BACKGROUND OF THE INVENTION
The subject matter disclosed herein relates generally to
monitoring systems and, more specifically, to systems and methods for use in
monitoring operation of rotor assemblies.
yRf Known machines, such as gas turbines, include rotor
assemblies. The rotor assemblies may exhibit vibrations or other behavior during
operation. Sensors may be used to monitor such behavior to determine the
operational status of one or more components. For example, sensors may measure an
amount of vibration induced in a motor drive shaft, a rotational position or
displacement of the motor drive shaft, and/or other operational characteristics of a
machine or motor. Often, sensors are coupled to a monitoring system that includes a
plurality of monitors and at least one processor. The monitoring system receives i
signals that are representative of measurements sensed from the sensors.
At least some known monitoring systems use vibration
sensors to determine the existence of cracks in a component being monitored.
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However, because vibration sensors may only be able to detect the existence of a
crack, and may be unable to pinpoint the location of a crack, at least some known
monitoring systems are unable to accurately determine the location of cracks.
Moreover, although at least some known monitoring systems use clearance sensors in
an effort to determine the location of cracks, because of temperature limitations of the •
sensors and space limitations within the machine being monitored, at least some of such monitoring systems are unable to monitor an operating (i.e., online) rotor
assembly in a gas turbine engine. j
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BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a system for use in monitoring operation of a
rotor assembly is provided. The system includes a plurality of clearance sensors
including at least a first clearance sensor configured to measure a distance between
the first sensor and a surface of a lockwire tab, and a monitoring unit coupled to the
plurality of clearance sensors, the monitoring unit configured to receive
measurements from the plurality of clearance sensors, and determine whether a crack
exists in the rotor assembly based on the received measurements.
Bp/ In another aspect, a monitoring unit for use in monitoring
operation of a rotor assembly is provided. The monitoring unit includes a memory
device configured to store measurements received from a plurality of clearance
sensors that include at least a first sensor configured to measure a distance between
the first sensor and a surface of a lockwire tab, and a processing device coupled to the
memory device and configured to determine whether a crack exists in the rotor
assembly based on the stored measurements.
In yet another aspect, a method for monitoring operation of a
rotor assembly is provided. The method includes acquiring, from at least one
clearance sensor, measurements indicative of the distance between the at least one
clearance sensor and a component of the rotor assembly, wherein the at least one
clearance sensor includes a first sensor configured to measure a distance between the
first sensor and a surface of a lockwire tab, transmitting the acquired measurements to
a monitoring unit, and determining, using the monitoring unit, whether a crack exists
in the rotor assembly based on the received measurements.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a schematic cross-sectional view of an exemplary
turbine engine.
Fig. 2 is a schematic cross-sectional view of an exemplary
rotor assembly that may be used with the turbine engine shown in Fig. 1.
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Fig. 3 is an enlarged view of a portion of the rotor assembly
shown in Fig. 2.
Fig. 4 is a block diagram of an exemplary monitoring unit that
may be used with the rotor assembly shown in Fig. 2.
DETAILED DESCRIPTION OF THE INVENTION
The systems and methods described herein enable cracks in a
rotor assembly of a gas turbine to be accurately identified. A plurality of clearance
^g^ sensors periodically measure distances to a component of the rotor assembly. More
specifically, at least one sensor measures a distance between the sensor and a surface
of a lockwire tab. Measurement taken by the plurality of clearance sensors are J
transmitted to a monitoring unit that uses the measurements to determine whether any
cracking exists. The monitoring unit may also compare measurements from at least
two clearance sensors to determine the location of a crack on the component.
Technical effects of the methods and systems described
herein include at least one of: (a) acquiring, from at least one clearance sensor,
measurements indicative of the distance between the at least one sensor and a
component of the rotor assembly, wherein the at least one clearance sensor includes a
first sensor configured to measure a distance between the first sensor and a surface of
a lockwire tab; (b) transmitting the acquired measurements to a monitoring unit; and
^ > (c) determining whether a crack exists in the rotor assembly based on the received
measurements.
