U.S. patent application number 13/566459 was filed with the patent office on 2014-02-06 for fuel nozzle assembly and methods of assembling same.
The applicant listed for this patent is Oscar Flores, Elias Marquez, Lucas John Stoia. Invention is credited to Oscar Flores, Elias Marquez, Lucas John Stoia.
Application Number | 20140033721 13/566459 |
Document ID | / |
Family ID | 48951612 |
Filed Date | 2014-02-06 |
United States Patent
Application |
20140033721 |
Kind Code |
A1 |
Marquez; Elias ; et
al. |
February 6, 2014 |
FUEL NOZZLE ASSEMBLY AND METHODS OF ASSEMBLING SAME
Abstract
A fuel nozzle assembly for use with a turbine engine is
provided. The fuel nozzle assembly includes a tube that is
configured to channel at least a first type of fuel through the
turbine engine. A flow member includes a first end portion and a
second end portion that is removably coupled to the tube such that
the flow member is severally removable from the tube to enable a
plurality of different types of fuel to be channeled through the
turbine engine for operation of the turbine engine.
Inventors: |
Marquez; Elias; (Queretaro,
MX) ; Stoia; Lucas John; (Taylors, SC) ;
Flores; Oscar; (Queretaro, MX) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Marquez; Elias
Stoia; Lucas John
Flores; Oscar |
Queretaro
Taylors
Queretaro |
SC |
MX
US
MX |
|
|
Family ID: |
48951612 |
Appl. No.: |
13/566459 |
Filed: |
August 3, 2012 |
Current U.S.
Class: |
60/734 ;
29/890.09 |
Current CPC
Class: |
Y10T 29/494 20150115;
F23R 2900/00017 20130101; F23N 2235/26 20200101; F23R 3/286
20130101 |
Class at
Publication: |
60/734 ;
29/890.09 |
International
Class: |
F23R 3/28 20060101
F23R003/28; B21D 51/16 20060101 B21D051/16 |
Claims
1. A fuel nozzle assembly for use with a turbine engine, said fuel
nozzle assembly comprising: a tube configured to channel at least a
first type of fuel through the turbine engine; and a flow member
comprising a first end portion and a second end portion that is
removably coupled to said tube such that said flow member is
severally removable from said tube to enable a plurality of
different types of fuel to be channeled through the turbine engine
for operation of the turbine engine.
2. A fuel nozzle assembly in accordance with claim 1, wherein said
flow member comprises an exterior tube and an interior tube that is
integrally formed within said exterior tube.
3. A fuel nozzle assembly in accordance with claim 2, wherein said
interior tube comprises an interior tube first end portion, an
interior tube second end portion, and a plurality of openings
extending from said interior tube first end portion to said
interior tube second end portion.
4. A fuel nozzle assembly in accordance with claim 2, wherein said
interior tube comprises a channel defined therein and is configured
to channel fluid therethrough.
5. A fuel nozzle assembly in accordance with claim 4, wherein said
tube comprises a channel defined therein, said interior tube
channel is concentrically aligned with said tube channel when said
flow member is coupled to said tube.
6. A fuel nozzle assembly in accordance with claim 1, wherein said
flow member second end portion comprises a plurality of
grooves.
7. A fuel nozzle assembly in accordance with claim 6, wherein said
tube comprises a tube end portion that is configured to receive
said plurality of grooves therein.
8. A turbine engine comprising: a compressor; a combustion assembly
coupled to said compressor, wherein said combustion assembly
comprises at least one combustor; at least one fuel nozzle assembly
coupled within said at least one combustor, said at least one fuel
nozzle assembly comprises: a tube that is configured to channel at
least a first type of fuel through said turbine engine; and a flow
member comprising a first end portion and a second end portion that
is removably coupled to said tube such that said flow member is
severally removable from said tube to enable a plurality of
different types of fuel to be channeled through said turbine engine
for operation of said turbine engine.
9. A turbine engine in accordance with claim 8, wherein said flow
member comprises an exterior tube and an interior tube that is
integrally formed within said exterior tube.
10. A turbine engine in accordance with claim 9, wherein said
interior tube comprises an interior tube first end portion, an
interior tube second end portion, and a plurality of openings
extending from said interior tube first end portion to said
interior tube second end portion.
