U.S. patent application number 15/383043 was filed with the patent office on 2018-08-16 for system and method for regulating velocity of gases in a turbomachine.
The applicant listed for this patent is General Electric Company. Invention is credited to Scott Richard Baker, Harold Lamar Jordan, JR., Bradly Aaron Kippel, Rex Allen Morgan, Kamlesh Mundra, Raymond Pang.
Application Number | 20180230849 15/383043 |
Document ID | / |
Family ID | 63104485 |
Filed Date | 2018-08-16 |
United States Patent
Application |
20180230849 |
Kind Code |
A1 |
Kippel; Bradly Aaron ; et
al. |
August 16, 2018 |
System and Method for Regulating Velocity of Gases in a
Turbomachine
Abstract
The present disclosure is direct to a system for regulating a
velocity of gases in a turbomachine. The system includes an exhaust
section of the turbomachine. The system also includes a damper
having an actuator and a restriction. The damper is positioned
within the exhaust section and is operable to adjust the velocity
of the gases based on a position of the restriction. The system
further includes a controller communicatively coupled to the
damper. The controller is configured to control the position of the
restriction to regulate the velocity of the gases relative to a
predetermined velocity range.
Inventors: |
Kippel; Bradly Aaron;
(Greenville, SC) ; Pang; Raymond; (Glenville,
NY) ; Baker; Scott Richard; (Greenville, SC) ;
Jordan, JR.; Harold Lamar; (Greenville, SC) ; Morgan;
Rex Allen; (Simpsonville, SC) ; Mundra; Kamlesh;
(Clifton Park, NY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
63104485 |
Appl. No.: |
15/383043 |
Filed: |
December 19, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2270/331 20130101;
F02C 9/20 20130101; F01D 25/30 20130101; F05D 2270/313 20130101;
F05D 2270/306 20130101; F05D 2220/32 20130101; F01D 17/14
20130101 |
International
Class: |
F01D 17/14 20060101
F01D017/14; F02C 9/20 20060101 F02C009/20 |
Claims
1. A system for regulating a velocity of gases in a turbomachine,
the system comprising: an exhaust section of the turbomachine; a
damper including an actuator and a restriction, the damper being
positioned within the exhaust section and operable to adjust the
velocity of the gases based on a position of the restriction; and a
controller communicatively coupled to the damper, the controller
being configured to control the position of the restriction to
regulate the velocity of the gases relative to a predetermined
velocity range.
2. The system of claim 1, wherein the damper is operable to adjust
the velocity of the gases while not reducing a flow rate of air
through the turbomachine.
3. The system of claim 1, wherein the controller is configured to
control the position of the restriction when the velocity of the
gases exceeds a maximum velocity threshold such that the velocity
of the gases is reduced.
4. The system of claim 1, wherein the controller is configured to
control the position of the restriction when the velocity of the
gases is below a minimum velocity threshold such that the velocity
of the gases is increased.
5. The system of claim 1, wherein the actuator moves the
restriction to a restricted position when the velocity of the gases
exceeds a maximum velocity threshold, and wherein the actuator
moves the restriction to an unrestricted position when the velocity
of the gases is below a minimum velocity threshold.
6. The system of claim 1, wherein the restriction is moveable
between an unrestricted position and a restricted position to
regulate the velocity of the gases relative to the predetermined
velocity range.
7. The system of claim 6, wherein the restriction is moveable to
one or more discrete intermediate positions located between the
unrestricted position and the restricted position to regulate the
velocity of the gases relative to the predetermined velocity
range.
8. The system of claim 1, further comprising: a sensor in operative
association with the turbomachine to detect an operating parameter
associated with the velocity of the gases through the turbomachine,
wherein the controller is configured to control the position of the
restriction based on measurement signals received from the
sensor.
9. The system of claim 8, wherein the sensor is in operative
association with the exhaust section.
10. The system of claim 8, wherein the operating parameter is a
pressure of exhaust gases, an ambient temperature, a load on the
turbomachine, a fuel flow rate, or a velocity of the exhaust
gases.
11. The system of claim 1, wherein the restriction comprises a
moveable door.
12. The system of claim 1, wherein the turbomachine comprises a gas
turbine engine.