Fig. 1 is a schematic cross-sectional view of an exemplary
turbine engine 100. More specifically, in the exemplary embodiment, turbine engine
100 is a gas turbine engine. While the exemplary embodiment is directed towards a [
gas turbine engine, the present invention is not limited to any one particular engine, }
and one of ordinary skill in the art will appreciate that the current invention may be
used in connection with other turbine engines and/or rotating structures other than a
rotor assembly. I
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In the exemplary embodiment, turbine engine 100 includes an
intake section 112, a compressor section 114 downstream from intake section 112, a
combustor section 116 downstream from compressor section 114, a turbine section
118 downstream from combustor section 116, and an exhaust section 120. In the
exemplary embodiment, turbine section 118 is coupled to compressor section 114 via
a rotor shaft 122. Alternatively, turbine engine 100 does not include a rotor shaft 102
coupling turbine section 118 to compressor section 114. In the exemplary
embodiment, combustor section 116 includes a plurality of combustors 124.
Combustor section 116 is coupled to compressor section 114 such that each
<^fe combustor 124 is in flow communication with compressor section 114. A fuel
injection assembly 126 is coupled within each combustor 124. Turbine section 118 is
coupled to compressor section 114 and to a load 128 such as, but not limited to, an
electrical generator and/or a mechanical drive application. In the exemplary
embodiment, each compressor section 114 and turbine section 118 includes at least
one rotor disk assembly 130 that is coupled to a rotor shaft 122 to form a rotor
assembly 132.
Fig. 2 is a schematic cross-sectional view of rotor assembly
132 that may be used with turbine engine 100 (shown in Fig. 1). Fig. 3 is an enlarged i
view of a portion of rotor assembly 132 taken along area 3 (shown in Fig. 2). In the
exemplary embodiment, rotor assembly 132 includes a rotor wheel 202 that
circumscribes a longitudinal axis 204 extending axially through rotor assembly 132. i
A plurality of buckets 206 are coupled to rotor wheel 202 and i
each extend radially outward from rotor wheel 202 towards an outer casing 208 in a
radial direction that is perpendicular to longitudinal axis 204. Moreover, each bucket
206 extends radially from a base 210 to a tip 212, and extends axially from a leading
edge 214 to a trailing edge 216. A lockwire tab 220 at base 210 secures an axial !
position of bucket 206 relative to rotor wheel 202. Although only one bucket 206 is
illustrated in Fig. 2, rotor assembly 132 includes a plurality of buckets 206 that are j
coupled to and that extend radially outward from rotor wheel 202. As such, during
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operation, rotor wheel 202 and bucket 206 simultaneously rotate about longitudinal
axis 204.
Rotor assembly 132 also includes one or more clearance
sensors 230 that each monitor a relative position of lockwire tab 220 and/or bucket
206 to enable determining whether any lockwire tabs 220 and/or buckets 206 have
developed any cracks, as is described in more detail below.
In the exemplary embodiment, clearance sensors 230 are
capacitive probes that have a relatively high temperature tolerance. Accordingly,
# clearance sensors 230 each measure a distance to a surface of a component based on a
detected capacitance. Alternatively, clearance sensors 230 may be any other type of
sensor that enables rotor assembly 132 to function as described herein. While in the ;
exemplary embodiment, clearance sensors 230 measure a position and displacement
of lockwire tab 220 and/or buckets 206, clearance sensors 230 may measure a position
and displacement of any surface and/or feature of any component in rotor assembly
132 that enables rotor assembly 132 to function as described herein. For example,
clearance sensors 230 may measure a position and displacement of features proximate
base 210 other than lockwire tab 220.
A first sensor 240 of the clearance sensors 230 is positioned
to measure a radial position and displacement of lockwire tab 220. Specifically, first
sensor 240 measures a radial distance Di between first sensor 240 and a first surface
^ P 242 of lockwire tab 220. First surface 242 is substantially parallel to longitudinal axis
204, and first sensor 240 is coupled to a monitoring unit 244 via a first cable 246.