11. A turbine engine in accordance with claim 10, wherein said
interior tube comprises a channel defined therein and is configured
to channel fluid therethrough.
12. A turbine engine in accordance with claim 11, wherein said tube
comprises a channel defined therein, said interior tube channel is
concentrically aligned with said tube channel when said flow member
is coupled to said tube.
13. A turbine engine in accordance with claim 8, wherein said flow
member second end portion comprises a plurality of grooves.
14. A turbine engine in accordance with claim 13, wherein said tube
comprises a tube end portion that is configured to receive said
plurality of grooves therein.
15. A method of assembling a fuel nozzle assembly for use with a
turbine engine, said method comprising: providing a tube that is
configured to channel at least a first type of fuel through the
turbine engine; coupling a flow member to the tube to enable the
first type of fuel to be channeled through the turbine engine; and
removing the flow member from the tube to enable a plurality of
different types of fuel to be channeled through the turbine engine
for operation of the turbine engine.
16. A method in accordance with claim 15, wherein coupling a flow
member further comprises coupling a flow member that includes an
exterior tube and an interior tube integrally formed within the
exterior tube.
17. A method in accordance with claim 15, wherein coupling a flow
member further comprises coupling a flow member that includes an
exterior tube and an interior tube that includes an interior tube
first end portion, an interior tube second end portion, and a
plurality of openings extending from the interior tube first end
portion to the interior tube second end portion.
18. A method in accordance with claim 15, wherein coupling a flow
member further comprises coupling a flow member that includes an
exterior tube and an interior tube that includes a channel defined
therein and is configured to channel fluid therethrough.
19. A method in accordance with claim 15, wherein coupling a flow
member further comprises coupling a flow member that includes a
first end portion and a second end portion that includes a
plurality of grooves.
20. A method in accordance with claim 19, wherein coupling a flow
member further comprises coupling the flow member second end
portion to a tube end portion that is configured to receive the
plurality of grooves therein.
Description
BACKGROUND OF THE INVENTION
[0001] The field of the invention relates generally to turbine
engines and, more particularly, to a fuel nozzle assembly for use
with turbine engines.
[0002] At least some known turbine engines, such as gas turbine
engines, are used in cogeneration facilities and power plants to
generate power. At least some known gas turbine engines may have
high specific work and power per unit mass flow requirements. To
increase the operating efficiency, gas turbine engines may operate
with increased combustion temperatures. Moreover, in at least some
known gas turbine engines, engine efficiency increases as
combustion gas temperatures increase.
[0003] However, operating with higher temperatures may also
increase the generation of polluting emissions, such as oxides of
nitrogen (NO.sub.x). In an attempt to reduce the generation of such
emissions, at least some known gas turbine engines include improved
combustion system designs. For example, at least some known
combustion systems may include a plurality of fuel nozzles or fuel
nozzle assemblies, wherein at least one of the fuel nozzles is a
pre-mix nozzle. For example, known pre-mix nozzles enable
substances to be mixed, such as diluents, gases, and/or air, with
fuel to generate a fuel mixture for combustion. The mixed
substances are discharged from a tube of the pre-mix nozzle through
a flow member, such as a tertiary diffusion tip, that is integrally
formed with the tube. More specifically, known flow members include
a plurality of openings that enable the fuel to be discharged
therefrom.
[0004] Various types of fuels may be used during operation of the
gas turbine engine. However, each of the different types of fuel
may require a specific size (i.e., diameter) of flow member
openings. For example, while the size of the flow member openings
may be sufficient for the passage of one type of fuel, those same
openings may be too large or too small for a different type of
fuel. As such, the flow member may need to be changed based on the
type of fuel being used. However, in order to replace the flow
member, the attached flow member may need to be cut from the tube
prior to a new flow member being welded onto the tube. Such a
process may time-consuming and/or labor intensive or relatively
challenging.
BRIEF DESCRIPTION OF THE INVENTION
[0005] In one embodiment, a fuel nozzle assembly for use with a
turbine engine is provided. The fuel nozzle assembly includes a
tube that is configured to channel at least a first type of fuel
through the turbine engine. A flow member includes a first end
portion and a second end portion that is removably coupled to the
tube such that the flow member is severally removable from the tube
to enable a plurality of different types of fuel to be channeled
through the turbine engine for operation of the turbine engine.
