BACKGROUND
The subject matter disclosed herein relates generally to gas turbine engines
and, more particularly, to methods and apparatus for controlling the operation of gas
turbine engines.
Some gas turbine engines may include a compressor section, a combustor
section, and at least one turbine section. The compressor compresses air, which is
mixed with fuel and channeled to the combustor. The mixture is then ignited,
generating hot combustion gases. The combustion gases are channeled to the turbine,
which extracts energy from the combustion gases for powering the compressor, as
well as producing usefbl work to power a load, such as an electrical generator, or to
propel an aircraft in flight.
In some gas turbine engines, certain control parameters may be adjusted based
upon the operating status of the engine. For example, in a gas turbine engine
configured to propel an aircraft or drive an electrical generator, the angular position of
variable stator vanes in the compressor may be configured to vary with corrected core
speed, such as according to predetermined schedule. The predetermined schedule
may be established such that the engine should produce at least a minimum expected
amount of thrust or power output and maintain a minimum required stall margin
throughout the operating envelope, while accounting for a full range of engine-toengine
manufacturing quality variations, deterioration of engine components over
many years of operation in service, control sensor measurement errors, changes in
operating conditions (e.g., humidity), and the like. As a result, and by design, the
engine may produce a reduced level of thrust or power output or suboptimal level of
efficiency, below its potential capability, in many circumstances.
The problem: Operation of gas turbines at suboptimal control parameter
settings due to the use of a predetermined schedule for certain control parameters may
impact fuel efficiency, operating temperatures, engine life, exhaust emissions, etc.
BRIEF DESCRIPTION
The solution for the above-mentioned problem is provided by the present
disclosure to include example embodiments, provided for illustrative teaching and not
meant to be limiting.
An example method of controlling operation of a gas turbine engine according
to at least some aspects of the present disclosure may include varying an engine input
parameter while operating the gas turbine engine to produce a desired output.
Varying the engine input parameter may include measuring a pre-adjustment value of
an engine operating parameter while operating the gas turbine engine with the engine
input parameter at an initial value while producing the desired output, adjusting the
engine input parameter to a current adjusted value, the current adjusted value
differing fiom the initial value, and measuring a post-adjustment value of the engine
operating parameter while operating the gas turbine engine with the engine input
parameter at the adjusted value and while producing the desired output. An example
method may include determining a future adjusted value of the engine input
parameter based at least in part upon the initial value of the engine input parameter,
the pre-adjustment value of the engine operating parameter, the current adjusted value
of the engine input parameter, and the post-adjustment value of the engine operating
parameter, the future adjusted value being closer to an optimal value of the engine
input parameter than the current adjusted value of the engine input parameter, with
respect to the engine operating parameter. An example method may include
iteratively repeating the varying the engine input parameter operation and the
determining the future adjusted value of the engine input parameter operation, using
the current adjusted value of a prior iteration as the initial value for a subsequent
iteration and the future adjusted value fiom the prior iteration as the current adjusted
value for the subsequent iteration.
An example control system for a gas turbine engine according to at least some
aspects of the present disclosure may include an operating parameter sensor operable
to measure an engine operating parameter associated with a gas turbine engine; an
output sensor operable to measure an output of the gas turbine engine; an actuator
operable to modulate an engine input parameter (e.g., variable stators, variable inlet
guide vanes, variable bleed or bypass airflow, cooling airflow to turbine nozzles or
casings, or combustor fuel flow distribution patterns) associated with the gas turbine
engine; a processor operatively coupled to the operating parameter sensor, the output
sensor, and the actuator; and a storage medium operatively coupled to the processor,
the storage medium comprising machine-readable instructions. The machine readable
instructions may operatively enabling the processor to: receive a pre-adjustment
value of the engine operating parameter (such as thrustlpower output, turbine
inlevexhaust temperatures, exhaust emissions, fuel efficiency) measured by the
operating parameter sensor (or calculated using an analytical model operating on data
measured by the operating parameter sensor), cause the actuator to adjust the engine
input parameter fiom an initial value to a current adjusted value while operating the
gas turbine engine to substantially maintain the output of the gas turbine engine at a
desired output as measured by the output sensor, receive a post-adjustment value of
the engine operating parameter measured by the operating parameter sensor,
determine a future adjusted value of the engine input parameter based at least in part
upon the initial value of the engine input parameter, the pre-adjustment value of the
engine operating parameter, the current adjusted value of the engine input parameter,
and the post-adjustment value of the engine operating parameter, the future adjusted
value being closer to an optimal value of the engine input parameter than the current
adjusted value of the engine input parameter, with respect to the engine operating
parameter, and iteratively adjust the engine input parameter and determine the future
adjusted value of the engine input parameter, using the current adjusted value of a
prior iteration as the initial value for a subsequent iteration and the future adjusted
value from the prior iteration as the current adjusted value for the subsequent
iteration, while operating the gas turbine engine to substantially maintain the output
of the gas turbine engine at the desired output.