Monitoring unit 244 processes data received from clearance sensors 230, as is
described in more detail below. Measurements from first sensor 240 are transmitted
to monitoring unit 244 via first cable 246. First cable 246 may also provide power to t
first sensor 240. In the exemplary embodiment, first sensor 240 is coupled to a ;
diaphragm seal 248, and first cable 246 passes through diaphragm seal 248, a stator
vane, and outer casing 208 to reach monitoring unit 244. Alternatively, first sensor 6
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240 and first cable 246 have any relative position and/or orientation that enables rotor assembly 132 to function as described herein.
A second sensor 250 of clearance sensors 230 measures an axial position and displacement of lockwire tab 220. Specifically, second sensor 250
measures an axial distance D2 between second sensor 250 and a second surface 252 of
lockwire tab 220. Second sensor 250 is coupled to monitoring unit 244 via a second ;
cable 256. Measurements from second sensor 250 are transmitted to monitoring unit
244 via second cable 256. Second cable 256 may also provide power to second
~. sensor 250. In the exemplary embodiment, second sensor 250 is coupled to
^^ diaphragm seal 248, and second cable 256 passes through diaphragm seal 248, a stator
vane, and outer casing 208 to reach monitoring unit 244. Alternatively, second sensor I
250 and second cable 256 have any relative position and/or orientation that enables rotor assembly 132 to function as described herein.
A third sensor 260 measures a radial position and
displacement of tip 212 adjacent to leading edge 214. Specifically, third sensor 260
measures a radial distance D3 defined between third sensor 260 and tip 212. Third
sensor 260 is coupled to monitoring unit 244 via a third cable 266. Measurements 1
from third sensor 260 are transmitted to monitoring unit 244 via third cable 266.
Third cable 266 may also provide power to third sensor 260. In the exemplary >
embodiment, third sensor 260 is coupled to outer casing 208, and third cable 266
At passes through outer casing 208. Alternatively, third sensor 260 and third cable 266
have any relative position and/or orientation that enables rotor assembly 132 to
function as described herein.
A fourth sensor 270 measures a radial position and
displacement of tip 212 adjacent to trailing edge 216. Specifically, fourth sensor 270
measures a radial distance D4 between fourth sensor 270 and tip 212. Fourth sensor j
270 is coupled to monitoring unit 244 via a fourth cable 276. Measurements from
fourth sensor 270 are transmitted to monitoring unit 244 via fourth cable 276. Fourth
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cable 276 may also provide power to fourth sensor 270. In the exemplary
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embodiment, fourth sensor 270 is coupled to outer casing 208, and fourth cable 276
passes through outer casing 208. Alternatively, fourth sensor 270 and fourth cable
276 have any relative position and/or orientation that enables rotor assembly 132 to
function as described herein.
In the exemplary embodiment, as first and second surfaces
242 and 252 are substantially continuous as rotor assembly 132 rotates, first and
second sensors 240 and 250 are amplitude modulated capacitive probes. In amplitude
modulated capacitive probes, the output voltage of the capacitive probe increases as
__ the clearance increases. On the other hand, due to space between adjacent buckets
^ ^ 206, surface of tip 212 is discontinuous as measured by third and fourth sensors 260
and 270 while rotor assembly 132 rotates. Accordingly, the in the exemplary
embodiment, third and fourth sensors 260 and 270 are frequency modulated
capacitive probes. In frequency modulated capacitive probes, the output voltage of
the capacitive probe decreases as the clearance increases. Amplitude modulated and
frequency modulated capacitive probes may be calibrated using any methods that
enable clearance sensors 230 to function as described herein.
While the exemplary embodiment includes four clearance
sensors 230, rotor assembly 132 may include any number of clearance sensors 230 that enables rotor assembly 132 to function as described herein. In the exemplary
embodiment, clearance sensors 230 periodically measure the position and
j £ . displacement of bucket 206. Alternatively, clearance sensors 230 may continuously
measure the position and displacement of bucket 206. Further, while in the
exemplary embodiment, clearance sensors 230 relay measurements to monitoring unit
244 via cables 246, 256, 266, and 276, alternatively, clearance sensors 230 may
wirelessly transmit measurements to monitoring unit.
