GAS TURBINE LIFE PREDICTION AND OPTIMIZATION DEVICE AND
METHOD
BACKGROUND
TECHNICAL FIELD
Embodiments of the subject matter disclosed herein generally relate to methods and
systems and, more particularly, to mechanisms and techniques for predicting and
optimizing the operating life of a gas turbine, or components therein.
DISCUSSION OF THE BACKGROUND
Figure 1, which is similar to Figure 1 of U.S. Patent Application Publication
2008/0243352 (incorporated herein by reference), illustrates an example of a gas
turbine 10 having a compressor 12, a combustor 14, a turbine 16 coupled to the
compressor 12, and a computer control system (controller) 18. An inlet duct 20 to the
compressor 12 may feed ambient air to compressor 12. The inlet duct 20 may have
ducts, filters, screens and noise abatement devices that contribute to a pressure loss of
ambient air flowing through the inlet 20 and into inlet guide vanes 2 1 of the
compressor 12. An exhaust duct 22 for the turbine directs combustion gases from the
outlet of the turbine 10 through, for example, emission control and noise abatement
devices. The turbine 10 may drive a generator 24 that produces electrical power.
Alternatively, whenever the turbine is a two shaft device (e.g., including a high
pressure turbine and a low pressure turbine), the low pressure turbine, which can turn
at a different speed than the high pressure rotor, may drive a more generic machine as
a compressor or even a generator.
The operation of the gas turbine 1 may be monitored by several sensors 26 designed
to measure different performance-related variables of the turbine 10, the generator and
the ambient environment. For example, groups of redundant temperature sensors 26
may monitor ambient temperature surrounding the gas turbine 10, compressor
discharge temperature, turbine exhaust gas temperature, and other temperature
measurements of the gas stream through the gas turbine 10. Similarly, groups of
redundant pressure sensors 26 may monitor ambient pressure, and static and dynamic
pressure levels at the compressor inlet and outlet turbine exhaust, at other locations in
the gas stream through the gas turbine 10. Groups of redundant humidity sensors 26,
for example, wet and dry bulb thermometers, may measure ambient humidity in the
inlet duct of the compressor 12. Groups of redundant sensors 26 may also include
flow sensors, speed sensors, flame detector sensors, valve position sensors, guide vane
angle sensors, or the like, that sense various parameters pertinent to the operation of
gas turbine 10. As used herein, "parameters" refer to items that can be used to define
the operating conditions of the turbine, such as but not limited to temperatures,
pressures, and gas flows at defined locations in the turbine.
Also, the fuel control system 28 regulates the fuel flowing from a fuel supply to the
combustor 14, one or more splits between the fuel flowing into primary and secondary
fuel nozzles, and the amount of fuel mixed with secondary air flowing into a
combustion chamber. The fuel control system 28 may also select the type of fuel for
the combustor. The fuel control system 28 may be a separate unit or may be a
component of the main controller 18. The controller 18 may be a computer system
having at least one processor that executes programs and operations to control the
operation of the gas turbine using sensor inputs and instructions from human
operators. The commands generated by the controller 18 may cause actuators on the
gas turbine to, for example, adjust valves (actuator 27) between the fuel supply and
combustors that regulate the flow, fuel splits and type of fuel flowing to the
combustors; adjust inlet guide vanes 2 1 (actuator 29) on the compressor; adjust inlet
bleed heat; as well as activate other control settings on the gas turbine.
The turbine may have a wide application in the oil and gas field. That is, it may drive
compressors in the pipelines as well it may still drive compressors to pump out petrol
or natural gas from wells. An important critical quality (CTQ) for oil and gas
companies is the availability of their plants so to maximize production. To minimize
plant shut down or disruption, plant core parts, such as the gas turbine, are ideally
replaced/maintained just when their probability of failure has a substantial impact on
plant reliability. Another important CTQ is maintenance cost, which should be
minimized wherever possible.
To improve these and other CTQs, various entities have launched life extension
initiatives as CBM (condition based maintenance) and RLM (rotor life management).
