U.S. patent application number 15/596770 was filed with the patent office on 2018-11-22 for rapid ceramic matrix composite fabrication of aircraft brakes via field assisted sintering.
This patent application is currently assigned to GOODRICH CORPORATION. The applicant listed for this patent is GOODRICH CORPORATION. Invention is credited to Robert Bianco, Sergey Mironets, Gavin Charles Richards.
Application Number | 20180335099 15/596770 |
Document ID | / |
Family ID | 62245153 |
Filed Date | 2018-11-22 |
United States Patent
Application |
20180335099 |
Kind Code |
A1 |
Bianco; Robert ; et
al. |
November 22, 2018 |
RAPID CERAMIC MATRIX COMPOSITE FABRICATION OF AIRCRAFT BRAKES VIA
FIELD ASSISTED SINTERING
Abstract
A method of making a ceramic matrix composite (CMC) brake
component may include the steps of applying a pressure to a mixture
comprising ceramic powder and chopped fibers, pulsing an electrical
discharge across the mixture to generate a pulsed plasma between
particles of the ceramic powder, increasing a temperature applied
to the mixture using direct heating to generate the CMC brake
component, and reducing the temperature and the pressure applied to
the CMC brake component. The ceramic powder may have a micrometer
powder size or a nanometer powder size, and the chopped fibers may
have an interphase coating.
Inventors: |
Bianco; Robert; (Bloomfield,
CT) ; Mironets; Sergey; (Charlotte, NC) ;
Richards; Gavin Charles; (Windsor, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
GOODRICH CORPORATION |
Charlotte |
NC |
US |
|
|
Assignee: |
GOODRICH CORPORATION
Charlotte
NC
|
Family ID: |
62245153 |
Appl. No.: |
15/596770 |
Filed: |
May 16, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
C04B 35/62868 20130101;
F16D 69/02 20130101; F16D 65/126 20130101; F16D 2065/1364 20130101;
C04B 35/575 20130101; C04B 35/645 20130101; F16D 2200/0086
20130101; C04B 35/62873 20130101; C04B 35/806 20130101; C04B
35/62884 20130101; C04B 2235/5244 20130101; C04B 35/593 20130101;
C04B 2235/3821 20130101; F16D 2250/0023 20130101; F16D 65/00
20130101; C04B 2235/5248 20130101; C04B 2235/3826 20130101; C04B
2235/5454 20130101; F16D 2200/006 20130101; C04B 2235/3873
20130101; C04B 35/563 20130101; F16D 2200/0047 20130101; F16D
2200/0069 20130101; C04B 35/6286 20130101; C04B 2235/666 20130101;
F16D 2200/0052 20130101; F16D 2200/0043 20130101; C04B 2235/5436
20130101; F16D 69/028 20130101 |
International
Class: |
F16D 65/12 20060101
F16D065/12; C04B 35/80 20060101 C04B035/80; C04B 35/645 20060101
C04B035/645; C04B 35/628 20060101 C04B035/628 |
Claims
1. A method of making a ceramic matrix composite (CMC) brake
component, the method comprising: increasing a pressure from a
first pressure to a second pressure in a mold containing a mixture
comprising a ceramic powder and fibers; pulsing an electrical
discharge across the mixture to generate a pulsed plasma between
particles of the ceramic powder; generating the CMC brake component
in response to increasing a temperature from a first temperature to
a second temperature in the mold using direct heating; and reduce
the temperature and the pressure applied to the CMC brake
component.
2. The method of claim 1, wherein the ceramic powder comprises an
average particle size ranging from micrometers to nanometers.
3. The method of claim 1, wherein the ceramic powder comprises at
least one of SiC, B.sub.4C, or Si.sub.3N.sub.4.
4. The method of claim 1, wherein the fibers comprises at least one
of chopped carbon fibers or chopped SiC fibers.
5. The method of claim 1, wherein the mold comprises at least one
of graphite, a refractory metal, or a ceramic.
6. The method of claim 1, further comprising machining the CMC
brake component.
7. The method of claim 1, wherein the direct heating comprises
resistance heating.