13. A method for regulating a velocity of gases in a turbomachine,
the method comprising: detecting, with a sensor in operative
association with the turbomachine, an operating parameter
associated with the velocity of the gases through the turbomachine;
receiving, with a controller, a measurement signal from the sensor,
the signal being associated with the operating parameter; and
controlling, with the controller, a position of a restriction of a
damper positioned within an exhaust section of the turbomachine
based on the measurement signal to regulate the velocity of the
gases relative to a predetermined velocity range, wherein the
damper is operable to adjust the velocity of the gases based on a
position of the restriction.
14. The method of claim 13, wherein the damper is operable to
adjust the velocity of the gases while not reducing a mass flow
rate of air through the turbomachine.
15. The method of claim 13, further comprising: controlling, with
the controller, the position of the restriction when the velocity
of the gases exceeds a maximum velocity threshold such that the
velocity of the gases is reduced.
16. The method of claim 13, further comprising: controlling, with
the controller, the position of the restriction when the velocity
of the gases is below a minimum velocity threshold such that the
velocity of the gases is increased.
17. The method of claim 13, further comprising: moving, with an
actuator of the damper, the restriction to a restricted position
when the velocity of the gases exceeds a maximum velocity
threshold; and moving, with the actuator of the damper, the
restriction to an unrestricted position when the velocity of the
gases is below a minimum velocity threshold.
18. The method of claim 13, further comprising: moving, with an
actuator of the damper, the restriction between an unrestricted
position and a restricted position to regulate the velocity of the
gases relative to the predetermined velocity range.
19. The method of claim 18, further comprising: moving, with the
actuator of the damper, the restriction to one or more intermediate
positions located between the unrestricted position and the
restricted position to regulate the velocity of the gases relative
to the predetermined velocity range.
20. The method of claim 13, wherein controlling the position of the
restriction comprises controlling, with an actuator of the damper,
a position of a moveable door.
Description
FIELD
[0001] The present disclosure generally relates to turbomachines.
More particularly, the present disclosure relates systems and
methods for regulating velocity of gases in turbomachines.
BACKGROUND
[0002] A gas turbine engine generally includes an inlet section, a
compressor, one or more combustors, a turbine, and an exhaust
section. Air enters the gas turbine engine through the inlet
section. The compressor progressively increases the pressure the
air therein and supplies this compressed air to the combustors. The
compressed air and a fuel (e.g., natural gas) mix and burn within
the combustors to generate high pressure and high temperature
combustion gases. The combustion gases flow from the combustors
into the turbine where they expand to produce work. For example,
expansion of the combustion gases in the turbine may rotate a rotor
shaft connected, e.g., to a generator to produce electricity. The
combustion gases then exit the gas turbine engine via the exhaust
section as exhaust gases.
[0003] Various gas turbine engine components may be exposed to the
flow of combustion and exhaust gases. For example, vanes and rotor
blades in the turbine may be exposed to the flow of combustion
gases. In this respect, there may be a limit to the velocity of the
gases to which certain gas turbine components, such as the vanes
and rotors blades, may be exposed. These limits may be exceeded
when the ambient air entering the inlet section is relatively cold.
Furthermore, the velocity limits may also be exceeded when the
inlet section conditions the air entering the gas turbine engine in
a manner that lowers the temperature thereof.
[0004] Conventional systems and methods regulating the velocity the
gases flowing through the gas turbine engine generally do so by
impeding or restricting the air flow entering the inlet section.
Impeding the flow of air entering the inlet section reduces the
mass flow rate of air through the gas turbine engine, which results
in a relatively large impact on the overall performance and
efficiency of the gas turbine engine.
BRIEF DESCRIPTION
[0005] Aspects and advantages of the technology will be set forth
in part in the following description, or may be obvious from the
description, or may be learned through practice of the
technology.
[0006] In one aspect, the present disclosure is directed to a
system for regulating a velocity of gases in a turbomachine. The
system includes an exhaust section of the turbomachine. The system
also includes a damper having an actuator and a restriction. The
damper is positioned within the exhaust section and is operable to
adjust the velocity of the gases based on a position of the
restriction. The system further includes a controller
communicatively coupled to the damper. The controller is configured
to control the position of the restriction to regulate the velocity
of the gases relative to a predetermined velocity range.
