U.S. patent application number 12/122263 was filed with the patent office on 2009-11-19 for systems involving fiber optic igniters.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to Johannes Eckstein, Herbert Kopecek, Craig Douglas Young.
Application Number | 20090282805 12/122263 |
Document ID | / |
Family ID | 41314826 |
Filed Date | 2009-11-19 |
United States Patent
Application |
20090282805 |
Kind Code |
A1 |
Kopecek; Herbert ; et
al. |
November 19, 2009 |
SYSTEMS INVOLVING FIBER OPTIC IGNITERS
Abstract
A gas turbine engine system comprising, a gas turbine engine
including a combustion area, a laser, a fuel nozzle including a
cavity operative to transmit a fuel into the combustion area, and
an optical fiber engaging the cavity, operative to transmit light
emitted from the laser to the combustion area, wherein the light is
operative to ignite the fuel in the combustion area.
Inventors: |
Kopecek; Herbert;
(Hallbergmoos, DE) ; Eckstein; Johannes;
(Ismaning, DE) ; Young; Craig Douglas;
(Maineville, OH) |
Correspondence
Address: |
GENERAL ELECTRIC COMPANY;GLOBAL RESEARCH
PATENT DOCKET RM. BLDG. K1-4A59
NISKAYUNA
NY
12309
US
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
41314826 |
Appl. No.: |
12/122263 |
Filed: |
May 16, 2008 |
Current U.S.
Class: |
60/39.828 ;
372/6; 431/258 |
Current CPC
Class: |
F02P 23/04 20130101;
F23R 2900/00006 20130101; F23Q 13/00 20130101; F02C 7/264
20130101 |
Class at
Publication: |
60/39.828 ;
431/258; 372/6 |
International
Class: |
F02C 7/264 20060101
F02C007/264; F23Q 7/06 20060101 F23Q007/06; F02P 23/04 20060101
F02P023/04 |
Claims
1. A gas turbine engine system comprising: a gas turbine engine
including a combustion area; a laser; a fuel nozzle including a
cavity operative to transmit a fuel into the combustion area; and
an optical fiber engaging the cavity, operative to transmit light
emitted from the laser to the combustion area, wherein the light is
operative to ignite the fuel in the combustion area.
2. The system of claim 1, wherein the optical fiber includes a
distal portion operative to focus the light in the combustion
area.
3. The system of claim 2, wherein the distal portion is convex
shaped.
4. The system of claim 1, wherein the system further comprises an
optics portion operative to focus the light in the combustion
area.
5. A system for igniting combustible fuel comprising: a laser; and
an optical fiber partially defining a first channel and a second
channel, wherein the first channel is operative to transmit light
emitted from the laser to a combustion area, and the second channel
is communicative with a fuel source and the combustion area and is
operative to introduce fuel from the fuel source into the
combustion area.
6. The system of claim 5, wherein the system further comprises an
end member disposed on a distal portion of the optical fiber
proximate to the laser.
7. The system of claim 5, wherein the system further comprises an
optics portion disposed between the laser and the optical fiber,
the optics portion operative to focus the light.
8. The system of claim 5, wherein the system optical fiber
comprises a photonic crystal.
9. The system of claim 5, wherein the system further comprises a
gas turbine engine.
10. The system of claim 5, wherein the system further comprises an
internal combustion engine.
11. A system for igniting combustible fuel comprising: a laser; and
an optical fiber partially defining a channel communicative with a
fuel source and a combustion area and operative to introduce fuel
from the fuel source into the combustion area, wherein the channel
is further operative to transmit light emitted from the laser to
the combustion area and the light is operative to ignite the
fuel.
12. The system of claim 11, wherein the system further comprises an
end member disposed on a distal portion of the optical fiber
proximate to the laser.
13. The system of claim 11, wherein the system further comprises an
optics portion disposed between the laser and the optical fiber,
the optics portion operative to focus the light.
14. The system of claim 11, wherein the light is operative to
ignite fuel in the channel.