8. The method of claim 1, wherein the direct heating comprises
inductive heating.
9. The method of claim 1, wherein the CMC brake component comprises
a CMC brake disc.
10. The method of claim 1, wherein the temperature is increased to
a maximum temperature of substantially 2400.degree. C.
11. The method of claim 1, wherein the pressure is increased by
actuating a punch to press against the mixture.
12. The method of claim 11, wherein the electrical discharge is
pulsed across the mixture through a graphite electrode coupled to
the punch, a brass electrode coupled to the graphite electrode, and
a copper plate coupled to the brass electrode.
13. The method of claim 1, wherein the electrical discharge is
pulsed at a cycle time of substantially 10 minutes.
14. The method of claim 1, wherein the fibers are coated with an
interphase layer.
15. The method of claim 14, wherein the interphase layer comprises
at least one of pyrolytic carbon or boron nitride.
16. A method of making a ceramic matrix composite (CMC) brake
component, the method comprising: applying a pressure to a mixture
comprising ceramic powder and chopped fibers, wherein the ceramic
powder comprises an average particle size ranging from micrometers
to nanometers, wherein the chopped fibers are coated with an
interphase layer; pulsing an electrical discharge across the
mixture to generate a pulsed plasma between particles of the
ceramic powder; generating the CMC brake component in response to
increasing a temperature applied to the mixture from a first
temperature to a second temperature using direct heating; and
reducing the temperature and the pressure applied to the CMC brake
component.
17. The method of claim 16, wherein the ceramic powder comprises at
least one of SiC, B.sub.4C, or Si.sub.3N.sub.4.
18. The method of claim 16, wherein the chopped fibers comprise at
least one of chopped carbon fiber or chopped SiC fiber.
19. The method of claim 16, wherein the interphase layer comprises
at least one of pyrolytic carbon or boron nitride.
20. A ceramic matrix composite (CMC) brake component for an
aircraft, comprising: an annular disc comprising: a ceramic
material having a monolithic grain structure, wherein the ceramic
material comprises at least one of SiC, B.sub.4C, or
Si.sub.3N.sub.4; and chopped fibers disposed within the ceramic
material, wherein the chopped fibers are coated with an interphase
layer, wherein the chopped fibers comprise at least one of carbon
fibers or SiC fibers.
Description
FIELD
[0001] The disclosure relates generally to making aircraft brake
components using field assisted sintering technique (FAST).
BACKGROUND
[0002] Carbon/carbon (C/C) composites are used in the aerospace
industry for aircraft brake heat sink materials. Silicon carbide
(SiC) based ceramic matrix composites (CMCs) have found use as
brake materials in automotive and locomotive applications. These
composites are typically produced using one or more of these three
main methods: chemical vapor infiltration (CVI), melt infiltration
(MI), and polymer impregnation and pyrolysis (PIP). However, each
of these CMC fabrication methods has limitations. The processing
time for both CVI and PIP, for example, can extend well over 100
hours. MI generated CMCs tend to contain residual silicon, which
limits upper use temperature. Thus, existing processes typically
run too long and/or have imprecise stoichiometric control for
aerospace.
SUMMARY
[0003] A method of making a ceramic matrix composite (CMC) brake
component is provided according to various embodiments. The method
may include the steps of increasing a pressure in a mold containing
a mixture comprising a ceramic powder and fibers, pulsing an
electrical discharge across the mixture to generate a pulsed plasma
between particles of the ceramic powder, and increasing a
temperature in the mold using direct heating to generate the CMC
brake component. The temperature and pressure applied to the CMC
brake component may be reduced to complete the process.