Fig. 4 is a block diagram of an exemplary monitoring unit
400, such as monitoring unit 244 (shown in Fig. 2), that may be used to monitor rotor
assembly 132 (shown in Fig. 2) for cracking. Monitoring unit 400 includes at least
one memory device 410 and a processor 415 that is coupled to memory device 410 for
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executing instructions. In some embodiments, executable instructions are stored in
memory device 410. Monitoring unit 400 performs one or more operations described <
herein by programming processor 415. For example, processor 415 may be
programmed by encoding an operation as one or more executable instructions and by
providing the executable instructions in memory device 410. Processor 415 may
include one or more processing units (e.g., in a multi-core configuration).
Memory device 410 is one or more devices that enable
information such as executable instructions and/or other data to be stored and
_. retrieved. Memory device 410 may include one or more computer readable media,
^ ^ such as, without limitation, dynamic random access memory (DRAM), static random
access memory (SRAM), a solid state disk, and/or a hard disk. Memory device 410
may be configured to store, without limitation, application source code, application
object code, source code portions of interest, object code portions of interest,
configuration data, execution events and/or any other type of data.
In some embodiments, monitoring unit 400 includes a ;
presentation interface 420 that is coupled to processor 415. Presentation interface 420
presents information, such as application source code and/or execution events, to a :
user 425. For example, presentation interface 420 may include a display adapter (not
shown) that may be coupled to a display device, such as a cathode ray tube (CRT), a
liquid crystal display (LCD), an organic LED (OLED) display, and/or an "electronic
^11 ink" display. In some embodiments, presentation interface 420 includes one or more
display devices.
In some embodiments, monitoring unit 400 includes an input
interface 430, such as a user input interface 435. In the exemplary embodiment, user
input interface 435 is coupled to processor 415 and receives input from user 425.
User input interface 435 may include, for example, a keyboard, a pointing device, a
mouse, a stylus, a touch sensitive panel (e.g., a touch pad or a touch screen), a
gyroscope, an accelerometer, a position detector, and/or an audio user input interface.
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A single component, such as a touch screen, may function as both a display device of
presentation interface 420 and user input interface 435.
In the exemplary embodiment, monitoring unit 400 includes a
communication interface 440 coupled to processor 415. Communication interface
440 communicates with one or more remote devices. In the exemplary embodiment,
communication interface 440 communicates with clearance sensors 230. To
communicate with remote devices, communication interface 440 may include, for
example, a wired network adapter, a wireless network adapter, and/or a mobile
telecommunications adapter.
Measurements from clearances sensors 230 are received by
monitoring unit 244 and stored in memory device 410. To determine whether cracks
exist in bucket 206, processor 415 analyzes and processes measurements stored in
memory device 410. In the exemplary embodiment, processor 415 analyzes
measurements for each clearance sensor 230 over time. Alternatively, processor 415
analyzes measurements in any manner that facilitates detecting cracks in bucket 206.
In the exemplary embodiment, processor 415 monitors
measurements for each clearance sensor 230 individually. For example, processor
415 may monitor distance Dj over time as measured by first sensor 240. If processor
415 determines that distance Di is increasing over time, such a trend may indicate that
lockwire tab first surface 242 is pulling away from first sensor 240, and accordingly,
^ p that a crack may be developing and/or have developed in lockwire tab 220. Similarly,
if processor 415 determines that distance Di is decreasing over time, a crack may be
developing and/or have developed in lockwire tab 220. Accordingly, measurements
from a single clearance sensor 230 may be used to determine the existence and/or
location of a crack.
In the exemplary embodiment, processor 415 also compares
measurements received from a plurality of sensors 230 to determine the location of a
potential crack. Specifically, based on the received measurements, processor 415 may
determine the axial location of a crack (i.e., whether the crack is proximate leading
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edge 214 or trailing edge 216) as well as the radial location of the crack (i.e., whether
the crack is in lockwire tab 220 or bucket 206). For example, processor may
compare data measured by third sensor 260 with data measured by fourth sensor 270.