15. The system of claim 11, wherein the light is operative to
ignite fuel in the combustion area.
16. The system of claim 11, wherein the system further comprises a
gas turbine engine.
Description
BACKGROUND OF THE INVENTION
[0001] The present disclosure relates generally to systems
involving igniting fuel, and more particularly to systems involving
igniting fuel with light from a fiber optic system.
[0002] Engines that use combustible fuel such as, for example, gas
turbine engines and internal combustion engines include combustion
areas such as, for example, combustors or cylinder and piston
assemblies that facilitate the conversion of energy from combustion
into mechanical energy. Fuel nozzles are used to introduce atomized
fuel into the combustion areas. The atomized fuel is ignited by an
igniter. Igniters may include, for example, electrical igniters
that create a spark proximate to the atomized fuel, heating
elements that introduce heat to the atomized fuel, and igniters
that introduce a flame in the combustion area.
[0003] For turbine applications, igniters are typically based on
electrical discharge. Electrical discharge igniters need much more
space inside the combustion chamber. The electrodes cannot be
placed inside the cone of the fuel spray since the droplets would
lead to strong deposits on the electrodes and thus reduce the
durability of the igniter. High spark energies, which are needed
for successful ignition, also significantly reduce the lifetime of
the igniter.
[0004] Accordingly, there is a need for improved igniters where
space is limited such as may be the case with turbine
applications.
BRIEF DESCRIPTION OF THE INVENTION
[0005] An exemplary embodiment includes a gas turbine engine system
comprising, a gas turbine engine including a combustion area, a
laser, a fuel nozzle including a cavity operative to transmit a
fuel into the combustion area, and an optical fiber engaging the
cavity, operative to transmit light emitted from the laser to the
combustion area, wherein the light is operative to ignite the fuel
in the combustion area.
[0006] An alternate exemplary embodiment includes a system for
igniting combustible fuel comprising, a laser, and an optical fiber
partially defining a first channel and a second channel, wherein
the first channel is operative to transmit light emitted from the
laser to a combustion area, and the second channel is communicative
with a fuel source and the combustion area and is operative to
introduce fuel from the fuel source into the combustion area.
[0007] Another alternate exemplary embodiment includes a system for
igniting combustible fuel comprising, a laser, and an optical fiber
partially defining a channel communicative with a fuel source and a
combustion area and operative to introduce fuel from the fuel
source into the combustion area, wherein the channel is further
operative to transmit light emitted from the laser to the
combustion area and the light is operative to ignite the fuel.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] These and other features, aspects, and advantages will
become better understood when the following detailed description is
read with reference to the accompanying drawings in which like
characters represent like parts throughout the drawings,
wherein:
[0009] FIG. 1 illustrates of an exemplary embodiment of a system
for igniting combustible fuel.
[0010] FIG. 2 illustrates of an exemplary portion of light from the
system of FIG. 1.
[0011] FIGS. 3-7 illustrate alternate exemplary embodiments of the
system for igniting combustible fuel.
[0012] FIG. 8 illustrates another alternate exemplary embodiment of
the system for igniting combustible fuel including a gas turbine
engine.
[0013] FIG. 9 illustrates another alternate exemplary embodiment of
the system for igniting combustible fuel including an internal
combustion engine.
DETAILED DESCRIPTION OF THE INVENTION
[0014] In the following detailed description, numerous specific
details are set forth in order to provide a thorough understanding
of various embodiments. However, the embodiments may be practiced
without these specific details. In other instances, well known
methods, procedures, and components have not been described in
detail.
[0015] Further, various operations may be described as multiple
discrete steps performed in a manner that is helpful for
understanding the embodiments. However, the order of description
should not be construed as to imply that these operations need be
performed in the order they are presented, or that they are even
order dependent. Moreover, repeated usage of the phrase "in an
embodiment" does not necessarily refer to the same embodiment,
although it may. Lastly, the terms "comprising," "including,"
"having," and the like, as used in the present application, are
intended to be synonymous unless otherwise indicated.
