U.S. patent application number 15/793838 was filed with the patent office on 2019-04-25 for segmented structural links for coupled disk frequency tuning.
This patent application is currently assigned to United Technologies Corporation. The applicant listed for this patent is United Technologies Corporation. Invention is credited to James H. Moffitt, Peter V. Tomeo.
Application Number | 20190120255 15/793838 |
Document ID | / |
Family ID | 63965259 |
Filed Date | 2019-04-25 |
![](/patent/app/20190120255/US20190120255A1-20190425-D00000.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00001.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00002.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00003.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00004.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00005.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00006.png)
![](/patent/app/20190120255/US20190120255A1-20190425-D00007.png)
United States Patent
Application |
20190120255 |
Kind Code |
A1 |
Tomeo; Peter V. ; et
al. |
April 25, 2019 |
SEGMENTED STRUCTURAL LINKS FOR COUPLED DISK FREQUENCY TUNING
Abstract
A segmented structural link may comprise a base portion having a
first face, a tail portion, and a distal end having a second face.
The tail portion may extend at an angle relative to the first face.
The tail portion may comprise a first bend and may further comprise
a second bend. The base portion may comprise at least one of a
captured nut, a nut plate, or a self-clinching nut.
Inventors: |
Tomeo; Peter V.;
(Middletown, CT) ; Moffitt; James H.; (Manchester,
CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Assignee: |
United Technologies
Corporation
Farmington
CT
|
Family ID: |
63965259 |
Appl. No.: |
15/793838 |
Filed: |
October 25, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F01D 5/10 20130101; F01D
5/3007 20130101; F04D 29/321 20130101; F05D 2260/941 20130101; F05D
2260/96 20130101; F05D 2220/36 20130101; F04D 29/388 20130101; F04D
29/324 20130101; F04D 29/668 20130101 |
International
Class: |
F04D 29/66 20060101
F04D029/66; F04D 29/38 20060101 F04D029/38; F04D 29/32 20060101
F04D029/32 |
Claims
1. A segmented structural link, comprising: a hub; a base portion
having a first face; a tail portion; and a distal end having a
second face.
2. The segmented structural link of claim 1, wherein the tail
portion extends at an angle relative to the first face.
3. The segmented structural link of claim 2, wherein the tail
portion comprises a first bend.
4. The segmented structural link of claim 3, wherein the tail
portion further comprises a second bend.
5. The segmented structural link of claim 2, wherein the base
portion further comprises at least one of a captured nut, a nut
plate, or a self-clinching nut.
6. The segmented structural link of claim 2, wherein the base
portion is coupled at the first face to a first flange.
7. The segmented structural link of claim 6, wherein the distal end
is coupled at the second face to a second flange.
8. The segmented structural link of claim 7, wherein the first
flange is one of a J-flange or a scalloped flange.
9. The segmented structural link of claim 8, wherein the second
flange is a forward flange of the hub, wherein the hub further
comprises a cone arm coupled to a blade ring at a web.
10. The segmented structural link of claim 9, wherein the blade
ring pivots over the cone arm about the web in response to a
rotation of the hub.
11. The segmented structural link of claim 10, wherein the first
flange is coupled to the blade ring and, in response to the blade
ring pivoting over the cone arm about the web, is driven toward the
second flange.
12. The segmented structural link of claim 11, wherein the
segmented structural link is compressed in response to the first
flange being driven toward the second flange.
13. A gas turbine engine comprising: a fan section having a fan
disk comprising a hub comprising a cone arm, a web, and a blade
ring; a compressor section configured to compress a gas; a
combustor section aft of the compressor section and configured to
combust the gas; a turbine section aft of the combustor section
configured to extract energy from the gas; and a segmented
structural link wherein the segmented structural link comprises: a
base portion having a first face; a tail portion; and a distal end
having a second face.
14. The gas turbine engine of claim 13, wherein the tail portion
extends at an angle relative to the first face.
15. The gas turbine engine of claim 14, wherein the tail portion
comprises a first bend.
16. The gas turbine engine of claim 15, wherein the base portion is
coupled at the first face to a first flange and the distal end is
coupled at the second face to a second flange.
17. The gas turbine engine of claim 16, wherein a plurality of
segmented structural links are distributed symmetrically about a
circumference of the fan disk.