[0007] In another aspect, the present disclosure is directed to a
method for regulating a velocity of gases in a turbomachine. The
method includes detecting, with a sensor in operative association
with the turbomachine, an operating parameter associated with the
velocity of the gases flowing through the turbomachine. The method
also includes receiving, with a controller, a measurement signal
from the sensor. The signal is associated with the operating
parameter. The method further includes controlling, with the
controller, a position of a restriction of a damper positioned
within an exhaust section of the turbomachine based on the
measurement signal to regulate the velocity of the gases relative
to a predetermined velocity range. The damper is operable to adjust
the velocity of the gases based on a position of the
restriction.
[0008] These and other features, aspects and advantages of the
present technology will become better understood with reference to
the following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the technology and,
together with the description, serve to explain the principles of
the technology.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] A full and enabling disclosure of the present technology,
including the best mode thereof, directed to one of ordinary skill
in the art, is set forth in the specification, which makes
reference to the appended FIGS., in which:
[0010] FIG. 1 is a schematic view of an exemplary gas turbine
engine in accordance with embodiments of the present
disclosure;
[0011] FIG. 2 is a front view of an exemplary damper in accordance
with embodiments of the present disclosure;
[0012] FIG. 3 is schematic view of a system for regulating a
velocity of gases within a gas turbine engine in accordance with
embodiments of the present disclosure; and
[0013] FIG. 4 is flow chart illustrating a method for regulating a
velocity of gases within a gas turbine engine in accordance with
embodiments of the present disclosure.
[0014] Repeat use of reference characters in the present
specification and drawings is intended to represent the same or
analogous features or elements of the present technology.
DETAILED DESCRIPTION
[0015] Reference will now be made in detail to present embodiments
of the technology, one or more examples of which are illustrated in
the accompanying drawings. The detailed description uses numerical
and letter designations to refer to features in the drawings. Like
or similar designations in the drawings and description have been
used to refer to like or similar parts of the technology. As used
herein, the terms "first", "second", and "third" may be used
interchangeably to distinguish one component from another and are
not intended to signify location or importance of the individual
components. The terms "upstream" and "downstream" refer to the
relative direction with respect to fluid flow in a fluid pathway.
For example, "upstream" refers to the direction from which the
fluid flows, and "downstream" refers to the direction to which the
fluid flows.
[0016] Each example is provided by way of explanation of the
technology, not limitation of the technology. In fact, it will be
apparent to those skilled in the art that modifications and
variations can be made in the present technology without departing
from the scope or spirit thereof. For instance, features
illustrated or described as part of one embodiment may be used on
another embodiment to yield a still further embodiment. Thus, it is
intended that the present technology covers such modifications and
variations as come within the scope of the appended claims and
their equivalents.
[0017] Although an industrial or land-based gas turbine is shown
and described herein, the present technology as shown and described
herein is not limited to a land-based and/or industrial gas turbine
unless otherwise specified in the claims. For example, the
technology as described herein may be used in any type of
turbomachine including, but not limited to, aviation gas turbines
(e.g., turbofans, etc.), steam turbines, and marine gas
turbines.
[0018] Now referring to the drawings, wherein identical numerals
indicate the same elements throughout the figures, FIG. 1
schematically illustrates an exemplary gas turbine engine 10. As
depicted therein, the gas turbine engine 10 includes an inlet
section 12, a compressor 14, one or more combustors 16, a turbine
18, and an exhaust section 20. The compressor 14 and the turbine 18
may be coupled by a shaft 22, which may be a single shaft or a
plurality of shaft segments coupled together. The shaft 22 may also
couple the turbine 18 to a generator 24.
[0019] During operation, the gas turbine engine 10 produces
mechanical rotational energy, which may, e.g., be used to drive the
generator 24. More specifically, air 26 enters the inlet section 12
of the gas turbine engine 10. From the inlet section 12, the air 26
flows into the compressor 14, where one or more rows of compressor
rotor blades 28 progressively compress the air 26 to provide
compressed air 30 to each of the combustors 16. The compressed air
30 in the combustors 16 mixes with a fuel 32 (e.g., natural gas)
supplied by a fuel supply 34. The resulting fuel-air mixture burns
in the combustors 16 to produce high temperature and high pressure
combustion gases 36 From the combustors 16, the combustion gases 36
flow through the turbine 18, where one or more rows of turbine
rotor blades 38 extract kinetic and/or thermal energy therefrom.