An example storage medium according to at least some aspects of the present
disclosure may include non-transitory, machine-readable instructions stored thereon,
which, if executed by one or more processors, may operatively enable a gas turbine
engine control system to vary an engine input parameter while operating a gas turbine
engine associated with the gas turbine engine control system to produce a desired
output, including: measure a pre-adjustment value of an engine operating parameter
while operating the gas turbine engine with the engine input parameter at an initial
value while producing the desired output, adjust the engine input parameter to a
current adjusted value, the current adjusted value differing from the initial value, and
measure a post-adjustment value of the engine operating parameter while operating
the gas turbine engine with the engine input parameter at the adjusted value and while
producing the desired output. Example machine-readable instructions may
operatively enable the gas turbine engine control system to determine a future
adjusted value of the engine input parameter based at least in part upon the initial
value of the engine input parameter, the pre-adjustment value of the engine operating
parameter, the current adjusted value of the engine input parameter, and the postadjustment
value of the engine operating parameter, the future adjusted value being
closer to an optimal value of the engine input parameter than the current adjusted
value of the engine input parameter, with respect to the engine operating parameter.
Example machine-readable instructions may operatively enable the gas turbine engine
control system to iteratively vary the engine input parameter and determine the future
adjusted value of the engine input parameter, using the current adjusted value of a
prior iteration as the initial value for a subsequent iteration and the future adjusted
value from the prior iteration as the current adjusted value for the subsequent
iteration.
BRIEF DESCRIPTION OF THE DRAWINGS
The subject matter for which patent claim coverage is sought is particularly
pointed out and claimed herein. The subject matter and embodiments thereof,
however, may be best understood by reference to the following description taken in
conjunction with the accompanying drawing figures in which:
FIG. 1 is a block diagram of an example gas turbine engine configured
to propel an aircraft;
FIG. 2 is a block diagram of an example gas turbine engine arranged to
drive an electrical generator;
FIG. 3 is a flow diagram of an example method of controlling
operation of a gas turbine engine;
FIG. 4 is a block diagram illustrating an example storage medium; all
in accordance with at least some aspects of the present disclosure.
DETAILED DESCRIPTION
In the following detailed description, reference is made to the accompanying
drawings, which form a part hereof. In the drawings, similar symbols typically
identify similar components, unless context dictates otherwise. The illustrative
embodiments described in the detailed description, drawings, and claims are not
meant to be limiting. Other embodiments may be utilized, and other changes may be
made, without departing from the spirit or scope of the subject matter presented here.
It will be readily understood that the aspects of the present disclosure, as generally
described herein, and illustrated in the figures, can be arranged, substituted,
combined, and designed in a wide variety of different configurations, all of which are
explicitly contemplated and make part of this disclosure.
The present disclosure includes, inter alia, methods and apparatus for
controlling the operation of gas turbine engines and, more specifically, to sensorbased,
performance-seeking methods and apparatus for controlling the operation of
gas turbine engines.
The present disclosure contemplates that it may be impractical to directly
measure an amount of thrust produced by a gas turbine engine, such as a gas turbine
engine propelling an aircraft in flight. Accordingly, some gas turbine engines may
use control systems configured to indirectly ascertain the amount of thrust being
produced. Some such control systems may infer engine thrust from parameters that
can be measured, such as a rotational speed of a fan or an engine pressure ratio (EPR)
(e.g., a ratio of the turbine exhaust stream pressure to the engine inlet total pressure).