18. The gas turbine engine of claim 16, wherein the segmented
structural link extends around a portion of a circumference of the
fan disk between a J-flange and a scalloped flange.
19. The gas turbine engine of claim 16, wherein the segmented
structural link is compressed in response to the first flange being
driven toward the second flange.
20. A method of tuning a vibrational response of a fan disk, the
method comprising: calculating a vibrational mode shape of the fan
disk; determining a point of maximum relative downward deflection
of a blade ring of the fan disk; and coupling a segmented
structural link to the fan disk at the point of maximum relative
downward deflection between a first flange and a second flange.
Description
FIELD
[0001] The disclosure relates generally to fans and fan hubs of gas
turbine engines.
BACKGROUND
[0002] Gas turbine engines typically include a fan section to drive
inflowing air, a compressor section to pressurize inflowing air, a
combustor section to burn a fuel in the presence of the pressurized
air, and a turbine section to extract energy from the resulting
combustion gases. The fan section may include a plurality of fan
blades coupled to a fan hub. The fan hub may experience vibrational
modes in operation.
SUMMARY
[0003] In various embodiments the present disclosure provides a
segmented structural link comprising a base portion having a first
face, a tail portion, and a distal end having a second face. In
various embodiments, the tail portion extends at an angle relative
to the first face. In various embodiments, the tail portion
comprises a first bend. In various embodiments, the tail portion
further comprises a second bend. In various embodiments, the base
portion further comprises at least one of a captured nut, a nut
plate, or a self-clinching nut.
[0004] In various embodiments, the base portion is coupled at the
first face to a first flange. In various embodiments, the distal
end is coupled at the second face to a second flange. In various
embodiments, the first flange is one of a J-flange or a scalloped
flange. In various embodiments, the second flange is a forward
flange of a hub comprising a cone arm coupled to a blade ring at a
web. In various embodiments, the blade ring pivots over the cone
arm about the web in response to a rotation of the hub. In various
embodiments, the first flange is coupled to the blade ring and, in
response to the blade ring pivoting over the cone arm about the
web, is driven toward the second flange. In various embodiments,
the segmented structural link is compressed in response to the
first flange being driven toward the second flange.
[0005] In various embodiments the present disclosure provides a gas
turbine engine comprising a fan section having a fan disk
comprising a hub comprising a cone arm, a web, and a blade ring, a
compressor section configured to compress a gas, a combustor
section aft of the compressor section and configured to combust the
gas, a turbine section aft of the combustor section configured to
extract energy from the gas, and a segmented structural link
wherein the segmented structural link comprises a base portion
having a first face, a tail portion, and a distal end having a
second face.
[0006] In various embodiments, the tail portion extends at an angle
relative to the first face. In various embodiments, the tail
portion comprises a first bend. In various embodiments, the base
portion is coupled at the first face to a first flange and the
distal end is coupled at the second face to a second flange. In
various embodiments, a plurality of segmented structural links are
distributed symmetrically about a circumference of the fan disk. In
various embodiments, the segmented structural link extends around a
portion of a circumference of the fan disk between a J-flange and a
scalloped flange. In various embodiments, the segmented structural
link is compressed in response to the first flange being driven
toward the second flange.
[0007] In various embodiments, the present disclosure provides a
method of tuning a vibrational response of a fan disk comprising
calculating a vibrational mode shape of the fan disk, determining a
point of maximum relative downward deflection of a blade ring of
the fan disk, and coupling a segmented structural link to the fan
disk at the point of maximum relative downward deflection between a
first flange and a second flange.
[0008] The forgoing features and elements may be combined in
various combinations without exclusivity, unless expressly
indicated herein otherwise. These features and elements as well as
the operation of the disclosed embodiments will become more
apparent in light of the following description and accompanying
drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] The subject matter of the present disclosure is particularly
pointed out and distinctly claimed in the concluding portion of the
specification. A more complete understanding of the present
disclosures, however, may best be obtained by referring to the
detailed description and claims when considered in connection with
the drawing figures, wherein like numerals denote like
elements.