[0016] In one embodiment, laser light is used to create heat in a
fuel, or may be focused to create a micro-spark so as to initiate
the combustion of fuel in a combustion area.
[0017] FIG. 1 illustrates a diagram of an optical fuel igniter
system 100. The optical fuel igniter system 100 includes a laser
source 101 in optical communication with one end of an optical
fiber 103. The other end of the optical fiber is in optical
communication with a fuel. Generally, the fuel is injected into a
combustion area by means of fuel nozzle 105. The laser source is
configured to generate light at a wavelength and power effective to
be absorbed by the fuel and ignite the fuel, or alternatively,
cause a microspark within the fuel to occur. The laser light is
focused at about an area within a combustion area 107 where the
fuel will flow. The fuel is not intended to be limited to any
particular type or kind so long s it is combustible. For example,
the fuel can be a gas or liquid,
[0018] In operation, the fuel nozzle 105 receives fuel from a fuel
source (not shown) and emits the fuel into a combustion area 107.
The fuel may be emitted as atomized fuel 109 such that the fuel may
be easily combusted. The laser 101 emits a light 111 that is
transmitted by the optical fiber 103. When the light 111 enters the
atomized fuel 109, the atomized fuel 109 combusts. FIG. 2
illustrates two examples of the interaction of the light 111 with
the atomized fuel 109 that may cause the atomized fuel to combust.
FIG. 2 includes fuel droplets 201 and light 111. The light 111 may
be absorbed by the fuel droplets 201 causing the temperature of the
fuel droplets 201 to increase. If the increase in the temperature
of the fuel droplets 201 reaches an ignition temperature of the
fuel droplets 201, the droplets will combust. Another cause of
combustion may be a micro-spark. As the light 111 passes through a
fuel droplet 201, it may become focused such that a micro-spark 203
results. The micro-spark may cause the fuel droplets 201 to
combust. Optics (not shown) that include, for example a lens, or a
number of lenses may also be used to focus the light 111 and create
the micro-spark 203. Examples of lasers that may be used for the
laser 101 include, but are not limited to Neodymium-type lasers,
Erbium-type lasers or any other solid state lasers. Semiconductor
lasers may also be used as for the laser 101.
[0019] FIG. 3 illustrates an alternate embodiment of an optical
fuel igniter system 300. The optical fuel igniter system 300 is
similar to the optical fuel igniter system 100 of FIG. 1, however
optical fuel igniter system 300 includes an optical fiber 303 that
has an distal portion 313 that has a convex shape. The convex shape
of the distal portion 313 focuses the light 111 causing a
micro-spark 203 in the atomized fuel 109.
[0020] FIG. 4 illustrates an alternate embodiment of an optical
fuel igniter system 400. The an optical fuel igniter system 400 is
similar to the an optical fuel igniter system 100, and includes an
optics portion 415 comprising, for example, a lenses, a number of
lenses, or similar devices that focus light. The optics portion 415
is disposed between the optical fiber 103 and the combustion area
107. The optics portion 415 focuses light emitted from the optical
fiber such that a micro-spark 203 is created in the atomized fuel
109.
[0021] FIG. 5 illustrates an alternate exemplary embodiment of an
optical fuel igniter system 500. In the illustrated embodiment a
fuel nozzle 505 includes a cavity 519. The cavity 519 is engaged by
the optical fiber 103. In operation, the fuel nozzle receives fuel
from a fuel source 517, and emits the fuel into the combustion area
107 via the cavity 519. The optical fiber 103 transmits light 111
from the laser 101 into the combustion area 107 to ignite the
atomized fuel 109 in the combustion area 107. The optical fiber 103
may also be convex shaped similar to the tip 313 of FIG. 3. In some
embodiments, the optics portion 415 may also be disposed in the
path of the light 111 to focus the light 111.