[0004] In various embodiments, suitable ceramic powders may have a
range of sizes on the order of micrometer powder size and/or a
nanometer powder size. The ceramic powder may include SiC,
B.sub.4C, and/or Si.sub.3N.sub.4 TiB.sub.2, or other oxides and/or
borides, for example. The fibers may be chopped carbon fibers,
chopped SiC fibers, chopped glass fibers, or chopped oxide
fibers,for example. The mold may be made from graphite, refractory
metals, and/or ceramics. The CMC brake component may be machined to
form precise contours and/or openings. The direct heating may be
accomplished using resistance heating and/or inductive heating. The
CMC brake component may be a CMC brake disc, for example. The
temperature applied to the mixture may increase a maximum
temperature of about 2400.degree. C. The pressure may be increased
by actuating a punch to press against the mixture. The electrical
discharges may be pulsed across the mixture through a graphite
electrode coupled to the punch, a brass electrode coupled to the
graphite electrode, and a copper plate coupled to the brass
electrode. The electrical discharges may also be pulsed at a cycle
time of substantially 10 minutes. The fibers may have an interphase
coating made of, for example, pyrolytic carbon or boron
nitride.
[0005] The method of making a CMC brake component may also include
the steps of applying a pressure to a mixture comprising ceramic
powder and chopped fibers, pulsing electrical discharges across the
mixture to generate a pulsed plasma between particles of the
ceramic powder, increasing a temperature applied to the mixture
using direct heating to generate the CMC brake component, and
reducing the temperature and the pressure applied to the CMC brake
component. The ceramic powder may have a micrometer powder size or
a nanometer powder size, and the chopped fibers may have an
interphase coating.
[0006] In various embodiments, the ceramic powder may include SiC,
B.sub.4C, and/or Si.sub.3N.sub.4, oxides, and/or borides. The
chopped fibers comprise at least one of chopped carbon fiber,
chopped SiC fiber, chopped glass fiber, and/or chopped oxide fiber.
The interphase coating may include pyrolytic carbon or boron
nitride.
[0007] A CMC brake component for an aircraft is also provided. The
CMC brake component may include an annular disc. The annular disc
may include a ceramic material having a monolithic grain structure
and comprising SiC, B.sub.4C, and/or Si.sub.3N.sub.4. Chopped
fibers may be dispersed within the ceramic material and may have an
interphase coating. The chopped fibers may also include chopped
carbon fiber, chopped SiC fiber, chopped glass fiber, and/or
chopped oxide fiber.
[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
disclosure, 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. 1A illustrates a cross-sectional view of an exemplary
aircraft brake system comprising various brake components, in
accordance with various embodiments;
[0011] FIG. 1B illustrates a cutaway view of an exemplary aircraft
brake system comprising various brake components, in accordance
with various embodiments;
[0012] FIG. 2 illustrates a schematic diagram of a FAST device for
generating brake components using a FAST process, in accordance
with various embodiments;
[0013] FIG. 3A illustrates an exemplary process for generating CMC
brake components, in accordance with various embodiments; and
[0014] FIG. 3B illustrates a process of generating CMC brake
components relative to time, in accordance with various
embodiments.
DETAILED DESCRIPTION
[0015] 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.
[0016] With initial reference to FIGS. 1A and 1B, an aircraft wheel
braking assembly 10 that may be found on an aircraft is shown, in
accordance with various embodiments. Aircraft wheel braking
assembly may, for example, comprise a bogie axle 12, a wheel 14
including a hub 16 and a wheel well 18, a web 20, a torque take-out
assembly 22, one or more torque bars 24, a wheel rotational axis
26, a wheel well recess 28, an actuator 30, multiple brake rotors
32, multiple brake stators 34, a pressure plate 36, an end plate
38, a heat shield 40, multiple heat shield sections 42, multiple
heat shield carriers 44, an air gap 46, multiple torque bar bolts
48, a torque bar pin 50, a wheel web hole 52, multiple heat shield
fasteners 53, multiple rotor lugs 54, and multiple stator slots 56.
FIG. 113 illustrates a portion of aircraft wheel braking assembly
10 as viewed into wheel well 18 and wheel well recess 28.
[0017] Brake disks (e.g., interleaved rotors 32 and stators 34) are
disposed in wheel well recess 28 of wheel well 18. Rotors 32 are
secured to torque bars 24 for rotation with wheel 14, while stators
34 are engaged with torque take-out assembly 22. At least one
actuator 30 is operable to compress interleaved rotors 32 and
stators 34 for stopping the aircraft. In this example, actuator 30
is shown as a hydraulically actuated piston, but many types of
actuators are suitable, such as an electromechanical actuator.