For example, some control systems may be configured to modulate fuel flow to a gas
turbine engine as necessary to produce a fan speed corresponding to an aircraft
throttle position. Similarly, some control systems may be configured to modulate fuel
flow to a gas turbine engine as necessary to produce an EPR corresponding to an
aircraft throttle position. Different aircraft throttle positions may correspond with
different fan speeds andlor EPRs, such that advancing the throttle may result in
increasing thrust.
Some example embodiments according to at least some aspects of the present
disclosure may include a control system for a gas turbine engine. An example control
system may include an operating parameter sensor configured to measure a gas
turbine engine operating parameter; an output sensor configured to measure an output
of the gas turbine engine; an actuator configured to modulate an engine input
parameter; a processor operatively coupled to the operating parameter sensor, the
output sensor, and the actuator; and a storage medium operatively coupled to the
processor. The storage medium may include machine-readable instructions stored
thereon.
In some example embodiments according to at least some aspects of the
present disclosure, the machine-readable instructions may be executable by the
processor andlor may operatively enable the processor to control at least some aspects
of the operation of the gas turbine engine. In some example embodiments, the
technical effect is the control at least some aspects of the operation of the gas turbine
engine. For example, the machine-readable instructions may enable the processor to
receive a pre-adjustment value of the engine operating parameter measured by the
operating parameter sensor. The machine-readable instructions may enable the
processor to cause the actuator to adjust the engine input parameter from an initial
value to a current adjusted value while operating the gas turbine engine to
substantially maintain the output of the gas turbine engine at a desired output as
measured by the output sensor. The machine-readable instructions may enable the
processor to receive a post-adjustment value of the engine operating parameter
measured by the operating parameter sensor. The machine-readable instructions may
enable the processor to determine a future adjusted value of the engine input
parameter based at least in part upon the initial value of the engine input parameter,
the pre-adjustment value of the engine operating parameter, the current adjusted value
of the engine input parameter, and the post-adjustment value of the engine operating
parameter, the future adjusted value being closer to an optimal value of the engine
input parameter than the current adjusted value of the engine input parameter, with
respect to the engine operating parameter. The machine-readable instructions may
enable the processor to iteratively adjust the engine input parameter and determine the
future adjusted value of the engine input parameter, using the current adjusted value
of a prior iteration as the initial value for a subsequent iteration and the future
adjusted value from the prior iteration as the current adjusted value for the subsequent
iteration, while operating the gas turbine engine to substantially maintain the output
of the gas turbine engine at the desired output.
As used herein, optimal may refer to a value that is more desirable or
satisfactory than other values. For example and without limitation, an optimal value
of an engine input parameter may refer to a value that corresponds to a minimum fuel
flow rate, a maximum electrical power output, a maximum efficiency, a minimum
exhaust emissions measurement, a minimum heat rate, and/or a minimum power
turbine inlet temperature. As used herein, optimal value may refer a more desirable
or satisfactory value in light of certain constraints, such as limits on particular
operating parameters associated with the engine, regardless of whether the optimal
value is strictly a mathematical minimum or maximum value. For example, gas
turbine engines may be operated within certain operating limits, which may be
established in view of performance, safety, reliability, etc. As used herein, an optimal
value of an engine input parameter may refer to a more desirable or satisfactory value
that still allows the gas turbine engine to operate within the operating limits.
Some example embodiments according to at least some aspects of the present
disclosure may be arranged for use in connection with aircraft engines. FIG. 1 is a
block diagram of an example gas turbine engine (GTE) 100, which may be configured
to propel an aircraft, according to at least some aspects of the present disclosure.
GTE 100 may include a control system 200. Control system 200 may include an
operating parameter sensor 202, which may be configured to measure an operating
parameter comprising, for example, a fuel flow rate of fuel 110 supplied to GTE 100.
Control system 200 may include an output sensor 204, which may be configured to
measure an output comprising, for example, a fan 102 speed of GTE 100 and/or an
EPR of GTE 100. Control system 200 may include an actuator 206, which may be
configured to modulate a position of a variable stator vane 106 in a compressor 104 of
GTE 100, which may comprise an engine input parameter. Some example engines
may comprise a plurality of variable stator vanes, and an input parameter may
comprise one or more positions of one or more variable stator vanes 106. Control
system 200 may include a processor 208, which may be operatively coupled to
operating parameter sensor 202, output sensor 204, andlor actuator 206. Control
system 200 may include a storage medium 210, which may be operatively coupled to
processor 208. Storage medium 2 10 may include machine-readable instructions 2 1 1,
which may be executable by processor 208.