This energy extraction rotates the shaft 22, thereby creating
mechanical rotational energy for powering the compressor 14 and/or
the generator 24. The combustion gases 36 exit the gas turbine
engine 10 through the exhaust section 20 as exhaust gases 40.
[0020] In the embodiment shown in FIG. 1, the exhaust section 20
includes a heat recovery steam generator (HRSG) 42 or other similar
heat exchanger. More specifically, an exhaust duct 44 may fluidly
couple the HRSG 42 and the turbine 18. In this respect, the exhaust
gases 40 exiting the gas turbine engine 10 may heat a fluid 46
(e.g., steam) for use a steam turbine or other turbomachine (not
shown). After flowing through the HRSG 42, the exhaust gases 40 may
exit the exhaust system through an exhaust stack 48. In alternate
embodiments, however, the exhaust section 20 may not include the
HRSG 42. In this respect, the exhaust gases 40 may flow through the
exhaust duct 44 and directly into the ambient air. That is, certain
embodiments of the exhaust section 20 may only include the exhaust
duct 44 or other similar conduit through which the exhaust gases 40
may flow from the turbine 18 to the ambient air.
[0021] The exhaust section 20 also includes a damper 50. In the
embodiment shown in FIG. 1, the damper 50 is positioned in the
exhaust duct 44 between the turbine 18 and the HRSG 42 (i.e.,
upstream of the HRSG 42). In alternate embodiments, however, the
damper 50 may be positioned in the HRSG 42, the exhaust stack 48
(i.e., downstream of the HRSG 42), or any other suitable position
in the exhaust section 20.
[0022] The damper 50 may adjustably impede or restrict the flow of
the exhaust gases 40 through the exhaust duct 44. As shown in FIG.
2, the damper 50 generally includes an actuator 52 and one or more
adjustable restrictions 54. More specifically, the actuator 52
moves the restrictions 54 between two or more positions within the
exhaust duct 44. Any suitable combination of gears, sprockets,
chains, linkages, or other components may transmit motion from the
actuator 52 to the restriction 54. The restrictions 54 may impede
the flow of the exhaust gases 40 to various extents based on the
position thereof. As will be discussed in greater detail below, a
velocity of the gases 36, 40 within the gas turbine engine 10 may
be regulated based on the position of the restrictions 54.
[0023] In the exemplary embodiment shown in FIG. 2, the damper 50
is a guillotine damper. In such embodiments, the restriction 54 is
a vertically moveable door 56. In this respect, the actuator 52
that adjusts the vertical position of the door 56. As shown, a pair
of pinion gears 58 are coupled to the actuator 52 (e.g., a
pneumatic or hydraulic cylinder, an electric motor, etc.). The
pinion gears 58 engage corresponding racks 60 coupled to the door
56. During operation of the damper 50, the actuator 52 rotates the
pinion gears 58, which vertically move the racks 60 and the door
56. In alternate embodiments, the restriction 54 may be one or more
louvers, diverters, butterfly valves, poppets, irising orifices, or
any other suitable type of restriction. Furthermore, the damper 50
may be any suitable structure or device that may adjustably impedes
or restricts the flow of the exhaust gases 40 through the exhaust
duct 44.
[0024] Referring again to FIG. 1, the gas turbine engine 10 may
include various sensors. As shown, for example, the gas turbine
engine 10 may include a load sensor 62, an ambient temperature
sensor 64, a fuel flow sensor 66, an exhaust pressure sensor 68,
and an exhaust gas velocity sensor 69. In alternate embodiments,
however, the gas turbine engine 10 may include only some of the
sensors 62, 64, 66, 68, 69 or none of the sensors 62, 64, 66, 68,
69. Furthermore, the gas turbine engine 10 may include other
sensors in addition to or lieu of the sensors 62, 64, 66, 68,
69.