Some techniques rely solely on optical inspections to measure crack lengths to develop a
statistical distribution of crack lengths. This statistical distribution is used to estimate
equipment life expectancy. Another technique involves inspecting a component for
damage or deterioration (e.g., micro-cracks), forming a structural model of the device,
setting a future use condition for the device, and simulating an advancement of the
damage or deterioration. Another approach is to estimate creep damage via an
expression including a Larson-Miller expression, and then performing statistical analysis
(e.g., Weibull statistical analysis) to estimate future creep damage. Here, an estimation
parameter based on an equipment start count and thermal stress is calculated based on a
statistical model. Another approach is to determine a relationship between a metal
temperature of a turbine component and an operating condition of the turbine housing
the component. This approach uses a thermal model of the component and an operating
history of the turbine to predict a current or future component operating temperature.
However, the conventional methods and systems for plant and turbine life extension
require plant shut down for inspections to collect data (e.g., crack lengths) and in
general are not applicable for components that do not show evident failure.
Accordingly, it would be desirable to provide systems and methods that avoid the
afore-described problems and drawbacks.
SUMMARY
Aspects of the invention relate to systems and methods for predicting and optimizing
an operating life of gas turbine components (e.g., rotors), especially components not
showing evident damage and for which a long operating life is expected but that, due
to high thermo-mechanical loads, may crack and quick degenerate into an engine
failure that may compromise plant safety.
According to an exemplary embodiment, there is a computer-based method for
determining a residual life expectancy of a rotor of a gas turbine. The method
includes receiving at the computer operating conditions of the gas turbine; receiving a
gas turbine rotor inspection result; updating, based on the operating conditions of the
gas turbine and the gas turbine rotor inspection result, a database for a fleet
corresponding to the gas turbine; and calculating the residual life expectancy of the
rotor of the gas turbine.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings, which are incorporated in and constitute a part of the
specification, illustrate one or more embodiments and, together with the description,
explain these embodiments. In the drawings:
Figure 1 illustrates an example of a gas turbine;
Figure 2 illustrates four concepts underpinning an embodiment of the invention;
Figure 3 illustrates analytical phases associated with an embodiment of the invention;
Figure 4 illustrates a method for predicting component life according to an
embodiment of the invention;
Figure 5 illustrates another method for predicting a component life of a gas turbine
according to an exemplary embodiment; and
Figure 6 illustrates a device configured to implement the method discussed herein.
DETAILED DESCRIPTION
The following description of the exemplary embodiments refers to the accompanying
drawings. The same reference numbers in different drawings identify the same or
similar elements. The following detailed description does not limit the invention.
Instead, the scope of the invention is defined by the appended claims. The following
embodiments are discussed, for simplicity, with regard to the terminology and structure
of a gas turbine, in particularly to a rotor. However, the embodiments to be discussed
next are not limited to these systems, but may be applied to other systems.
Reference throughout the specification to "one embodiment" or "an embodiment" means
that a particular feature, structure, or characteristic described in connection with an
embodiment is included in at least one embodiment of the subject matter disclosed.
Thus, the appearance of the phrases "in one embodiment" or "in an embodiment" in
various places throughout the specification is not necessarily referring to the same
embodiment. Further, the particular features, structures or characteristics may be
combined in any suitable manner in one or more embodiments.
Gas turbines require periodic inspections to ensure the minimization of operational and
safety risks. Maintenance factors for rotors include both starts and operating
hours. These inspections assess the health of a customer's rotor by compiling and
utilizing pertinent information, including: operational variables (model time, cycle, and
temperature to assess their impact on low cycle fatigue and creep); material history
(including models of the application environment, duty cycle, and maintenance
practices); subcomponent condition (determined by closely examining subcomponents
for damage and fit). With this information, it is possible to make an informed
recommendation for rotor life extension or retirement. When replacement is warranted,
the novel process can provide recommendations regarding the possibility of either an inkind
replacement, or the installation of a new rotor.