In some example embodiments according to at least some aspects of the
present disclosure, control system 200 may be configured to control the fuel flow rate
of fuel 1 10 to GTE 100 to provide a desired fan 102 speed and/or a desired engine
pressure ratio. The optimal value of the engine input parameter may include a
position of the variable stator vane 106 that corresponds to a minimum fuel flow rate
that substantially maintains the desired output (e.g., desired fan speed and/or desired
engine pressure ratio).
Some example embodiments according to at least some aspects of the present
disclosure may include gas turbine engines configured for electrical power
generation. FIG. 2 is a block diagram of an example gas turbine engine (GTE) 300,
which may be arranged to drive an electrical generator 301, according to at least some
aspects of the present disclosure. GTE 300 may include a low-pressure compressor
302, an intercooler 303, a high-pressure compressor 304, a combustor 308, a highpressure
turbine 3 12, an intermediate-pressure turbine 3 14, and a power turbine 3 16.
Power turbine 3 16 may be operatively coupled to drive electrical generator 30 1.
An example GTE 300 may include a control system 400. Control system 400
may include an operating parameter sensor 402, which may be configured to measure
an operating parameter comprising, for example, an electrical power output of
generator 301, an efficiency of GTE 300, an exhaust emissions parameter (e.g., NO,
concentration), a heat rate of GTE 300, a fuel flow rate of fuel 3 10 supplied to GTE
300, and/or a power turbine inlet temperature associated with a power turbine of GTE
300. Control system 400 may include an output sensor 404, which may be configured
to measure an output parameter comprising, for example, an electrical output of
generator 301 (e.g., alternating current frequency and/or electrical power output).
Control system 400 may include an actuator 406, which may be configured to
modulate an engine input parameter comprising, for example, a high-pressure
compressor inlet temperature associated with a high-pressure compressor of GTE 300
(e.g., by controlling the flow of cooling water 305 through an intercooler 303), a
position of a variable stator vane 306 associated with high-pressure compressor 304, a
position of a variable inlet guide vane 320 associated with booster 302, and/or a flow
rate of injection water 322 supplied to combustor 308. Control system 400 may
include a processor 408, which may be operatively coupled to operating parameter
sensor 402, output sensor 404, and/or actuator 406. Control system 400 may include
a storage medium 410, which may be operatively coupled to processor 408. Storage
medium 4 10 may include machine-readable instructions 4 1 1, which may be
executable by processor 408.
In some example embodiments, engine input parameters may include, without
limitation, variable stators, variable inlet guide vanes, variable bleed or bypass
airflow, cooling airflow to turbine nozzles and/or casings, and/or combustor fuel flow
distribution patterns. In some example embodiments, engine operating parameters
may include, without limitation, thrusvpower output, turbine inlevexhaust
temperatures, exhaust emissions, and/or fuel efficiency.
As used herein, heat rate may refer to a ratio given by fuel flow rate multiplied
by fuel heating value divided by power output.
In some example embodiments according to at least some aspects of the
present disclosure, control system 400 may be configured to control the fuel flow rate
of he1 3 10 to GTE 300 to provide a desired electrical power output of generator 301
andlor a desired power turbine 3 16 speed. The optimal value of the engine input
parameter may correspond to, for example, a maximum electrical power output, a
maximum efficiency, a minimum exhaust emissions measurement (e.g., NO,), a
minimum heat rate, a minimum fuel flow rate, and/or a minimum power turbine 3 16
inlet temperature.
FIG. 3 is a flow diagram of an example method 500 of controlling operation of
a gas turbine engine, according to at least some aspects of the present disclosure.