Pressure plate 36 and end plate 38 are disposed at opposite ends of
the interleaved rotors 32 and stators 34. Rotors 32 and stators 34
can comprise any material suitable for friction disks, including
ceramics or carbon materials, such as a carbon/carbon
composite.
[0018] Through compression of interleaved rotors 32 and stators 34
between pressure plates 36 and end plate 38, the resulting
frictional contact slows rotation of wheel 14. Torque take-out
assembly 22 is secured to a stationary portion of the landing gear
truck s as a bogie beam or other landing gear strut, such that
torque take-out assembly- 22 and stators 34 are prevented from
rotating during braking of the aircraft.
[0019] Carbon and/or ceramic structures in the friction disks may
operate as a heat sink to absorb large amounts of kinetic energy
converted to heat during slowing of the aircraft, Heat shield 40
may reflect thermal energy away from wheel well 18 and back toward
rotors 32 and stators 34. With reference to FIG. 1A, a portion of
wheel well 18 and torque bar 24 is removed to better illustrate
heat shield 40 and heat shield sections 42. With reference to FIG.
1B, heat shield 40 is attached to wheel 14 and is concentric with
wheel well 18. Individual heat shield sections 42 may be secured in
place between wheel well 18 and rotors 32 by respective heat shield
carriers 44 fixed to wheel well 18. Air gap 46 is defined annularly
between heat shield sections 42 and wheel well 18.
[0020] Torque bars 24 and heat shield carriers 44 can be secured to
wheel 14 using bolts or other fasteners. Torque bar bolts 48 can
extend through a hole formed in a flange or other mounting surface
on wheel 14. Each torque bar 24 can optionally include at least one
torque bar pin 50 at an end opposite torque bar bolts 48, such that
torque bar pin 50 can be received through wheel web hole 52 in web
20. Heat shield sections 42 and respective heat shield carriers 44
can then be fastened to wheel well 18 by heat shield fasteners
53.
[0021] With reference to FIG. 2., one or more of the brake
components described herein may be made using a field assisted
sintering technique (FAST) device 200. FAST is also commonly
referred to as plasma activated sintering (PAS). FAST is a
technique that employs temperature, pressure, and high voltage to
rapidly sinter powders into monolithic materials. In essence, FAST
is a technique for pressure-assisted sintering activated by
electrical discharges between powder particles. Brake components
may be made using FAST to form the components using a mixture 212
of ceramic powder and fibers to form a ceramic matrix composite
(CMC) in a short time period.
[0022] In various embodiments, the fibers may comprise chopped
fibers. Mixture 212 is thus also referred to herein as CMC mixture
212. Examples of suitable fibers for use in mixture 212 may include
carbon fibers, aramid fibers, silicon carbide fibers, or other
types of fibers. Fiber filament diameters tend to be similar
between different types. Fiber filaments may have diameters of
substantially 5 .mu.m (0.0002 in), 10 .mu.m (0.0004 in), 20 .mu.m
(0.0008 in), 50 .mu.m (0.002 in), or 100 .mu.m (0.004 in), for
example. In that regard, fiber filament diameters may range from 7
.mu.m (0.0003 in)-15 .mu.m (0.0006 in), 5 .mu.m (0.0002. in)-50
.mu.m (0.002 in), or 3 .mu.m (0.0001 in)-100 .mu.m (0.004 in).
Length for chopped fiber may have a length ranging from 3.2 mm
(0.125 in)-50 mm (2 in), 2.5 .rho.mm (0.1 in)-100 mm (4 in), or 2
mm (0.07 in)-254 mm (10 in). Fiber preform lengths may scale with
the graphite mold up to the mold diameter.
[0023] In various embodiments, the fibers may be treated with an
interphase layer applied to inhibit fiber sintering to the ceramic
matrix. Examples of the interphase layer may include pyrolytic
carbon or boron nitride. The addition of the interphase layer to
the fibers may improve fracture toughness relative to other
composites prepared using FAST without such a coating.