As shown in Fig. 2, according to one embodiment, there is a method for predicting
component life with greater accuracy than is possible with conventional systems and
methods. This method may be implemented in a predicting device 20 that will be
discussed in more details later. The method is based on four concepts: physics based
models for predicting a probabilistic life of one or more gas turbine components (21),
results of a thorough inspection of the components (22), results of an evaluation of the
history of the operating life of the engine to which the part belongs (23); and results from
destructive tests on some parts (24). These four concepts may be linked in a method
having multiple Phases as discussed below.
In one embodiment, there are 6 phases as shown in Fig. 3. While 6 phases are described,
one skilled in the art would know that some phases may be skipped and others may be
added. Also, while Fig. 3 shows phases flowing consecutively from 1 to 6, feedback
between phases is possible, as discussed below.
In Fig. 3, numerical/analytical models of Phase 1 (31) feed various transfer functions of
Phase 2 (32). The results of the transfer functions feed various probabilistic analyses
(33) of Phase 3. The results of the probabilistic analyses may be used with destructive
testing results of phase 4 (34) for predicting the life of a given component. Further, the
component's operating history and the non-destructive inspection shown in phase 5 (35)
may also be used when predicting the life of a given component. Results from each of
the first 5 phases may be combined into a life extension prediction of Phase 6 (36).
Details of each of these 6 phases are now described below. Also, while destructive tests
(34) are useful to the process, these destructive tests are usually performed only once so
to characterize material employed on rotor after many hours of operating life. In
contrast, non-destructive tests (inspections) may be performed every time maintenance is
performed on a rotor for which life extension is expected.
Phase 1 of an embodiment of the invention includes the creation of numerical/analytical
models that are able to predict, e.g., a) Flow, pressure and temperature of engine primary
and secondary flows; b) Heat transfer coefficients between flows and rotors; c) Rotor
metal temperatures; and d) Rotor displacements, strains and stresses. In one
embodiment, the models are directed to an "ideal" gas turbine or components, i.e., based
on exclusively on design and manufacturing specifications that are unadulterated by
"real world" experiences. In another embodiment, one or more of the models may
include "real world" parameters. One or more of these models may be specific to a type
of gas turbine, or may be generic. The models as well as the predicting tools may be
commercially available or they may be developed in house.
The numerical/analytical models are designed to be operated in series or in parallel,
depending on an overall scenario or device to be modeled. In one embodiment, the
numerical/analytical models will use one or more input independent variables (vitalX's)
and will output dependent variables (e.g., metal temperatures). The created models may
be stored in a library or model tool kit for later use, e.g., a memory. These models use as
input independent variables and are capable to calculate various dependent variables that
characterize the gas turbine. Examples of independent variables, vitalXs, are an ambient
temperature, a rotor speed, a firing temperature, various internal geometrical clearances,
etc. associated with a turbine.
Phase 2 of an embodiment of the invention includes: a) defining a specific and
appropriate design of experiment (DOE) plan; b) applying one or more of the models
developed in Phase 1 to the DOE to thereby generate corresponding dependent variables;
and c) creating transfer functions (TFs) between cl) life variables [Z] (e.g., cycles-to-
LCF (low cycle fatigue) crack initiation, hours to creep crack initiation, hours/cycles for
crack to propagate in a failure, etc.) and c2) the independent variables (vitalX's) of the
corresponding models. The transfer functions are either those known in the art or new
functions defined for this process or a combination of both. A life variable is in general a
variable representing a maintenance concept or concern over the life of the gas turbine or
turbine component. Regarding crack initiation TFs (LCF), preferably there is at least
one TF for each single part so to allow a replacement of just the single part which is at
the end of life or a replacement of the full rotor, depending on what is more convenient
to the customer. Preferably there will be at least one crack propagation TF for each
surface so to be able to obtain one or more indications and to reduce an amount of
scraps.
Phase 3 of an embodiment of the invention includes: a) Estimation/Definition of vital
X's distributions; b) execution of one or more MonteCarlo simulations to determine a
fleet probabilistic life and/or a Fleet risk of failure; and c) execution of one or more
MonteCarlo simulations to set, for example, a Wheel space alarm (confirmation or
update of existing setting, whenever assessing mature fleet) to minimize risk of failure.