Method 500 of controlling operation of a gas turbine engine may begin with operation
502, which may include varying an engine input parameter while operating a gas
turbine engine to produce a desired output. Varying the engine input parameter may
include measuring a pre-adjustment value of an engine operating parameter while
operating the gas turbine engine with the engine input parameter at an initial value
while producing the desired output, adjusting the engine input parameter to a current
adjusted value, the current adjusted value differing from the initial value, and/or
measuring a post-adjustment value of the engine operating parameter while operating
the gas turbine engine with the engine input parameter at the adjusted value and while
producing the desired output. Operation 502 may be followed by operation 504,
which may include determining a future adjusted value of the engine input parameter
based at least in part upon the initial value of the engine input parameter, the preadjustment
value of the engine operating parameter, the current adjusted value of the
engine input parameter, and the post-adjustment value of the engine operating
parameter, the future adjusted value being closer to an optimal value of the engine
input parameter than the current adjusted value of the engine input parameter, with
respect to the engine operating parameter. Operation 504 may be followed by
operation 506, which may include iteratively repeating the varying the engine input
parameter operation and the determining the future adjusted value of the engine input
parameter operation, using the current adjusted value of a prior iteration as the initial
value for a subsequent iteration and the future adjusted value from the prior iteration
as the current adjusted value for the subsequent iteration.
In some example methods according to at least some aspects of the present
disclosure, operating the gas turbine engine to produce the desired output may include
controlling a fuel flow rate of fuel to the gas turbine engine to provide the desired
output. The desired output may include a desired value of a parameter associated
with thrust produced by the engine, such as a desired fan speed andlor a desired
engine pressure ratio. The engine operating parameter may include the fuel flow rate.
The engine input parameter may include a position of a variable stator vane associated
with a compressor of the gas turbine engine. The optimal value of the engine input
parameter may include the position of the variable stator vane that corresponds to a
minimum fuel flow rate that produces the desired output.
In some example methods according to at least some aspects of the present
disclosure, the desired output may include a desired electrical output of a generator
operatively coupled to the gas turbine engine. The engine operating parameter may
include an electrical power output of the generator, an efficiency of the gas turbine
engine, an exhaust emissions measurement associated with the gas turbine engine, a
heat rate of the gas turbine engine, a fuel flow rate of fuel supplied to the gas turbine
engine, andlor a power turbine inlet temperature associated with a power turbine of
the gas turbine engine, for example. The engine input parameter may include a highpressure
compressor inlet temperature associated with a high-pressure compressor of
the gas turbine engine, a position of a variable stator vane associated with the highpressure
compressor, a position of a variable inlet guide vane associated with a
booster of the gas turbine engine, and/or an injection water flow rate of injection
water supplied to a combustor of the gas turbine engine, for example. The optimal
value of the engine input parameter may correspond to a maximum electrical power
output, a maximum efficiency, a minimum exhaust emissions measurement, a
minimum heat rate, a minimum fuel flow rate, and/or a minimum power turbine inlet
temperature, for example.
In some example methods according to at least some aspects of the present
disclosure, the desired electrical output may include a desired alternating current
frequency andlor a desired electrical power output.
In some example methods according to at least some aspects of the present
disclosure, a method may include, prior to varying the engine input parameter while
operating the gas turbine engine, determining that the gas turbine engine is operating
in a pseudo-steady-state condition. For example, a gas turbine engine may be
mounted to an aircraft and the pseudo-steady-state condition may include cruise,
climb, andlor descent. As another example, a gas turbine engine may be operatively
coupled to a generator and the pseudo-steady-state condition may include a
substantially constant electrical power output of the generator.
In some example methods according to at least some aspects of the present
disclosure, the engine input parameter may consist of a single parameter, and
determining the future adjusted value of the engine input parameter may include
parametric optimization. Parametric optimization may be performed using any of the
well-known optimization techniques for univariate optimization, such as the bisection
technique or the gradient search.
In some example methods according to at least some aspects of the present
disclosure, the engine input parameter may include a plurality of parameters, and
determining the future adjusted value of the engine input parameter may be performed
using any of the well-known techniques for multivariate optimization including
gradient-based optimization such as conjugate gradient or Newton techniques,
gradient-free search such as Hooke-Jeeves pattern search, or population-based
methods such as genetic algorithms.
Some example methods according to at least some aspects of the present
disclosure may include storing the current adjusted value of the engine input
parameter during a first period of pseudo-steady state operation of the gas turbine
engine and using the stored current adjusted value as the initial value of the engine
input parameter in a second period of pseudo-steady state operation. The first period
of pseudo-steady state operation and the second period of pseudo-steady state
operation may be separated by an intervening period of non-steady-state operation.