[0006] In another embodiment, a turbine engine is provided. The
turbine engine includes a compressor. A combustion assembly is
coupled to the compressor and the combustion assembly includes at
least one combustor. At least one fuel nozzle assembly is coupled
within the combustor. The fuel nozzle assembly includes a tube that
is configured to channel at least a first type of fuel through the
turbine engine. A flow member includes a first end portion and a
second end portion that is removably coupled to the tube such that
the flow member is severally removable from the tube to enable a
plurality of different types of fuel to be channeled through the
turbine engine for operation of the turbine engine.
[0007] In yet another embodiment, a method of assembling a fuel
nozzle assembly for use with a turbine engine is provided. A tube
that is configured to channel at least a first type of fuel through
the turbine engine is provided. A flow member is coupled to the
tube to enable the first type of fuel to be channeled through the
turbine engine. The flow member is removed from the tube to enable
a plurality of different types of fuel to be channeled through the
turbine engine for operation of the turbine engine.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a schematic cross-sectional view of an exemplary
turbine engine;
[0009] FIG. 2 is a schematic cross-sectional view of a portion of
an exemplary fuel nozzle that may be used with the turbine engine
shown in FIG. 1 and taken from area 2;
[0010] FIG. 3 is an enlarged cross-sectional view of a portion of
an exemplary fuel nozzle assembly that may be used with the fuel
nozzle shown in FIG. 2 and taken from area 3;
[0011] FIG. 4 is a schematic cross-sectional view of a portion of
an exemplary flow member that may be used with the fuel nozzle
assembly shown in FIG. 3 and taken from area 4; and
[0012] FIG. 5 is a schematic cross-sectional view of a portion of
the flow member shown in FIG. 4 and taken from area 5.
DETAILED DESCRIPTION OF THE INVENTION
[0013] The exemplary systems and methods described herein overcome
at least some known disadvantages associated with at least some
known combustion systems of turbine engines. More specifically, the
embodiments described herein provide a fuel nozzle assembly that
includes components that may relatively easily and/or efficiently
removed and/or replaced for the various types of fuels being used
with the turbine engine. For example, in the exemplary embodiment,
the fuel nozzle assembly includes a flow member, such as a tertiary
diffusion tip, that is removably coupled to a tube of the fuel
nozzle assembly fuel to be channeled therethrough and to be easily
removed and replaced if a different type of fuel is to be used to
operate the turbine engine. Accordingly, in the exemplary
embodiment, in order to replace the flow member, it no longer needs
to be cut from the nozzle and welding is not required for attaching
the flow member.
[0014] FIG. 1 illustrates an exemplary turbine engine 100. More
specifically, turbine engine 100 is a gas turbine engine. While the
exemplary embodiment illustrates a gas turbine engine, the present
invention is not limited to any one particular engine, and one of
ordinary skill in the art will appreciate that the current
invention may be used in connection with other turbine engines.
[0015] Moreover, in the exemplary embodiment, turbine engine 100
includes an intake section 112, a compressor section 114 coupled
downstream from intake section 112, a combustor section 116 coupled
downstream from compressor section 114, a turbine section 118
coupled downstream from combustor section 116, and an exhaust
section 120. It should be noted that, as used herein, the term
"couple" is not limited to a direct mechanical, thermal,
communication, and/or an electrical connection between components,
but may also include an indirect mechanical, thermal, communication
and/or electrical connection between multiple components.
[0016] In the exemplary embodiment, turbine section 118 is coupled
to compressor section 114 via a rotor shaft 122. Combustor section
116 includes a plurality of combustors 124. Combustor section 116
is coupled to compressor section 114 such that each combustor 124
is positioned in flow communication with the compressor section
114. A plurality of fuel nozzles, such as fuel nozzles 126 and fuel
nozzle 127, are coupled within each combustor 124. In the exemplary
embodiment, fuel nozzles 126 are diffusion type nozzles and fuel
nozzle 127 is a pre-mix nozzle. Alternatively, fuels nozzles 126
and 127 may be any suitable fuel nozzle that enables turbine engine
100 to function as described herein. Moreover, fuel nozzles 126 and
127 may be aligned substantially within a cap member (not shown)
and/or fuel nozzles 126 and 127 may be integrally formed with the
cap member.