[0022] FIG. 6 illustrates an alternate embodiment of an optical
fuel igniter system 600. The illustrated embodiment includes the
laser 101, the optics 415, the fuel source 517, the combustion area
107, an end member 627, and an optical fiber 625 having a first
channel 623 and a second channel 621. The optical fiber 625 may be,
for example, a photonic crystal fiber, or other types of optical
fibers that have a number of channels. The end member is disposed
on an end of the optical fiber 625. In operation, fuel is received
from the fuel source 517 and emitted into the combustion area 107
as atomized fuel 109 via the second channel 621. The laser 101
emits light 111 that may be focused with the optics 415 such that
the light 111 causes the atomized fuel 109 to combust. The
illustrated embodiment shows a single second channel 621, however
other embodiment may include a plurality of channels similar to the
second channel 621 that may carry fuel from the fuel source 517 to
the combustion area 107. The end member 627 may be transparent or
semitransparent. The end member 627 seals the first channel 623 and
the second channel 621 such that fuel flows towards the combustion
area 107. The optical fiber 103 may also be convex shaped similar
to the tip 313 of FIG. 3. In some embodiments, the optics portion
415 may also be disposed in the path of the light 111 to focus the
light 111.
[0023] FIG. 7 illustrates an alternate embodiment of an optical
fuel igniter system 700. The optical fuel igniter system 700
includes a hollow core fiber 727 having a channel 729. The hollow
core fiber 727 may be, for example, a fiber having a channel with a
high reflection coating on the surface of the channel 729 and
hollow core photonic crystal fibers. In operation, fuel 731 from
the fuel source 517 enters the channel 729. Light 111 enters the
channel 729 after it has been focused by the optics 415. In
alternate embodiments, and the light 111 may enter the channel 729
without the optics 415 disposed between the laser 101 and the
hollow core fiber 727. The focused light 111 in the channel 729
causes the micro-spark 203 in the channel 729. The micro-spark 203
ignites the fuel 731 in the channel 729, causing a flame (not
shown) to exit the channel 729 and ignite atomized fuel in the
combustion area 107. The optical fiber 103 may also be convex
shaped similar to the tip 313 of FIG. 3. In some embodiments, the
optics portion 415 may also be disposed in the path of the light
111 to focus the light 111.
[0024] FIG. 8 illustrates a side partially cut-away view of an
exemplary embodiment of a gas turbine engine system 800 that
includes a combustor section 801 that partially defines the
combustion area 107. An optical fuel igniter system 802 including
the fuel nozzle 105, the laser 101, and the optical fiber 103 may
be similar to any of the embodiments of the optical fuel igniter
system described above. The gas turbine engine system 800 also
includes a controller 809 that is operative to control the optical
fuel igniter system 802
[0025] In some embodiments components of the optical fuel igniter
system 802 may be located in a remote location from the gas turbine
engine such as, for example, the controller 809 and the laser 101
may be located in an integrated electronic control unit (not
shown).
[0026] In operation, compressed air enters the combustion area 107
and is mixed with fuel from the fuel nozzle 105. The fuel-air
mixture is ignited by light from the laser 101 via the optical
fiber 103 as described in the embodiments above. The resultant
expanding gas exits the combustion area 107 and is converted into
mechanical power.
[0027] FIGS. 1-7 illustrate embodiments of a fuel nozzle that may,
for example, be used as a main fuel nozzle for the combustion area
107. Alternatively, the embodiments described above may be used as
pilot nozzles that are operative to ignite fuel in the combustion
area 107. If used as a pilot nozzle, the embodiments may, for
example, receive fuel from a separate fuel supply line that
services the pilot nozzle.
[0028] FIG. 9 illustrates a side partially cut-away view of an
exemplary embodiment of an internal combustion engine system 900
that includes an optical fuel igniter system having the combustion
area 107, the fuel nozzle 105, the laser 101, and the optical fiber
103. The internal combustion engine system 900 may be similar to
any of the embodiments of the optical fuel igniter system described
above.
[0029] This written description uses examples to disclose the
embodiments, including the best mode, and also to enable practice
of the embodiments, including making and using any devices or
systems and performing any incorporated methods. The patentable
scope of the embodiments is defined by the claims, and may include
other examples. 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.
* * * * *