FIG. 4 is a block diagram illustrating an example storage medium 600,
according to at least some aspects of the present disclosure. Storage medium 600 may
include one or more sets of non-transitory, machine-readable instructions 602 stored
thereon. Machine-readable instructions 602 may be executable by one or more
processors (e.g., processor 208 andor processor 408), which may operatively enable a
gas turbine engine control system (e.g., control system 200 and/or control system 400)
to perform a method of controlling operation of a gas turbine engine, such as the
method generally described above and illustrated in FIG. 3. In some example
embodiments, storage medium 600 may comprise a computer program product, a
computer-readable medium, andor a recordable medium.
Depending on the desired configuration, processor 208 and/or processor 408
may be of any type including but not limited to a microprocessor, a microcontroller, a
digital signal processor, or any combination thereof. Depending on the desired
configuration, storage medium 210 and/or storage medium 41 0 may include, but is
not limited to, RAM, ROM, EEPROM, flash memory or other memory technology,
CD-ROM, digital versatile disks (DVD) or other optical storage, magnetic cassettes,
magnetic tape, magnetic disk storage or other magnetic storage devices, or any other
medium which may be used to store the desired information and which may be
accessed by processor 208 andor processor 408.
This written description uses examples to disclose the invention, including the
best mode, and also to enable any person skilled in the art to 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.

WE CLAIM
1. A method of controlling operation of a gas turbine engine, the method comprising:
varying an engine input parameter while operating a gas turbine engine to
produce a desired output, varying the engine input parameter comprising
measuring a pre-adjustment value of an engine operating parameter
while operating the gas turbine engine with the engine input parameter at an
initial value while producing the desired output,
adjusting the engine input parameter to a current adjusted value, the
current adjusted value differing from the initial value, and
measuring a post-adjustment value of the engine operating parameter
while operating the gas turbine engine with the engine input parameter at the
adjusted value and while producing the desired output;
determining a future adjusted value of the engine input parameter based at
least in part upon the initial value of the engine input parameter, the pre-adjustment
value of the engine operating parameter, the current adjusted value of the engine input
parameter, and the post-adjustment value of the engine operating parameter, the future
adjusted value being closer to an optimal value of the engine input parameter than the
current adjusted value of the engine input parameter, with respect to the engine
operating parameter; and
iteratively repeating the varying the engine input parameter operation and the
determining the future adjusted value of the engine input parameter operation, using
the current adjusted value of a prior iteration as the initial value for a subsequent
iteration and the future adjusted value from the prior iteration as the current adjusted
value for the subsequent iteration.
2. The method of claim 1, wherein operating the gas turbine engine to produce the
desired output comprises controlling a fuel flow rate of fuel to the gas turbine engine
to provide the desired output, the desired output comprising at least one of a desired
fan speed and a desired engine pressure ratio;
wherein the engine operating parameter comprises the fuel flow rate;
wherein the engine input parameter comprises a position of a variable stator
vane associated with a compressor of the gas turbine engine; and
wherein the optimal value of the engine input parameter comprises the
position of the variable stator vane that corresponds to a minimum fuel flow rate that
produces the desired output.
3. The method of claim 1, wherein the desired output comprises a desired electrical
output of a generator operatively coupled to the gas turbine engine;
wherein the engine operating parameter comprises at least one of an electrical
power output of the generator, an efficiency of the gas turbine engine, an exhaust
emissions measurement associated with the gas turbine engine, a heat rate of the gas
turbine engine, a fuel flow rate of fuel supplied to the gas turbine engine, and a power
turbine inlet temperature associated with a power turbine of the gas turbine engine;
wherein the engine input parameter comprises at least one of a high-pressure
compressor inlet temperature associated with a high-pressure compressor of the gas
turbine engine, a position of a variable stator vane associated with the high-pressure
compressor, a position of a variable inlet guide vane associated with a booster of the
gas turbine engine, and an injection water flow rate of injection water supplied to a
combustor of the gas turbine engine; and
wherein the optimal value of the engine input parameter corresponds to at
least one of a maximum electrical power output, a maximum efficiency, a minimum
exhaust emissions measurement, a minimum heat rate, a minimum fuel flow rate, and
a minimum power turbine inlet temperature.