A fleet is understood here to describe a class of gas turbines that have a same set of
characteristics in common. The wheel space alarm is one possible example of possible
alarms that exists in a gas turbine and can be lowered or increased based on the
calculations described herein.
A distribution of a vitalX is now described. Suppose that various gas turbines from a
fleet are provided to various customers, located around the word. An ambient
temperature of the gas turbine is one independent variable, i.e., vitalX. However, an
ambient temperature in Doha (Qatar) is different from an ambient temperature in Alaska.
Thus, for a given vitalX (Tamb), there is a distribution of temperatures for the gas
turbines that make up the fleet. This distribution may be, for example, a Gauss bell or
other shapes.
If a number of data points for any measured vitalX is large enough, it will be possible to
develop a reasonably accurate distribution function for the vitalX. Then, filters (e.g.,
Kalman filters) may be applied to tune the models with field data (e.g. crack length).
However, if a number of data points for any measured vitalX is not large enough, these
filters may not give accurate results. In this case, engineering judgment may be used to
develop a "best guess" distribution function for the vitalX. In this case, the distribution
is defined.
Returning to the wheel space alarm, it is noted that combustion turbines include a
compressor having a plurality of stages that create a compressed airflow and a turbine
having a turbine rotor that drives a shaft. During operation, temperatures at the turbine
rotor rise significantly. Cooling may be provided by directing compressor discharge air
into a wheel space that extends about the turbine rotor. Wheel space temperature may be
maintained at a material limit between compressor discharge temperature and hot gas
path temperature. In the event that the wheel space temperature exceeds the material
limit, an alarm may be sounded to indicate an over temperature condition. When the
material limit is exceeded, the turbomachine may be shut down and, after accurate
inspection and study, one or more devices may be applied to provide additional cooling
flow. Various factors can affect compressor discharge air temperature. For example, as
ambient inlet air temperature rises, compressor discharge air rises. Thus, correctly
setting a Wheel space alarm is desirable and the novel process described herein is
capable of adjusting this alarm.
The preceding Phases (31 to 33) are applicable to both predicting a total life span of a
device/component and to the prediction of a residual life span (i.e., remaining life
optimization). The following Phases are generally more applicable to the prediction of a
residual life span.
Phase 4 (34) of an embodiment of the invention includes destructive laboratory testing of
a statistical amount of scraped parts (in the middle or at the end of their life) to confirm if
material strength is still consistent with design expectations.
Phase 5 (35) of an embodiment of the invention includes the acquisition and exploitation
of a database of historical operating conditions for each specific unit. The data in the
database may include a) the results of any non-destructive tests and b) inspections during
the life of the component. Inspections may include one or more of the following types:
eddy current inspections, magnetic particle inspections, fluorescent penetrant inspections
and/or ultrasonic inspections. Optimally, such tests and inspections will have been
performed on 100% of the part surfaces. Of interest is identifying operating histories
that may indicate that a unit may have been operated in more benign conditions than
were assumed when a manufacturer's life expectancy was estimated.
Phase 6 of an embodiment of the invention includes using the results of the previous 5
Phases to estimate a life extension of a specific part or device (i.e., estimating the risk of
failure associated with extending a life of a component beyond an initial manufacturing
estimated end of life). This estimation may employ statistics that encompass some or all
the vitalXs that affect life expectancy of the part (e.g., operating conditions, geometrical
dimensions, material properties). To simplify calculations, the number of vitalXs in this
Phase (as well as in Phase 3) may be reduced (e.g., to less than 7 vitalXs). This
reduction of vitalXs may be facilitated by creating (inside Phase 2) linear TFs associated
to different groups of vitalXs. These linear TFs may be used to select, from each group
of vitalXs, the vitalX that most effects the corresponding life variable.
A goal of Phase 6 is to use the data of the previous 5 Phases to predict if a component
may have a longer life than what was predicted by the original designer (who may have
used more conservative product life calculations, or who may have assumed an operating
environment more severe than the actual operating environment identified in Phase 5, or
who may have assumed a material strength higher that the actual material strength
identified in Phase 4).