If, for example, distance D3 increases over time while distance D4 decreases over
time, such data may indicate that bucket 206 is shifting or tipping towards leading
edge 214, and there is a likelihood that a crack may have developed along bucket
trailing edge 216. Similarly, if distance D3 decreases over time while distance D4
increases over time, it is probable that a crack may have developed along bucket
leading edge 214. In yet another example, if distances D3 and D4 change over time,
J f t but distances Di and D2 remain constant, it is probable that a crack may have
developed in bucket 206, but not in lockwire tab 220.
Accordingly, by analyzing measurements from clearance
sensors 230, processor 415 can determine the existence of a crack in bucket 206
and/or lockwire tab 220, as well as an approximate location of the crack. That is,
processor 415 can monitor and/or compare measurements for any number of
clearance sensors 230 to determine the existence and/or location of a crack. For
example, processor 415 may compare measurements between first sensor 240 and
second sensor 250 to determine the location of a crack within lockwire tab 220.
Moreover, other data related to rotor assembly 132, such as pressure, temperature,
and/or vibration data may be combined with the measurements from clearance sensors
230 for further analysis.
In some embodiments, a baseline clearance for each clearance
sensor 230 is stored in memory device 410. Further, each clearance sensor 230 may
have a distinct baseline clearance for each of a plurality of operating regimes. The
operating regimes may be characterized by operating parameters such as, for example,
power produced, a fuel stroke ratio, a turbine speed, an inlet guide vane angle, and an
estimated firing temperature. Such operating parameters may be monitored and
stored to determine the applicable operating regime. When measurements from a I
given clearance sensor 230 deviate from the associated baseline measurement, £
processor 415 may establish a corresponding threat level. For example, in one
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embodiment, processor 415 may generate a minor "watch" threat level when j
measurements deviate from the baseline by three or more standard deviations, a
moderate "warn" threat level when measurements deviate by four-and-a-half or more
standard deviations, and a major "alert" threat level when measurements deviate by
six or more standard deviations. Thresholds for the threat levels may also be
determined by finite element modeling and/or observation of rotor assembly 132.
Appropriate alerts may be generated by processor 415 based on the threat level.
Further, alerts from multiple sensors 230 may be combined to generate a composite
alert for rotor assembly 132.
^ ^ In the exemplary embodiment, when processor 415 detects a
crack in bucket 206 by analyzing measurements from clearance sensors 230 using one
or more of the methods described herein, processor 415 generates an alert to notify an
operator of the possibility of a crack. The alert may include any audio and/or visual
indication that notifies user 425 of existence and/or location of a crack. For example,
the alert may include at least one of a sound generated by presentation interface 420
and/or an icon, symbol, and/or message displayed on presentation interface 420. The
alert may also be an electronic alert (e.g., a text message) sent to a mobile device.
Processor 415 may also be used to detect anomalies other
than cracks in rotor assembly 132 by analyzing measurements from clearance sensors
230. For example, by analyzing measurements from first and/or second sensors 240
I—.. and 250, processor 415 may determine that lockwire tab 220 is failing and/or that a
^ ^ lockwire of lockwire tab 220 has slipped. Similar to above, when processor 415
detects failure of one or more components of lockwire tab 220, processor 415 may
generate a corresponding alert. An operator who receives the alert can take
appropriate action to prevent damage to rotor assembly 132.
The embodiments described herein enable cracks in a rotor
assembly of a gas turbine to be accurately identified. A plurality of clearance sensors
periodically measure distances to a component of the rotor assembly. More
specifically, at least one sensor measures a distance between the sensor and a surface '
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of a lockwire tab. Measurement taken by the plurality of clearance sensors are
transmitted to a monitoring unit that uses the measurements to determine whether any
cracking exists. The monitoring unit may also compare measurements from at least
two clearance sensors to determine the location of a crack on the component. <
As compared to at least some known monitoring systems, the
monitoring systems described herein enable cracks to be identified in a rotor assembly
while the rotor assembly is in operation (i.e., online). Moreover, at least some known
monitoring systems are able to determine the existence of a crack, but not the location
-p. of the crack. In contrast, the embodiments described herein enable determination of
an existence and a location of a crack. Furthermore, unlike at least some known
monitoring systems that measure only blade clearance, the monitoring systems
described herein also accurately measure clearances of a lockwire tab.