[0017] In the exemplary embodiment, fuel nozzles 126 are spaced
circumferentially about fuel nozzle 127 such that each fuel nozzle
127 is positioned within the center of the cap member.
Alternatively, fuel nozzles 126 and 127 may be oriented in any
orientation that enables turbine engine 100 to function as
described herein. Moreover, as described in more detail below, fuel
nozzle 127 includes a fuel nozzle assembly (not shown in FIG. 1)
that includes components (not shown in FIG. 1) that can be
relatively easily and efficiently removed and/or replaced from fuel
nozzle 127. In the exemplary embodiment, while only fuel nozzle 127
includes the fuel nozzle assembly, other nozzles 126 may also
include the fuel nozzle assembly.
[0018] Further, in the exemplary embodiment, turbine section 118 is
coupled to compressor section 114 and to a load 128 such as, but
not limited to, an electrical generator and/or a mechanical drive
application. In the exemplary embodiment, each compressor section
114 and turbine section 118 includes at least one rotor disk
assembly 130 that is coupled to a rotor shaft 122 to form a rotor
assembly 132.
[0019] During operation, intake section 112 channels air towards
compressor section 114 wherein the air is compressed to a higher
pressure and temperature prior to being discharged towards
combustor section 116. The compressed air is mixed with fuel and
other fluids that are ignited to generate combustion gases that are
channeled towards turbine section 118. More specifically, fuel,
such as natural gas and/or fuel oil, air, diluents, and/or Nitrogen
gas (N.sub.2) may be channeled into combustors 124, into the air
flow, and into at least fuel nozzle 127. The blended mixtures are
ignited to generate high temperature combustion gases that are
channeled towards turbine section 118. Turbine section 118 converts
the thermal energy from the gas stream to mechanical rotational
energy, as the combustion gases impart rotational energy to turbine
section 118 and to rotor assembly 132.
[0020] FIG. 2 is a schematic cross-sectional view of a portion of
fuel nozzle 127 taken from area 2 (shown in FIG. 1). In the
exemplary embodiment, fuel nozzle 127 includes a cylindrical tube
assembly 202 that includes an inner cylindrical tube 204 and an
outer cylindrical tube 206. More specifically, in the exemplary,
outer tube 206 includes a channel 207 defined therein, and inner
tube 204 is positioned within channel 207 such that outer tube 206
substantially circumscribes inner tube 204. Inner tube 204 also
includes a channel 210 defined therein that is sized and oriented
to channel fluids, such as various types of fuel, therethrough. In
the exemplary embodiment, outer tube 206 includes an exterior
portion 212, an interior portion 214, and a plurality of openings
216 that extend from exterior portion 212 to interior portion 214.
Moreover, at least a first channel 220 is defined within interior
portion 214 of outer tube 206 to channel fluids, such as various
types of fuel, therethrough. For example, channel 220 may extend
from at least one fuel source (not shown) to openings 216 such that
fuel may be channeled through channel 220 and through each opening
216. Moreover, in some embodiments, channel 220 may also extend
from opening 216 to an end portion 222 of fuel nozzle 127, wherein
channel 220 is independent from fuel nozzle end portion 222.
[0021] In the exemplary embodiment, outer tube 206 and inner tube
204 may be integrally formed together such that tube assembly 202
is a unitary component. Alternatively, outer tube 206 and inner
tube 204 may be separate structures that are coupled together.
Moreover, tube assembly 202 may be formed via a variety of
manufacturing processes known in the art, such as, but not limited
to, molding process, drawing process or a machining process. One or
more types of materials may be used to fabricate tube assembly 202
with the materials selected based on suitability for one or more
manufacturing techniques, dimensional stability, cost, moldability,
workability, rigidity, and/or other characteristic of the
material(s). For example, tube assembly 202 may be fabricated from
steel.
[0022] Moreover, in the exemplary embodiment, fuel nozzle 127
includes a plurality of pegs or fasteners 230 that are coupled to
tube assembly 202. More specifically, fasteners 230 may be coupled
to exterior portion 212 of outer tube 206. In the exemplary
embodiment, each fastener 230 is coupled to outer tube 206 such
that each fastener 230 extends radially outwardly from outer tube
206 and such that fasteners 230 are concentrically aligned with
openings 216. Moreover, in the exemplary embodiment, each fastener
230 is substantially cylindrical. Alternatively, each fastener 230
may have any suitable shape that enables fuel nozzle 127 and/or
turbine engine 100 to function as described herein.