[0010] FIG. 1 illustrates an exemplary gas turbine engine, in
accordance with various embodiments;
[0011] FIG. 2 illustrates a fan section having a segmented
structural link, in accordance with various embodiments;
[0012] FIG. 3A illustrates a segmented structural link, in
accordance with various embodiments;
[0013] FIG. 3B illustrates a segmented structural link, in
accordance with various embodiments;
[0014] FIG. 4A illustrates a segmented structural link, in
accordance with various embodiments;
[0015] FIG. 4B illustrates a segmented structural link, in
accordance with various embodiments; and
[0016] FIG. 5 illustrates a method of tuning the vibrational
response of a fan disk, in accordance with various embodiments.
DETAILED DESCRIPTION
[0017] The detailed description of exemplary embodiments herein
makes reference to the accompanying drawings, which show exemplary
embodiments by way of illustration and their best mode. While these
exemplary embodiments are described in sufficient detail to enable
those skilled in the art to practice the disclosures, it should be
understood that other embodiments may be realized and that logical,
chemical, and mechanical changes may be made without departing from
the spirit and scope of the disclosures. Thus, the detailed
description herein is presented for purposes of illustration only
and not of limitation. For example, the steps recited in any of the
method or process descriptions may be executed in any order and are
not necessarily limited to the order presented. Furthermore, any
reference to singular includes plural embodiments, and any
reference to more than one component or step may include a singular
embodiment or step. Also, any reference to attached, fixed,
connected or the like may include permanent, removable, temporary,
partial, full and/or any other possible attachment option.
Additionally, any reference to without contact (or similar phrases)
may also include reduced contact or minimal contact.
[0018] In various embodiments and with reference to FIG. 1, a gas
turbine engine 20 is provided. Gas turbine engine 20 may be a
two-spool turbofan that generally incorporates a fan section 22, a
compressor section 24, a combustor section 26 and a turbine section
28. Alternative engines may include, for example, an augmenter
section among other systems or features. In operation, fan section
22 can drive air along a bypass flow-path B while compressor
section 24 can drive air for compression and communication into
combustor section 26 then expansion through turbine section 28.
Although depicted as a turbofan gas turbine engine 20 herein, it
should be understood that the concepts described herein are not
limited to use with turbofans as the teachings may be applied to
other types of turbine engines including three-spool
architectures.
[0019] Gas turbine engine 20 may generally comprise a low speed
spool 30 and a high speed spool 32 mounted for rotation about an
engine central longitudinal axis A-A' relative to an engine static
structure 36 via one or more bearing systems 38 (shown as bearing
system 38-1 and bearing system 38-2). It should be understood that
various bearing systems 38 at various locations may alternatively
or additionally be provided, including for example, bearing system
38, bearing system 38-1, and bearing system 38-2.
[0020] Low speed spool 30 may generally comprise an inner shaft 40
that interconnects a fan 42, a low pressure (or first) compressor
section 44 (also referred to a low pressure compressor) and a low
pressure (or first) turbine section 46. Inner shaft 40 may be
connected to fan 42 through a geared architecture 48 that can drive
fan 42 at a lower speed than low speed spool 30. Geared
architecture 48 may comprise a gear assembly 60 enclosed within a
gear housing 62. Gear assembly 60 couples inner shaft 40 to a
rotating fan structure. High speed spool 32 may comprise an outer
shaft 50 that interconnects a high pressure compressor ("HPC") 52
(e.g., a second compressor section) and high pressure (or second)
turbine section 54. A combustor 56 may be located between HPC 52
and high pressure turbine 54. A mid-turbine frame 57 of engine
static structure 36 may be located generally between high pressure
turbine 54 and low pressure turbine 46. Mid-turbine frame 57 may
support one or more bearing systems 38 in turbine section 28. Inner
shaft 40 and outer shaft 50 may be concentric and rotate via
bearing systems 38 about the engine central longitudinal axis A-A',
which is collinear with their longitudinal axes. As used herein, a
"high pressure" compressor or turbine experiences a higher pressure
than a corresponding "low pressure" compressor or turbine.
[0021] The core airflow C may be compressed by low pressure
compressor 44 then HPC 52, mixed and burned with fuel in combustor
56, then expanded over high pressure turbine 54 and low pressure
turbine 46. Mid-turbine frame 57 includes airfoils 59 which are in
the core airflow path. Low pressure turbine 46, and high pressure
turbine 54 rotationally drive the respective low speed spool 30 and
high speed spool 32 in response to the expansion.