The methods and systems described herein are not limited to }
the specific embodiments described herein. For example, components of each system
and/or steps of each method may be used and/or practiced independently and
separately from other components and/or steps described herein. In addition, each
component and/or step may also be used and/or practiced with other systems,
apparatus, and methods.
This written description uses examples to disclose the
invention, including the best mode, and also to enable any person skilled in the art to
^ r practice the invention, including making and using any devices or systems and
performing any incorporated methods. The patentable scope of the invention is
defined by the claims, and may include other examples that occur to those skilled in
the art. Such other examples are intended to be within the scope of the claims if they
have structural elements that do not differ from the literal language of the claims, or if
they include equivalent structural elements with insubstantial differences from the
literal languages of the claims.
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While the invention has been described in terms of various
specific embodiments, those skilled in the art will recognize that the invention may be
practiced with modification within the spirit and scope of the claims.

WE CLAIM :
1. A system for use in monitoring operation of a rotor assembly (132), said
system comprising:
a plurality of clearance sensors (230) comprising at least a first clearance
sensor (240, 250) configured to measure a distance between said first sensor and a
surface (242, 252) of a lockwire tab (220); and
a monitoring unit (244) coupled to said plurality of clearance sensors, said
gm, monitoring unit configured to:
receive measurements fi^om said plurality of clearance sensors; and
determine whether a crack exists in the rotor assembly based on the
received measurements.
2. A system in accordance with Claim 1, wherein said first sensor (240)
comprises a sensor positioned to measure a distance between said first sensor and a
surface (242) of the lockwire tab (220) that is substantially parallel to a longitudinal
axis (204) of the rotor assembly (132).
3. A system in accordance with Claim 1, wherein said first sensor (250)
comprises a sensor positioned to measure a distance between said sensor and a surface
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(252) of the lockwire tab (220) that is substantially perpendicular to a longitudinal
axis (204) of the rotor assembly.
4. A system in accordance with Claim 1, wherein said plurality of clearance
sensors (230) further comprises at least a second sensor (260, 270) positioned to
measure a distance between said second sensor and a surface (212) of a bucket (206)
coupled to the rotor assembly (132).
5. A system in accordance with Claim 4, wherein said second sensor (260)
comprises a sensor positioned to measure a distance between said second sensor and a
tip (212) of the bucket (206) adjacent to a leading edge (214) of the bucket (206).
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6. A system in accordance with Claim 4, wherein said second sensor (270)
comprises a sensor positioned to measure a distance between said second sensor and a
tip (212) of the bucket (206) adjacent to a trailing edge (216) of the bucket (206).
7. A system in accordance with Claim 1, wherein said monitoring unit (244)
is further configured to compare measurements firom at least two of said plurality of
clearance sensors (230) to determine a location of a crack in the rotor assembly (132).
8. A system in accordance with Claim 1, wherein said monitoring unit (244)
is configured to generate an alert when a crack is detected.
9. A monitoring unit (400) for use in monitoring operation of a rotor assembly
(132), said monitoring unit comprising:
a memory device (410) configured to store measurements received from a
plurality of clearance sensors (230) that include at least a first sensor (240, 250)
configured to measure a distance between the first sensor and a surface (242, 252) of a
lockwire tab (220); and
a processing device (415) coupled to said memory device and configured to
determine whether a crack exists in the rotor assembly based on the stored
measurements.
10. A monitoring unit (400) in accordance with Claim 9, wherein said
^R> memory device (410) is configured to store measurements fi-om a first sensor (240)
positioned to measure a distance between the first sensor and a surface (242) of the
lockwire tab (220) that is substantially parallel to a longitudinal axis (204) of the rotor
assembly (132).