[0023] In the exemplary embodiment, each fastener 230 includes an
exterior portion 232 and an interior portion 234 that has a channel
236 defined therein such that various types of fuels may be
channeled therethrough. Moreover, in the exemplary embodiment, each
fastener 230 includes a plurality of openings 240 that extend from
exterior portion 232 to interior portion 234. As such, fuel may be
channeled from channel 220 to channel 236, and through openings 240
for use within combustor 124 (shown in FIG. 1). In the exemplary
embodiment, openings 240 each have a predefined size (e.g.,
diameter) that is suitable to enable specific types of fuel to be
channeled therethrough. Fasteners 230 may be removably coupled to
tube assembly 202 or be integrally formed with tube assembly 202.
In the exemplary embodiment, fasteners 230 and/or tube assembly 202
may be fabricated from the same material that enables fuel nozzle
127 and/or turbine engine 100 to function as described herein.
Alternatively, fasteners 230 and/or tube assembly 202 may each be
fabricated from different materials that enable fuel nozzle 127
and/or turbine engine 100 to function as described herein.
[0024] In the exemplary embodiment, fuel nozzle 127 includes a fuel
nozzle assembly 250 at end portion 222 of fuel nozzle 127.
Moreover, a second channel 254 defined within interior portion 214
of outer tube 206 is configured to channel fluids, such as various
types of fuel, therethrough. For example, channel 254 may extend
from at least one fuel source (not shown) to fuel nozzle assembly
250. As described in more detail below, fuel may be channeled
through channel 254 and through fuel nozzle assembly 250.
[0025] FIG. 3 is an enlarged cross-sectional view of a portion of
fuel nozzle assembly 250 taken from area 3 (shown in FIG. 2). FIG.
4 is a schematic cross-sectional view of a portion of a flow member
314 that may be used with fuel nozzle assembly 250 taken from area
4 (shown in FIG. 3). FIG. 5 is a schematic cross-sectional view of
a portion of flow member 314 taken from area 5 (shown in FIG. 4).
In the exemplary embodiment, fuel nozzle assembly 250 includes
inner tube 204 that includes a first end portion 302, a second end
portion 304, and a middle portion 306 that extends between first
end portion 302 and second end portion 304. Tube 204 also includes
an outer portion 308 and an opposite inner portion 310. Channel 210
is defined within inner portion 310, and channel 210 extends from
first end portion 302 to second end portion 304.
[0026] A flow member 314 is removably coupled to tube 204. More
specifically, in the exemplary embodiment, flow member 314 includes
an exterior tube 320 having an outer portion 322 and an opposing
inner portion 324 that defines a channel 326 therein. Flow member
314 also includes an interior tube 328 that is positioned within
channel 326. Interior tube 328 includes an outer portion 330 that
is adjacent to inner portion 324 of exterior tube 320, and an inner
portion 332 that includes a channel 334 defined therein. Channel
334 is sized and shaped to channel various fluids, such as various
types of fuels, therethrough. In the exemplary embodiment, when
flow member 314 is coupled to tube 204, tube channel 210 is
substantially concentrically aligned within flow member channel
334.
[0027] In the exemplary embodiment, exterior tube 320 and interior
tube 328 of flow member 314 are integrally formed together such
that flow member 314 is a unitary component. Alternatively,
exterior tube 320 and interior tube 328 may be separate structures
that are coupled together. Moreover, flow member 314 may be formed
via a variety of manufacturing processes known in the art, such as,
but not limited to, molding process, drawing process or a machining
process. One or more types of materials may be used to fabricate
flow member 314 with the materials selected based on suitability
for one or more manufacturing techniques, dimensional stability,
cost, moldability, workability, rigidity, and/or other
characteristic of the material(s). For example, flow member 314 may
be fabricated from steel. Further, flow member 314 and tube 204 may
be fabricated from the same material(s) or each may be fabricated
from different material(s).