[0022] Gas turbine engine 20 may be, for example, a high-bypass
geared aircraft engine. In various embodiments, the bypass ratio of
gas turbine engine 20 may be greater than about six (6). In various
embodiments, the bypass ratio of gas turbine engine 20 may be
greater than ten (10). In various embodiments, geared architecture
48 may be an epicyclic gear train, such as a star gear system (sun
gear in meshing engagement with a plurality of star gears supported
by a carrier and in meshing engagement with a ring gear) or other
gear system. Geared architecture 48 may have a gear reduction ratio
of greater than about 2.3 and low pressure turbine 46 may have a
pressure ratio that is greater than about 5. In various
embodiments, the bypass ratio of gas turbine engine 20 is greater
than about ten (10:1). In various embodiments, the diameter of fan
42 may be significantly larger than that of the low pressure
compressor 44, and the low pressure turbine 46 may have a pressure
ratio that is greater than about (5:1). Low pressure turbine 46
pressure ratio may be measured prior to inlet of low pressure
turbine 46 as related to the pressure at the outlet of low pressure
turbine 46 prior to an exhaust nozzle. It should be understood,
however, that the above parameters are exemplary of various
embodiments of a suitable geared architecture engine and that the
present disclosure contemplates other gas turbine engines including
direct drive turbofans.
[0023] In various embodiments, the next generation of turbofan
engines may be designed for higher efficiency which is associated
with higher pressure ratios and higher temperatures in the HPC 52.
These higher operating temperatures and pressure ratios may create
operating environments that may cause thermal loads that are higher
than the thermal loads encountered in conventional turbofan
engines, which may shorten the operational life of current
components.
[0024] In various embodiments, HPC 52 may comprise alternating rows
of rotating rotors and stationary stators. Stators may have a
cantilevered configuration or a shrouded configuration. More
specifically, a stator may comprise a stator vane, a casing support
and a hub support. In this regard, a stator vane may be supported
along an outer diameter by a casing support and along an inner
diameter by a hub support. In contrast, a cantilevered stator may
comprise a stator vane that is only retained and/or supported at
the casing (e.g., along an outer diameter).
[0025] In various embodiments, rotors may be configured to compress
and spin a fluid flow. Stators may be configured to receive and
straighten the fluid flow. In operation, the fluid flow discharged
from the trailing edge of stators may be straightened (e.g., the
flow may be directed in a substantially parallel path to the
centerline of the engine and/or HPC) to increase and/or improve the
efficiency of the engine and, more specifically, to achieve
enhanced compression and efficiency when the straightened air is
compressed and spun by rotor 64.
[0026] According to various embodiments and with reference to FIGS.
1 and 2, a fan section 200 having a segmented structural link, is
provided. Fan 202 comprises blade 206 coupled at blade root 207 to
a fan disk 208 and compressor inlet cone 204. Fan 202 may be
coupled to a shaft, such as inner shaft 40, where inner shaft 40
may be in mechanical communication with geared architecture 48. Tip
205 of blade 206 lies proximate rub strip 214 which forms a part of
the inner aerodynamic surface 216 of fan case 210. A segmented
structural link 302 lies radially inward of blade 206 aft of
compressor inlet cone 204 at the forward face of fan disk 208. In
various embodiments, a plurality of segmented structural links may
be coupled circumferentially about the forward face of the disk. In
various embodiments, segmented structural link 302 may be coupled
proximate and radially outward of a shaft, such as inner shaft 40.
Fan case 210 may be coupled at an aft end to pylon 218 which may be
coupled to compressor case 220. As fan 202 rotates about the shaft
it tends to draw in gas 222, such as, for example air, at the fore
end of fan case 210. Rotating fan 202 tends to conduct gas 222
along inner aerodynamic surface 215 toward pylon 218 passing
between inner aerodynamic surface 215 and compressor case 220 as
fan exhaust 224.