4. The method of claim 4, wherein the desired electrical output comprises at least one
of a desired alternating current frequency and a desired electrical power output.
5. The method of claim 1, further comprising, prior to varying the engine input
parameter while operating the gas turbine engine, determining that the gas turbine
engine is operating in a pseudo-steady-state condition.
6. The method of claim 5, wherein the gas turbine engine is mounted to an aircraft;
and
wherein the pseudo-steady-state condition comprises one of cruise, climb, or
descent.
7. The method of claim 5, wherein the gas turbine engine is operatively coupled to a
generator; and
wherein the pseudo-steady-state condition comprises a substantially constant
electrical power output of the generator.
8. The method of claim 1,
wherein the engine input parameter consists of a single parameter; and
wherein determining the future adjusted value of the engine input parameter
comprises univariate optimization.
9. The method of claim 1,
wherein the engine input parameter comprises a plurality of parameters; and
wherein determining the future adjusted value of the engine input parameter
comprises multivariate optimization.
10. The method of claim 1, further comprising
storing the current adjusted value of the engine input parameter during a first
period of pseudo-steady state operation of the gas turbine engine; and
using the stored current adjusted value as the initial value of the engine input
parameter in a second period of pseudo-steady state operation;
wherein the first period of pseudo-steady state operation and the second period
of pseudo-steady state operation are separated by an intervening period of non-steadystate
operation.
1 1. A control system for a gas turbine engine, the control system comprising:
an operating parameter sensor operable to measure an engine operating
parameter associated with a gas turbine engine;
an output sensor operable to measure an output of the gas turbine engine;
an actuator operable to modulate an engine input parameter associated with
the gas turbine engine;
a processor operatively coupled to the operating parameter sensor, the output
sensor, and the actuator; and
a storage medium operatively coupled to the processor, the storage medium
comprising machine-readable instructions operatively enabling the processor to:
receive a pre-adjustment value of the engine operating parameter
measured by the operating parameter sensor,
cause the actuator to adjust the engine input parameter from an initial
value to a current adjusted value while operating the gas turbine engine to
substantially maintain the output of the gas turbine engine sensor at a desired
output as measured by the output sensor,
receive a post-adjustment value of the engine operating parameter
measured by the operating parameter sensor,
determine a future adjusted value of the engine input parameter based
at least in part upon the initial value of the engine input parameter, the preadjustment
value of the engine operating parameter, the current adjusted value
of the engine input parameter, and the post-adjustment value of the engine
operating parameter, the W r e adjusted value being closer to an optimal value
of the engine input parameter than the current adjusted value of the engine
input parameter, with respect to the engine operating parameter, and
iteratively adjust the engine input parameter and determine the future
adjusted value of the engine input parameter, using the current adjusted value
of a prior iteration as the initial value for a subsequent iteration and the future
adjusted value from the prior iteration as the current adjusted value for the
subsequent iteration, while operating the gas turbine engine to substantially
maintain the output of the gas turbine engine at the desired output.
12. The control system of claim 11, wherein operating the gas turbine engine to
substantially maintain the output of the gas turbine engine at the desired output
comprises controlling a fuel flow rate of fuel to the gas turbine engine to provide the
desired output, the desired output comprising at least one of a desired fan speed and a
desired engine pressure ratio;
wherein the engine operating parameter comprises the fuel flow rate;
wherein the engine input parameter comprises a position of a variable stator
vane associated with a compressor of the gas turbine engine; and
wherein the optimal value of the engine input parameter comprises the
position of the variable stator vane that corresponds to a minimum fuel flow rate that
substantially maintains the desired output.