[0024] In various embodiments, mixture 212 may also include ceramic
material in the form of ceramic powder. Suitable ceramic powders
may include SiC, B.sub.4C, and/or Si.sub.3N.sub.4, TiB.sub.2, or
other oxides and/or borides, for example. A range of particle sizes
may be employed in the ceramic powder used to make the CMC brake
components of the present disclosure. The particle size of the
ceramic powder is also referred to herein as powder size.
Typically, powder sizes in the micrometer or nanometer ranges are
appropriate for FAST processing. For example, a micron-sized
boron-carbide powder may be selected when the manufacturing tools
are not suited to operate on nano-sized powders without the powders
escaping from a die or mold. When chopped fiber is included in
mixture 212, a nano-sized powder may infiltrate into the fiber more
readily than the micron-sized powder. The powder size may include a
particle size distribution such as a bimodal particle distribution.
Powder size may thus be selected based on desired grain size with
smaller powder sizes yielding smaller grain sizes. For example,
nano-sized powder yields a smaller grain size than micrometer-sized
powder. The grain size may impact the thermal properties of the
finished component. Particle uniformity may vary. For example,
particle uniformity may vary in diameter by +/-80%. Particle size
may also vary according to a Gaussian distribution or by other
industrially accepted variances.
[0025] In various embodiments, the upper size limit for powder may
be defined by the inter-filament distance in a given tow bundle.
This varies, but will be something on the order of the filament
diameter, which may be substantially 5 .mu.m (0.0002 in), 10 .mu.m
(0.0004 in), 20 .mu.m (0.0008 in), 50 .mu.m (0.002 in), or 100
.mu.m (0.004 in), for example. Minimum size may be governed by
commercial availability and the issues with potential escape from
the graphite die if the powder is too small. For example, minimum
powder sizes may be on the order of 10 nm (4.times.10.sup.-7 in),
50 nm (2.times.10.sup.-6 in), 100 nm (4.times.10.sup.-6 in), 500 nm
(2.times.10.sup.-5 in), 5 .mu.m (0.0002 in), 10 .mu.m (0.0004 in),
20 .mu.m (0.0008 in), 50 .mu.m (0.002 in), or other suitable
sizes.
[0026] In various embodiments, FAST device 200 may include a ring
mold 214. Ring mold 214 may he an annular mold suitable for forming
circular or annular CMCs. Ring mold 214 may be formed from various
die materials including graphite, refractory metals, ceramics, or
other suitable materials. Although a ring mold 214 is shown for
exemplary purposes, other die shapes may be suitable for making
non-circular brake components.
[0027] In various embodiments, FAST device 200 may also include at
least one punch 210 to engage ring mold 214 along an inner diameter
and apply pressure during the FAST process. Punch 210 may thus be
an electronically or hydraulically actuated piston suitable for
applying substantial force to a heated material. For example, punch
210 may apply 1,400 kN, 1,200 kN-1,600 kN, 1,000 kN-2,000 kN, or
800 kN-2200 kN of force to CMC mixture 212. by actuating within an
inner diameter of ring mold 214 and compressing CMC mixture 212
along the axis of ring mold 214. In that regard, ring mold 214 may
be well suited for use in forming annular or disc-shaped brake
components such as friction disks.
[0028] In various embodiments, FAST device 200 may further include
an electrode 208, which may be graphite, coupled to and/or in
electronic communication with punch 210. An electrode 206, which
may be brass, may be coupled to and/or in electronic communication
with graphite electrode 208. Graphite electrode 208 may thus be
disposed between punch 210 and brass electrode 206. A copper plate
204 may be coupled to and/or in electronic communication with brass
electrode 206. Although copper, brass, and graphite are identified
for illustrative purposes, various metallic or otherwise conductive
materials may be used to form the electrodes of FAST device
200.