[0025] The load sensor 62 that detects a load on the gas turbine
engine 10. In the embodiment shown in FIG. 1, the load on the gas
turbine engine 10 is the generator 24. In this respect, the load
sensor 62 may be operatively associated with the generator 24. As
such, the load sensor 62 may be an ammeter that detects the amount
of electricity produced by the generator 24. In alternate
embodiments, the load sensor 62 may be operatively associated with
the shaft 22. In this respect, the load sensor 62 may be a Hall
Effect sensor that detects a rotational speed of the shaft 22. The
rotational speed of the shaft 22 may be used to determine the load
of the gas turbine engine 10. Nevertheless, the load sensor 62 may
be any suitable sensor for detecting the load on the gas turbine
engine 10.
[0026] The ambient temperature sensor 64 detects a temperature of
ambient air (e.g., the air 26 entering the inlet section 12). In
this respect, the ambient temperature sensor 64 is exposed to the
ambient air. The ambient temperature sensor 64 may be a thermistor,
thermocouple, or any other suitable temperature sensor.
[0027] The fuel flow sensor 66 detects a flow rate or pressure of
the fuel 32 flowing from the fuel supply 34 to the combustors 16.
As shown in FIG. 1, the fuel flow sensor 66 is operatively
associated with and in fluid communication with the fuel 32 flowing
to the combustors 16. For example, the fuel flow sensor 66 may be
an orifice meter, a turbine flowmeter, a vortex flowmeter, or any
other suitable type of fuel flow sensor.
[0028] The exhaust pressure sensor 68 detects a pressure of the
exhaust gases 40 within the exhaust section 20. In this respect,
the exhaust pressure sensor 68 is operatively associated with the
exhaust section 20 and in fluid communication with the exhaust
gases 40. In the embodiment shown in FIG. 1, the exhaust pressure
sensor 68 is positioned within the exhaust duct 44. In alternate
embodiments, however, the exhaust pressure sensor 68 may be
positioned in any suitable location within the exhaust section 20.
The exhaust pressure sensor 68 may be a diaphragm pressure
transducer or any other suitable type of pressure sensor.
[0029] The exhaust velocity sensor 69 detects a velocity of the
exhaust gases 40 within the exhaust section. In this respect, the
exhaust velocity sensor 69 is exposed to the exhaust gases 40. The
exhaust velocity sensor 69 may be a flow meter, a pitot tube, or
any other suitable velocity sensor.
[0030] FIG. 3 illustrates a system 100 for regulating the velocity
of the gases 36, 40 within the gas turbine engine 10 in accordance
with embodiments of the present disclosure. As will be discussed in
greater detail below, the system 100 controls the position of the
restrictions 54 of the damper 50 to regulate the velocity of the
gases 36, 40 relative to a predetermined velocity range.
[0031] As shown, the system 100 includes a sensor 102 for detecting
an operating parameter of the gas turbine engine 10. The operating
parameter is associated with or is indicative of the velocity of
the gases 36, 40. For example, the operating parameter may the load
on the gas turbine engine 10, the temperature of ambient air, the
flow rate or pressure of the fuel 32, the pressure of the exhaust
gases 40, or the velocity of the exhaust gases 40. In this respect,
the sensor 102 may correspond to the load sensor 62, the ambient
temperature sensor 64, the fuel flow sensor 66, the exhaust
pressure sensor 68, or the exhaust velocity sensor 69. In alternate
embodiments, the sensor 102 may correspond to sensors not shown in
FIG. 1 and the operating parameter may be any suitable operating
parameter. Although only one sensor 102 is shown in FIG. 3, the
system 100 may include more sensors.
[0032] The system 100 also includes a controller 104
communicatively coupled to one or more components of the system 100
and/or the gas turbine engine 10, such as the sensor 102 and the
damper 50. The controller 104 may also be communicatively coupled
to any other sensors included in the system 100. In certain
embodiments, the controller 104 may correspond to a turbine
controller (not shown) of the gas turbine engine 10. Alternately,
the controller 104 may be a separate processing device of the gas
turbine engine 10 in addition to the turbine controller.