13. The control system of claim 1 1, wherein the desired output comprises a desired
electrical output of a generator operatively coupled to the gas turbine engine;
wherein the engine operating parameter comprises at least one of an electrical
power output of the generator, an efficiency of the gas turbine engine, an exhaust
emissions measurement associated with the gas turbine engine, a heat rate of the gas
turbine engine, a fuel flow rate of fuel supplied to the gas turbine engine, and a power
turbine inlet temperature associated with a power turbine of the gas turbine engine;
wherein the engine input parameter comprises at least one of a high-pressure
compressor inlet temperature associated with a high-pressure compressor of the gas
turbine engine, a position of a variable stator vane associated with the high-pressure
compressor, a position of a variable inlet guide vane associated with a booster of the
gas turbine engine, and an injection water flow rate of injection water supplied to a
combustor of the gas turbine engine; and
wherein the optimal value of the engine input parameter corresponds to at
least one of a maximum electrical power output, a maximum efficiency, a minimum
exhaust emissions measurement, a minimum heat rate, a minimum fuel flow rate, and
a minimum power turbine inlet temperature; and
14. The control system of claim 11, wherein the desired electrical output comprises at
least one of a desired alternating current frequency and a desired electrical power
output.
15. The control system of claim 1 1, wherein the machine-readable instructions
operatively enable the gas turbine engine control system to determine that the gas
turbine engine is operating in a pseudo-steady-state condition prior to varying the
engine input parameter.
16. A storage medium comprising non-transitory, machine-readable instructions
stored thereon, which, if executed by one or more processors, operatively enable a gas
turbine engine control system to:
vary an engine input parameter while operating a gas turbine engine
associated with the gas turbine engine control system to produce a desired
output, including
measure a pre-adjustment value of an engine operating parameter
while operating the gas turbine engine with the engine input parameter at an
initial value while producing the desired output,
adjust the engine input parameter to a current adjusted value, the
current adjusted value differing from the initial value, and
measure a post-adjustment value of the engine operating parameter
while operating the gas turbine engine with the engine input parameter at the
adjusted value and while producing the desired output;
determine a future adjusted value of the engine input parameter based at least
in part upon the initial value of the engine input parameter, the pre-adjustment value
of the engine operating parameter, the current adjusted value of the engine input
parameter, and the post-adjustment value of the engine operating parameter, the future
adjusted value being closer to an optimal value of the engine input parameter than the
current adjusted value of the engine input parameter, with respect to the engine
operating parameter; and
iteratively vary the engine input parameter and determine the future adjusted
value of the engine input parameter, using the current adjusted value of a prior
iteration as the initial value for a subsequent iteration and the future adjusted value
from the prior iteration as the current adjusted value for the subsequent iteration.
17. The storage medium of claim 16, wherein operating the gas turbine engine to
produce the desired output comprises controlling a fuel flow rate of fuel to the gas
turbine engine to provide the desired output, the desired output comprising a desired
value of a parameter associated with thrust produced by the gas turbine engine;
wherein the engine operating parameter comprises the fuel flow rate;
wherein the engine input parameter comprises a position of a variable stator
vane associated with a compressor of the gas turbine engine; and
wherein the optimal value of the engine input parameter comprises the
position of the variable stator vane that corresponds to a minimum fuel flow rate that
produces the desired output.
18. The storage medium of claim 16,
wherein the desired output comprises at least one of a desired alternating
current frequency and a desired electrical power output of a generator operatively
coupled to the gas turbine engine;
wherein the engine operating parameter comprises at least one of the electrical
power output of the generator, an efficiency of the gas turbine engine, an exhaust
emissions measurement associated with the gas turbine engine, a heat rate of the gas
turbine engine, a fuel flow rate of fuel supplied to the gas turbine engine, and a power
turbine inlet temperature associated with a power turbine of the gas turbine engine;
wherein the engine input parameter comprises at least one of a high-pressure
compressor inlet temperature associated with a high-pressure compressor of the gas
turbine engine, a position of a variable stator vane associated with the high-pressure
compressor, a position of a variable inlet guide vane associated with a booster of the
gas turbine engine, and an injection water flow rate of injection water supplied to a
combustor of the gas turbine engine; and
wherein the optimal value of the engine input parameter corresponds to at
least one of a maximum electrical power output, a maximum efficiency, a minimum
exhaust emissions measurement, a minimum heat rate, a minimum fuel flow rate, and
a minimum power turbine inlet temperature.
19. The storage medium of claim 16, wherein the machine-readable instructions
operatively enable the gas turbine engine control system to determine that the gas
turbine engine is operating in a pseudo-steady-state condition prior to varying the
engine input parameter.