[0029] In various embodiments, transformer 216 may be in electronic
communication with copper plate 204 to provide electrical current
to mixture 212. Heat may be generated for the FAST process by
dispersing electrical current through the electrodes, ring mold
214, punch 210, and/or mixture 212. An induction coil 202 may be
disposed about ring mold 214 to provide inductive heating to CMC
mixture 212, though resistance heating by dissipating electrical
current through electrodes, ring mold 214 and mixture 212 may
provide sufficient heat for densification absent induction coil 202
in various embodiments. Direct heating through resistance heating
or otherwise may enhance densification over grain growth. Direct
heating may further allow for fast heating and cooling rates,
promote diffusion during the FAST process, and allow for the
intrinsic properties of nano and micro powders to remain present in
their fully dense product.
[0030] With reference to FIGS. 3A and 3B, an exemplary process 300
is shown for making CMC brake components, in accordance with
various embodiments. Process 300 may be completed using a FAST'
device 200 as disclosed in FIG. 2. Graph 301 depicts the various
changes in temperature, pressure, and CMC density over the course
of process 300. Process 300 may include mixing and/or depositing a
mixture 212 into a ring mold 214 (Step 302). Mixture 212 may
comprise ceramic powder and fibers, as described above. FAST device
200 may increase pressure applied to the mixture by actuating punch
210 to press against the mixture (Step 304). Step 304 may be
performed over period 305. The pressing force applied by punch 210
may be substantially 100 tons (90,700 kg), 150 tons (136,078 kg),
200 tons (181,437 kg), or another suitable pressing force.
[0031] In various embodiments, the FAST device may pulse electrical
discharges across the mixture (Step 306). Step 306 may be performed
over period 307. The pulsed electrical current may flow through the
ceramic powder along the boundaries of the ceramic particles making
up the ceramic powder and, as a result, generate pulsed plasma
between particles of the ceramic powder. Pulsed current gray be
applied using direct current. A typical cycle time for the CMC
process may span 10 minutes, 15 minutes, or 20 minutes, for
example. Current levels for the electrical pulses in FAST device
200 may vary depending on the machine. For example, the current
levels may range from 2,000 A-20,000 A, 1,000 A-25,000 A, or 500
A-30,000 A. FAST device 200 may also operate with electronic energy
levels of substantially 140 kVA, 200 kVA, or 240 kVA, for example.
FAST device 200 may increase the temperature in the mold using
resistance heating or other direct heating techniques described
herein. FAST device 200 may apply pressure for final densification
of the mixture (Step 308). Step 308 may be performed over period
309. Pressure may be applied using punch 210 as described above.
Appropriate maximum heating temperatures may be selected based on
the ceramic and fiber selected for mixture 212. Examples of
appropriate maximum temperatures may include substantially
3000.degree. C. (5432.degree. F.), 2600.degree. C. (4712.degree.
F.), 2400.degree. C. (4352.degree. F.), 2200.degree. C.
(3992.degree. F.), or 2000.degree. C. (3632.degree. F.). The term
substantially as to describe quantitatively measurable
characteristics herein such as temperature and pressure shall refer
to a variation in the quantitatively measurable characteristic
ranging by +/-5%.
[0032] In various embodiments, the FAST device may reduce the
voltage and the pressure at completion of the FAST process (Step
310). Step 310 may be performed over period 311. The resulting CMC
brake component gray be operated on further using milling,
machining, or other techniques to refine the finished product. A
suitable time to complete process 300 may be 1 hour, 2 hours, 5
hours, 10 hours, 20 hours or any other suitable time. The CMC FAST
process may thus yield a CMC brake component in a period on the
order of hours rather than days or weeks.
[0033] The FAST process may cause the ceramic particles to undergo
vaporization, solidification, volume diffusion, surface diffusion,
and/or grain boundary diffusion. As a result, the CMC brake
components made using the processes and systems described herein
may have a dense, monolithic grain structure. The dense, monolithic
grain structure may have controlled proportions of ceramic to fiber
resulting in a superior upper use temperature relative to
components made using MI, for example. The CMC brake components can
also be completed in a shorter period than similar components made
using CVI or PIP.
[0034] 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.
[0035] 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.
[0036] 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 killed 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.
[0037] 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.
* * * * *