[0027] In various embodiments and with reference to FIGS. 3A and
3B, a segmented structural link 302 is shown coupled to a fan disk
300. FIG. 3A illustrates fan disk 300 in a section through the x-y
plane and FIG. 3B illustrates a perspective view of the fan disk
300 from the forward face looking aft. Segmented structural link
302 comprises a base portion 304 and a tail 306 extending at an
angle .theta. relative to the plane of the forward face 305 of base
portion 304. Tail 306 extends radially inward (along the x and
y-axis) from the base portion toward a distal end 308 and may
comprise one or more bends. In various embodiments, tail 306 may
have a distal taper (along the y-axis) from base portion 304 toward
distal end 308. Segmented structural link 302 is coupled at the
base portion 304 to J-flange 312, with forward face 305 in contact
with an aft face of J-flange 312. In various embodiments, base
portion 304 further comprises a captured nut 321 and segmented
structural link 302 that may be coupled at the base portion 304 via
first fastener 310 extending through J-flange 312 and base portion
304 to engage captured nut 321. Distal end 308 is coupled at aft
face 309 to forward flange 316 of hub 322.
[0028] In various embodiments, hub 322 engages a shaft, such as
inner shaft 40, at splines 324 and in response to rotation of the
shaft transmits torque from the shaft via cone arm 326 and web 328
to blade ring 330 causing blade ring 330 to rotate about the axis
of the shaft. Blade ring 330 comprises channels 334 configured to
receive a blade at a blade root, such as, for example, receiving
blade 206 at blade root 207, and in this regard a fan, such as fan
202, may be caused to rotate about the shaft. In response to the
rotation of the fan about the shaft, vibrations may be induced in
the structure of the fan manifesting as a vibrational bending mode
such as, for example, a first bending mode, a second bending mode,
or a third bending mode. Blade ring 330 is coupled to J-flange 312
and, in response to a bending mode, tends to pivot over cone arm
326 about web 328 tending to induce a torque 332 which tends to
cause a downward (relative to the y-axis) deflection of J-flange
312 which is in turn transmitted as a downward (relative to the
y-axis) load "F" at J-flange 312. Stated another way, J-flange 312
is driven relatively towards forward flange 316 by downward load
"F". Downward load "F" is transmitted through segmented structural
link 302 into forward flange 316 and is resisted by upward
(relative to the y-axis) load "C" at forward flange 316 tending
thereby to place segmented structural link 302 in compression. In
this regard, segmented structural link 302 may be said to increase
the stiffness of a fan disk, such as fan disk 208, by resisting
vibrationally induced bending loads.
[0029] In various embodiments and with reference to FIGS. 4A and
4B, a segmented structural link 402 is shown coupled to a fan disk
400, which may comprise features, geometries, construction,
manufacturing techniques, and/or internal components similar to fan
disk 300 of FIGS. 3A and 3B. FIG. 4A illustrates fan disk 400 in a
section through the x-y plane and FIG. 4B illustrates a perspective
view of the fan disk 400 from the forward face looking aft.
Segmented structural link 402 comprises a base portion 404 and tail
portion 408 having a first bend 406 proximate base portion 404, a
second bend 410 proximate a distal end 412, and extending at an
angle .theta. relative to the plane of the aft face 434 of the base
portion 404. Segmented structural link 402 extends in a continuous
arc segment over a portion of the circumference of fan disk 400 and
base portion 404 is coupled to J-flange 418 with aft face 434 of
base portion 404 in contact with a forward face of J-flange 418 and
coupled to scalloped flange 419 with aft face 434 of base portion
404 in contact with a forward face of scalloped flange 419. Distal
end 412 is coupled at aft face 413 to forward flange 416 of hub
422. In response to a bending mode, blade ring 430 tends to pivot
over cone arm 426 about web 428 tending to induce a torque 432
which tends to cause a downward (relative to the y-axis) deflection
of J-flange 418 and scalloped flange 419 which is in turn
transmitted as a downward (relative to the y-axis) load "F" at
J-flange 312 and scalloped flange 419. Downward load "F" is
transmitted through segmented structural link 402 into forward
flange 416 and is resisted by upward (relative to the y-axis) load
"C" at forward flange 416 tending thereby to place segmented
structural link 402 in compression. In this regard, segmented
structural link 402 may be said to increase the stiffness of a fan
disk, such as fan disk 208, by resisting vibrationally induced
bending loads.