[0033] In general, the controller 104 may comprise any suitable
processor-based device known in the art, such as a computing device
or any suitable combination of computing devices. In this respect,
the controller 104 may include one or more processor(s) 106 and
associated memory device(s) 108 configured to perform a variety of
computer-implemented functions. As used herein, the term
"processor" refers not only to integrated circuits referred to in
the art as being included in a computer, but also refers to a
controller, a microcontroller, a microcomputer, a programmable
logic controller (PLC), an application specific integrated circuit,
and other programmable circuits. Additionally, the memory device(s)
108 of the controller 104 may generally comprise memory element(s)
including, but not limited to, computer readable medium (e.g.,
random access memory (RAM)), computer readable non-volatile medium
(e.g., a flash memory), a floppy disk, a compact disc-read only
memory (CD-ROM), a magneto-optical disk (MOD), a digital versatile
disc (DVD) and/or other suitable memory elements. Such memory
device(s) 108 may generally be configured to store suitable
computer-readable instructions that, when executed by the
processor(s) 106, cause the controller 104 to perform various
computer-implemented functions, such as one or more aspects of the
method 200 described below with reference to FIG. 4. In addition,
the controller 104 may also include various other suitable
components, such as a communications circuit or module, one or more
input/output channels, a data/control bus, and/or the like.
[0034] As indicated above, the controller 104 is communicatively
coupled to the sensor 102, e.g., via a wired or wireless
connection. In this respect, the sensor 102 may transmit
measurement signals 110 associated with the operating parameter to
the controller 104. The controller 104 may then be configured to
determine the velocity of the gases 36, 40 based on the measurement
signals 110 received from the sensor 102. For example, the
controller 104 may include a look-up table or suitable mathematical
formula stored within its memory 108 that correlates the operating
parameter measurements to the velocity of the gases 36, 40. In some
embodiments, the velocity of the gases 36, 40 may be based on
multiple operating parameters in embodiments of the system 100
having multiple sensors.
[0035] The controller 104 may also be communicatively coupled to
the damper 50, e.g., via a wired or wireless connection. In this
respect, the controller 104 may transmit control signals 112 to the
damper 50. The control signals 112 indicate the position to the
actuator 52 should move the restriction 54. As will be discussed in
greater detail below, the controller 104 may generate the control
signals 112 based on the measurement signals 110 received from the
sensor 102.
[0036] The controller 104 is configured to control the position of
the restrictions 54 to regulate the velocity of gases 36, 40
relative to a predetermined velocity range. For example, upon
receiving the measurement signals 110 from the sensor 102, the
controller 104 may be configured to compare the monitored velocity
to a predetermined velocity range defined for the gases 36, 40.
When the monitored velocity exceeds a maximum velocity or threshold
for the velocity range, the velocity of the gases 36, 40 may be too
high. In such instances, the controller 104 may be configured to
control (e.g., via the control signals 112) the position of the
restriction 54 such that the velocity of the gases 36, 40 is
reduced. When the monitored velocity falls below a minimum velocity
or threshold for the velocity range, the velocity of gases 36, 40
may be too low. In such instances, the controller 104 may be
configured to control (e.g., via the control signals 112) the
position of the restrictions 54 such that the velocity of the gases
36, 40 is increased.
[0037] The embodiment of the damper 50 shown in FIGS. 1 and 2, the
restriction 54 is the vertically moveable door 56. In this respect,
the actuator 52 may move the door 56 downward to reduce the
velocity of the gases 36, 40. More specifically, moving the door 56
downward increases the extent to which the door 56 impedes the flow
of the exhaust gases 40. This increases a back pressure in gas
turbine engine 10, which decreases the velocity of the gases 36,
40. Conversely, the actuator 52 may move the door 56 upward to
increase the velocity of the gases 36, 40. In particular, moving
the door 56 upward decreases the extent to which the door 56
impedes the flow of the exhaust gases 40. This decreases the back
pressure in gas turbine engine 10, which decreases the velocity of
the exhaust gases 40.
[0038] The restriction 54 may be moveable between an unrestricted
position and a restricted position to regulate the velocity of the
gases 36, 40. In general, the restrictions 54 provide no or
negligible impedance of the exhaust gases 40 when in the
unrestricted position. Conversely, the restrictions 54 impede of
the exhaust gases 40 to the maximum extent when in the restricted
position. FIG. 2, for example, shows the door 56 is in the
unrestricted position. That is, the door 56 is in the restricted
position when the door 56 is in the highest position. Dashed lines
114 indicate the restricted position of the door 56. In this
respect, the door 56 is in the unrestricted position when the door
56 is in the lowest position.