The preceding comments provided an overview of at least 6 phases that may be
combined to generate a more accurate estimate of product life. The following comments
provide additional details about at least some of these 6 phases.
In one embodiment, the inspections of Phase 4 may be used to support (but not validate)
the calculations of Phase 6, as well as to confirm that part has been manufactured
according to design and that part has even been operated and maintained according to
design. The inspections of Phase 4 are preferably not used to validate the calculations of
Phase 6 because the non-destructive inspections of Phase 4 are often not able to detect
local fatigue or creep damage and so are often not reliable for assigning a value for
accumulated damage.
Preferably, the life extension predictions of Phase 6 should rely on a material database
from Phase 4 that is consistent with the estimated life. Preferably, a material creep
database from Phase 4 should include tests not shorter than 1/20 times the expected life.
In other words, the database should include enough information (in terms of time) to be
reliable. An example in this sense is as follows. Suppose that a rotor of the gas turbine
has an expected life time of 20 years. It is desirable that the database includes at least 1
year worth of information about the rotor, i.e., not shorter than 1/20 times the expected
life.
The results of Phase 3 may be used to predict a fleet probabilistic life that is different
from a product specification. Before and after using the results of Phase 3, any
"unexpected" results should be investigated to determine if any models and/or vitalX
distributions should be modified.
The results of Phase 5 may highlight unexpected defects in a part (e.g., cracks). If
unexpected defects are uncovered in Phase 5, a root cause analysis (RCA) should be
performed. The results of the RCA may be applied to phase 6 to further tune the life
extension estimate, and may be applied to design and manufacturing to improve initial
component design and production. In phase 5, cracks may be considered to be an
indication of an end of the part life and should be investigated through RCA so to verify
if predicting models and TFs may still be considered reliable or require modification.
Alternatively, non-crack indications (e.g., scratches, marks, prints) may be acceptable
but just if these non-crack indications do not appear to affect the part life. Re-machining
of defects may be suggested so to make indications more smooth.
These non-crack indications (usage indicators) may be assessed generating dedicated
TFs. The TF will be having same vitalXs as the other TF plus the dimensions of the
indication (length, depth, thickness). As noted above, in order to reduce the amount of
TFs, one embodiment may group part surfaces and define just one TF for each group of
surfaces. Each group may be composed according to surfaces having a similar behavior
so that a final group having a worst location may be selected as being representative of
the full zone. A rotor may have hundredths if not thousands of small surfaces.
The previously described Phases may be combined into the process flow of Fig. 4. The
process may begin with a turbine rotor inspection (41). The inspection determines if
cracks are present (42) or if other life cycle related indications (e.g., scratches, marks,
prints) are present (43). If cracks due to operations are present, a root cause analysis
(RCA) is performed (48). RCA results may be fed back to any predicting models used
by the manufacturer as well as any life extension analysis. If other life cycle related
indications (e.g., scratches, marks, prints) are discovered, these indications may be
combined with historical operating results (44) to estimate a residual life for each
indication. If neither cracks nor other indications are detected, fleet distributions may be
updated to predict a residual life of a specific unit (46). For example, the Y distributions
for a full fleet are generated using vitalX distributions which include the total variability
present on the fleet (e.g., distribution will include all possible sites where machines
may operate. Also, specific unit Y's having distributions which fall inside the fleet
distributions typically maintain a common form (e.g., a Gaussian bell curve). However,
these distributions may be narrow because one or more vitalX distributions can be
replaced by a value (e.g., internal clearance) or replaced by more narrow distributions
(e.g., site ambient temperature). This residual life calculation may also take into account
historical operating results (44). The updated fleet distribution may be used to predict an
overall risk for a unit (47). Examples of predicted risk include predictions for initiation
of cracking and/or a propagation of an existing crack.
In the process of Fig. 4, items 41, 42, 43 and 44 may be considered to be part of Phase 5,
with the remaining items (45, 46, 47 and 48) being associated with Phase 6. One or
more of the previously described Phases 1-4 may feed results to Phase 4. This is useful
because most turbine OEMs design their components so they do not form cracks during
their operating life.