[0028] In the exemplary embodiment, flow member exterior tube 320
has a first end portion 340 and a second end portion 342 that is
coupled to second end portion 304 of tube 204. More specifically,
in the exemplary embodiment, second end portion 342 includes a
plurality of grooves 346 formed on outer portion 322 such that
second end portion 342 is threaded. Second end portion 304 of tube
204 receives grooves 346 therein. For example, second end portion
304 may be keyed to receive grooves. Accordingly, second end
portion 324 of exterior tube 320 of flow member 314 may be
threadably coupled to second portion 304 of tube 204.
Alternatively, second end portion 342 may not have grooves 346 and
may be coupled to second end portion 304 of tube 204 in any
suitable manner that enables fuel nozzle assembly 250 and/or
turbine engine 100 to function as described herein.
[0029] Similar to exterior tube 320, interior tube 328 also
includes a first end portion 350 and a second end portion 352.
Moreover, in the exemplary embodiment, interior tube 328 includes a
plurality of openings 360 that are defined between outer portion
330 and inner portion 332 of tube 328. Openings 360 also extend
from first end portion 350 to second end portion 352 such that
fluids, such as various types of fuels may be channeled
therethrough.
[0030] Prior to operation of turbine engine 100, flow member 314
may be coupled to tube 204. More specifically, in the exemplary
embodiment, second end portion 342 of exterior tube 320 may be
threadably coupled to second end portion 304 of tube 204. When flow
member 314 is securely coupled to tube 204, fuel, such as natural
gas and/or fuel oil, air, diluents, and/or Nitrogen gas (N.sub.2)
is channeled into fuel nozzle 127 (shown in FIG. 1). For example,
in the exemplary embodiment, fuel may be channeled through channel
254 (shown in FIG. 2) of outer tube 206 (shown in FIG. 2) and fuel
may be channeled through channel 210 (shown in FIG. 2). At the same
time, fuel, such as gas fuel, may be channeled from channel 220
(shown in FIG. 2) to channel 236 (shown in FIG. 2) of each fastener
230 (shown in FIG. 2) and through fastener openings 240 (shown in
FIG. 2).
[0031] Fuels from channels 254, 210, and 220 may then be channeled
to end portion 222 (shown in FIG. 2) of fuel nozzle 127 and towards
fuel nozzle assembly 250. More specifically, the fuel is channeled
through channel 210 and through channel 334. Fuel is also channeled
through openings 360 that are defined between outer portion 330 and
inner portion 332 of tube 328 such that the fuel may be ignited to
generate high temperature combustion gases that are channeled
towards turbine section 118 (shown in FIG. 1).
[0032] A user of turbine engine 100 may change the type of fuels
being used with turbine engine 100. However, the new type of fuel
may not fit through fastener openings 360. As such, the user may
remove flow member 314 from tube 204. More specifically, second end
portion 342 of exterior tube 320 of flow member 314 may be removed
from second end portion 304 of tube 204 and be replaced with a
different flow member (not shown) having openings (not shown) that
are suitable for the new type of fuel being used.
[0033] As compared to known turbine engines, the embodiments
described herein provide a fuel nozzle assembly that enables the
use of different types of fuels by providing a relatively easy and
efficient solution to removing and replacing components of the fuel
nozzle assembly. More specifically, the fuel nozzle assembly
described herein includes a cylindrical tube that is configured to
channel at least a first type of fuel through the turbine engine. A
flow member includes a first end portion and a second end portion
that is removably coupled to the cylindrical tube such that the
flow member is severally removable from the tube to enable a
plurality of different types of fuel to be channeled through the
turbine engine for operation of the turbine engine. Accordingly, in
the exemplary embodiment, in order to replace the flow member, it
no longer needs to be cut from the nozzle and welding is not
required for attaching the flow member.
[0034] Exemplary embodiments of the apparatus, systems, and methods
are described above in detail. The apparatus, systems, and methods
are not limited to the specific embodiments described herein, but
rather, components of the apparatus, systems, and/or steps of the
methods may be utilized independently and separately from other
components and/or steps described herein. For example, the systems
may also be used in combination with other systems and methods, and
is not limited to practice with only the systems as described
herein. Rather, the exemplary embodiment can be implemented and
utilized in connection with many other applications.
[0035] Although specific features of various embodiments of the
invention may be shown in some drawings and not in others, this is
for convenience only. In accordance with the principles of the
invention, any feature of a drawing may be referenced and/or
claimed in combination with any feature of any other drawing.
[0036] 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 language of the claims.
* * * * *