[0039] In certain embodiments, the restrictions 54 may be
positioned in either the restricted position or the unrestricted
position. More specifically, the actuator 52 may move the
restriction 54 to the restricted position when the velocity of the
gases 36, 40 exceeds the maximum velocity threshold. The actuator
52 may move the restriction 54 to the unrestricted position when
the velocity of the gases 36, 40 drops below the maximum velocity
threshold. Alternately, the actuator 52 may move the restriction 54
to the unrestricted position only when the velocity of the gases
36, 40 drops below the minimum velocity threshold.
[0040] In other embodiments, the restrictions 54 may be positioned
the unrestricted position, the restricted position, or one or more
intermediate positions located between the unrestricted and
restricted positions. The intermediate positions may be discrete
positions located between the unrestricted and restricted
positions. As shown in FIG. 2, for example, the door 56 may be
positioned at different intermediate positions respectively
identified by dashed lines 116 and 118. Alternately, the
intermediate positions may be any positions located between the
unrestricted and restricted positions.
[0041] The controller 104 may be configured to determine which of
the unrestricted, the restricted, or intermediate positions in
which the restriction 54 should be located based on a look-up table
stored on the memory 108. More specifically, the look-up table may
include a first table of values and a second table of values. Each
value in the first table may correspond to the velocity of the
gases 36, 40. Similarly, each value in the second table may
correspond to one of the unrestricted, the restricted, or
intermediate positions. As such, the controller 104 may select a
first value from the first table of values based on the velocity of
the gases 36, 40. The controller 104 may then determine the
corresponding position of the restriction 54 from the second table
based on the selected first value. In alternate embodiments,
however, controller 104 may be configured to determine the position
of the restriction 54 using one or more mathematical functions.
[0042] FIG. 4 illustrates a method 200 for regulating the velocity
of the gases 36, 40 within of the gas turbine engine 10 in
accordance with embodiments of the present disclosure.
[0043] In step 202, the operating parameter associated with the
velocity of the gases 36, 40 is detected. For example, the sensor
102 may detect the operating parameter and generate the measurement
signals 110 indicative of the operating parameter. As mentioned
above, the operating parameter may be the load on the gas turbine
engine 10, the temperature of ambient air, the flow rate or
pressure of the fuel 32, or the pressure of the exhaust gases
40.
[0044] Additionally, in step 204, the measurement signals 110 are
received. For example, as indicated above, the controller 104 may
be communicatively coupled to the sensor 102. As such, the
measurement signals 110 transmitted from the sensor 102 may be
received by the controller 104 for subsequent processing of the
associated operating parameter measurements.
[0045] Furthermore, in step 206, the position of the restriction 54
is controlled based on the measurement signals 110 to regulate the
velocity of the gases 36, 40 relative to a predetermined velocity
range. For example, the controller 104 may be configured to control
the position of the restriction 54. As described, the controller
104 may be configured to control the position of the restriction 54
when the velocity of the gases 36, 40 exceeds the maximum velocity
threshold such that the velocity of the gases 36, 40 is reduced. In
such instances, the actuator 52 may move the restriction 54 (e.g.,
the door 56) to the intermediate positions or the restricted
position. The controller 104 may also be configured to control the
position of the restriction 54 when the velocity of the gases 36,
40 falls below the minimum velocity threshold such that the
velocity of the gases 36, 40 is increased. In such instances, the
actuator 52 may move the restriction 54 (e.g., the door 56) to the
intermediate positions or the unrestricted position.
[0046] As discussed above, the system 100 and method 200 disclosed
herein regulates the velocity the gases 36, 40 flowing through the
gas turbine engine 10 by adjustably impeding or restricting the
flow of exhaust gases 40 through the exhaust section 20. In this
respect, and unlike with conventional systems and methods, the
system 100 and method 200 do not necessarily restrict the mass flow
rate of air through the gas turbine engine 10 when
controlling/restricting the flow of exhaust gases 40. As such, the
system 100 and method 200 provide a smaller impact on the
performance of the gas turbine engine 10 than conventional systems
and methods, which restrict the flow of the air 26 entering the
inlet portion 12. In this respect, the gas turbine engine 10
provides better performance and efficiency than conventional gas
turbine engines.
[0047] This written description uses examples to disclose the
technology, including the best mode, and also to enable any person
skilled in the art to practice the technology, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the technology 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 include 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 language of the claims.
* * * * *