The methodology described above is directed to currently installed and operating gas
turbines. However, one skilled in the art would know that at least the first three are
applicable for a new design (e.g., life predictions for new designs).
The preceding methodology may be performed in one or more processor based devices
(computers) that may or may not be connected over a wired or wireless network. The
processor based device includes a processor, a memory and an input unit. The processor
based device may also include a display. Such a device is discussed with regard to
Figure 6. Computer programs associated with the preceding methodology may be stored
in a non-transistory storage medium such as a memory or a disk or another device.
According to an exemplary embodiment illustrated in Figure 5, there is a method for
determining a residual life expectancy of a rotor of a gas turbine. The method includes a
step 500 of receiving at the computer operating conditions of the gas turbine; a step 502
of receiving a gas turbine rotor inspection result; a step 504 of updating, based on the
operating conditions of the gas turbine and the gas turbine rotor inspection result, a
database for a fleet corresponding to the gas turbine; and a step 506 of calculating the
residual life expectancy of the rotor of the gas turbine.
The above method may be implemented into a device to determine a residual life
expectancy of a gas turbine component. The device may include a memory; and a
processor operatively connected to the memory. The processor may be configured to
receive operating conditions of the gas turbine, receive a gas turbine rotor inspection
result, update, based on the operating conditions of the gas turbine and the gas turbine
rotor inspection result, a database for a fleet corresponding to the gas turbine, and
calculate the residual life expectancy of the rotor of the gas turbine.
The processor may be further configured to use physical models of the gas turbine to
calculate plural dependent variables of the gas turbine based on independent variables, or
to provide the independent variables as input to transfer functions for calculating life
variables, or to receive distributions of the independent variables, or to execute
Montecarlo simulations based on the independent variables, the distributions of the
independent variables, and the transfer functions to determine the fleet probabilistic life,
or to receive destructive lab tests performed on parts of the gas turbine, or to calculate
the residual life expectancy of the rotor of the gas turbine based on the independent
variables, the transfer functions, the MonteCarlo simulations and the destructive lab
tests.
In an exemplary embodiment, a non-transitory computer based product contains
instructions for determining a residual life expectancy of a component of a gas turbine,
the computer based product is arranged to cause a processor based device to perform the
following instructions: receiving operating conditions of the gas turbine; receiving a gas
turbine rotor inspection result; updating, based on the operating conditions of the gas
turbine and the gas turbine rotor inspection result, a database for a fleet corresponding to
the gas turbine; and calculating the residual life expectancy of the rotor of the gas turbine
and an associated risk to life extension.
An example of a representative device capable of carrying out operations in accordance
with the embodiments discussed above is illustrated in Figure 6. Hardware, firmware,
software or a combination thereof may be used to perform the various steps and
operations described herein. The computing structure 600 of Figure 6 is an exemplary
computing structure that may be used in connection with such a system.
The exemplary computing arrangement 600 suitable for performing the activities
described in the exemplary embodiments may include a server 601 . Such a server 801
may include a central processor (CPU) 602 coupled to a random access memory
(RAM) 604 and to a read-only memory (ROM) 606. The ROM 606 may also be other
types of storage media to store programs, such as programmable ROM (PROM),
erasable PROM (EPROM), etc. The processor 602 may communicate with other
internal and external components through input/output (I O) circuitry 608 and bussing
610, to provide control signals and the like. The processor 602 carries out a variety of
functions as is known in the art, as dictated by software and/or firmware instructions.
The server 601 may also include one or more data storage devices, including hard and
floppy disk drives 612, CD-ROM drives 614, and other hardware capable of reading
and/or storing information such as DVD, etc. In one embodiment, software for
carrying out the above discussed steps may be stored and distributed on a CD-ROM
616, diskette 618 or other form of media capable of portably storing information.
These storage media may be inserted into, and read by, devices such as the CD-ROM
drive 614, the disk drive 612, etc. The server 601 may be coupled to a display 620,
which may be any type of known display or presentation screen, such as LCD
displays, plasma display, cathode ray tubes (CRT), etc. A user input interface 622 is
provided, including one or more user interface mechanisms such as a mouse,
keyboard, microphone, touch pad, touch screen, voice-recognition system, etc.
