01-07 | 2001-07-11 | Rotadata Ltd | Pyrometric determination of radiance and/ or temperature |
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| GB2358059A (en) * | 2000-01-07 | 2001-07-11 | Rotadata Ltd | Pyrometric determination of radiance and/ or temperature |
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Address after: Florida, USA Patentee after: Siemens energy USA Address before: Florida, USA Patentee before: SIEMENS ENERGY, Inc. |