[0030] In various embodiments, a blade ring, such as, for example,
blade ring 330, may comprise one or more flanges or J-flanges, such
as J-flange 312 or scalloped flange 313. In various embodiments,
one or more segmented structural links such as, for example,
segmented structural link 302 or segmented structural link 402, may
be located circumferentially around the forward end of a fan disk,
such as fan disk 300, and coupled between one or more flanges or
J-flanges, such as J-flange 312 or scalloped flange 313, and a
forward flange such as, for example forward flange 316 of a hub,
such as hub 322, to resist vibrationally induced bending loads. In
various embodiments, between one (1) and thirty-five (35) segmented
structural links, or between five (5) and thirty (30) segmented
structural links, or between ten (10) and twenty-five (25)
segmented structural links may be distributed symmetrically about
the circumference of a fan disk. In various embodiments, a
segmented structural link, such as, for example segmented
structural link 402, extends around a portion of the circumference
of a fan disk, such as, for example, fan disk 400 between a
J-flange and a scalloped flange or may extend around the entire
circumference of a fan disk. In various embodiments, a fastener,
such as fastener 314 or fastener 421, may comprise a threaded stud
coupled to a forward flange, such as forward flange 316. In various
embodiments, a captured nut, such as captured nut 321 or captured
nut 420, may comprise a self-clinching nut, a nut plate, or any
other captured fastener know to those skilled in the art. In
various embodiments, a segmented structural link is one of a metal,
an alloy, a steel, a titanium, a titanium alloy, a nickel, or a
nickel alloy. In various embodiments angle .theta. is between zero
degrees (0.degree.) and sixty degrees (60.degree.), or between ten
degrees (10.degree.) and fifty degrees (50.degree.), or between
twenty-five degrees (25.degree.) and forty-five degrees
(45.degree.).
[0031] In various embodiments and with reference now to FIG. 5, a
method 500 of tuning the vibrational response of a fan disk
comprises calculating the vibrational mode shapes of a fan disk
(502); determining a point of maximum relative downward deflection
of a blade ring (504) of the fan disk; coupling a segmented
structural link to the fan disk (506) at the point of maximum
relative downward deflection between a first flange, such as, for
example J-flange 312 of FIG. 3A, and a second flange, such as, for
example, forward flange 316 of FIG. 3A.
[0032] Benefits, other advantages, and solutions to problems have
been described herein with regard to specific embodiments.
Furthermore, the connecting lines shown in the various figures
contained herein are intended to represent exemplary functional
relationships and/or physical couplings between the various
elements. It should be noted that many alternative or additional
functional relationships or physical connections may be present in
a practical system. However, the benefits, advantages, solutions to
problems, and any elements that may cause any benefit, advantage,
or solution to occur or become more pronounced are not to be
construed as critical, required, or essential features or elements
of the disclosures.
[0033] The scope of the disclosures is accordingly to be limited by
nothing other than the appended claims, in which reference to an
element in the singular is not intended to mean "one and only one"
unless explicitly so stated, but rather "one or more." Moreover,
where a phrase similar to "at least one of A, B, or C" is used in
the claims, it is intended that the phrase be interpreted to mean
that A alone may be present in an embodiment, B alone may be
present in an embodiment, C alone may be present in an embodiment,
or that any combination of the elements A, B and C may be present
in a single embodiment; for example, A and B, A and C, B and C, or
A and B and C. Different cross-hatching is used throughout the
figures to denote different parts but not necessarily to denote the
same or different materials.
[0034] Systems, methods and apparatus are provided herein. In the
detailed description herein, references to "one embodiment", "an
embodiment", "an example embodiment", etc., indicate that the
embodiment described may include a particular feature, structure,
or characteristic, but every embodiment may not necessarily include
the particular feature, structure, or characteristic. Moreover,
such phrases are not necessarily referring to the same embodiment.
Further, when a particular feature, structure, or characteristic is
described in connection with an embodiment, it is submitted that it
is within the knowledge of one skilled in the art to affect such
feature, structure, or characteristic in connection with other
embodiments whether or not explicitly described. After reading the
description, it will be apparent to one skilled in the relevant
art(s) how to implement the disclosure in alternative
embodiment
[0035] Furthermore, no element, component, or method step in the
present disclosure is intended to be dedicated to the public
regardless of whether the element, component, or method step is
explicitly recited in the claims. No claim element is intended to
invoke 35 U.S.C. 112(f) unless the element is expressly recited
using the phrase "means for." As used herein, the terms
"comprises", "comprising", or any other variation thereof, are
intended to cover a non-exclusive inclusion, such that a process,
method, article, or apparatus that comprises a list of elements
does not include only those elements but may include other elements
not expressly listed or inherent to such process, method, article,
or apparatus.
* * * * *