The server 601 may be coupled to other computing devices, such as landline and/or
wireless terminals, via a network. The server may be part of a larger network
configuration as in a global area network (GAN) such as the Internet 628, which
allows ultimate connection to the various landline and/or mobile client/watcher
devices.
The disclosed exemplary embodiments provide a method, computer software and
device for determining a remaining life of a component of a gas turbine. It should be
understood that this description is not intended to limit the invention. On the
contrary, the exemplary embodiments are intended to cover alternatives,
modifications and equivalents, which are included in the spirit and scope of the
invention as defined by the appended claims. Further, in the detailed description of
the exemplary embodiments, numerous specific details are set forth in order to
provide a comprehensive understanding of the claimed invention. However, one
skilled in the art would understand that various embodiments may be practiced
without such specific details.
Although the features and elements of the present exemplary embodiments are described
in the embodiments in particular combinations, each feature or element can be used
alone without the other features and elements of the embodiments or in various
combinations with or without other features and elements disclosed herein. The methods
or flow charts provided in the present application may be implemented in a computer
program, software, or firmware tangibly embodied in a computer-readable storage
medium for execution by a specifically programmed computer or processor
This written description uses examples of the subject matter disclosed to enable any
person skilled in the art to practice the same, including making and using any devices or
systems and performing any incorporated methods. The patentable scope of the subject
matter 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.
CLAIMS:
1. A computer-based method for determining a residual life expectancy of a
rotor of a gas turbine, the method comprising:
receiving at the computer operating conditions of the gas turbine;
receiving a gas turbine rotor inspection result;
updating, based on the operating conditions of the gas turbine and the gas
turbine rotor inspection result, a database for a fleet corresponding to the gas turbine;
and
calculating the residual life expectancy of the rotor of the gas turbine and an
associated risk to life extension.
2. The method of Claim 1, wherein the gas turbine rotor inspection result
indicates the presence of a crack in the rotor, or a usage indication in the rotor or no
event in the rotor.
3. The method of Claim 1 or Claim 2, wherein if there is an unexpected crack
in the rotor, a model of the gas turbine needs to be modified.
4. The method of any preceding Claim, wherein if there is a usage indication
in the rotor or an expected crack, a residual life for the rotor for the usage indication
or expected crack is calculated.
5. The method of any preceding Claim, wherein the usage indication is a mark,
scratch, or print in the rotor.
6. The method of any preceding Claim, further comprising:
using physical models of the gas turbine to calculate plural dependent
variables of the gas turbine based on independent variables, wherein the plural
dependent variables are flows, pressures, and temperatures of the gas turbine, heat
transfer coefficients between flows and the rotor, rotor metal temperatures, rotor
displacements, strains and stresses; and
providing the independent variables as input to transfer functions for
calculating life variables, wherein a life variable is a cycles-to-LCF (low cycle
fatigue) crack initiation parameter, and an independent variable is one of an ambient
temperature and a rotor rotating speed.
7. The method of any preceding Claim, further comprising:
executing MonteCarlo simulations based on the independent variables, the
distributions of the independent variables, and the transfer functions to determine the
fleet probabilistic life.
8. The method of any preceding Claim, further comprising:
executing Monte Carlo simulations based on the independent variables, the
distributions of the independent variables.
9. The method of any preceding Claim, further comprising:
calculating the residual life expectancy of the rotor of the gas turbine based on
the independent variables, the transfer functions, the Monte Carlo simulations and the
destructive lab tests.
10. A device configured to determine a residual life expectancy of a gas
turbine component, the device comprising:
a memory; and
a processor operatively connected to the memory and configured to
receive operating conditions of the gas turbine,
receive a gas turbine rotor inspection result,
update, based on the operating conditions of the gas turbine and the gas
turbine rotor inspection result, a database for a fleet corresponding to the gas turbine,
and
calculate the residual life expectancy of the rotor of the gas turbine.