U.S. patent application number 16/112451 was filed with the patent office on 2019-01-03 for thermally driven spring valve for turbine gas path parts.
This patent application is currently assigned to UNITED TECHNOLOGIES CORPORATION. The applicant listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to Tracy A. Propheter-Hinckley, Lane M. Thornton.
Application Number | 20190003333 16/112451 |
Document ID | / |
Family ID | 57749879 |
Filed Date | 2019-01-03 |
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United States Patent
Application |
20190003333 |
Kind Code |
A1 |
Propheter-Hinckley; Tracy A. ;
et al. |
January 3, 2019 |
THERMALLY DRIVEN SPRING VALVE FOR TURBINE GAS PATH PARTS
Abstract
A thermally driven spring valve for turbine gas path parts is
disclosed herein. A thermally driven spring valve includes a
bimetallic sheet comprising a base, a first finger portion
extending from the base and a second finger portion extending from
the base, the first finger portion having a first curvature vector
and the second finger portion have a second curvature vector,
wherein an exterior surface extends from the base through the first
finger portion and the second finger portion and an interior
surface extends from the base through the first finger portion and
the second finger portion, wherein the exterior surface of the
first finger portion is disposed proximate the interior surface of
the base wherein the exterior surface of the second finger portion
is disposed proximate the interior surface of the base. A thermally
driven spring valve may include perforations through a finger
portion.
Inventors: |
Propheter-Hinckley; Tracy A.;
(Manchester, CT) ; Thornton; Lane M.; (Tolland,
CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Farmington |
CT |
US |
|
|
Assignee: |
UNITED TECHNOLOGIES
CORPORATION
Farmington
CT
|
Family ID: |
57749879 |
Appl. No.: |
16/112451 |
Filed: |
August 24, 2018 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
14990528 |
Jan 7, 2016 |
10113441 |
|
|
16112451 |
|
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
Y02T 50/676 20130101;
F16K 31/002 20130101; F05D 2300/50212 20130101; F16K 15/16
20130101; F05D 2240/12 20130101; F05D 2300/17 20130101; F01D 9/02
20130101; F05D 2240/81 20130101; Y02T 50/60 20130101; F01D 17/12
20130101; F05D 2220/32 20130101; F05D 2300/143 20130101; F05D
2260/20 20130101; F01D 17/105 20130101; F01D 5/189 20130101; F01D
25/12 20130101; F05D 2240/126 20130101 |
International
Class: |
F01D 17/12 20060101
F01D017/12; F16K 15/16 20060101 F16K015/16; F01D 5/18 20060101
F01D005/18; F01D 17/10 20060101 F01D017/10; F01D 25/12 20060101
F01D025/12; F01D 9/02 20060101 F01D009/02; F16K 31/00 20060101
F16K031/00 |
Claims
1. A thermally driven spring valve comprising: a metallic sheet
comprising a base mount portion and a floating portion having a
curvature vector, wherein the base mount portion is coupled to a
wall of a chamber, wherein the floating portion is disposed
proximate an aperture in the wall.
2. The thermally driven spring valve of claim 1, wherein the
metallic sheet is coupled to the wall of the chamber by at least
one of brazing or welding. The thermally driven spring valve of
claim 1, wherein the metallic sheet is a bimetallic sheet.
4. The thermally driven spring valve of claim 1, wherein the
metallic sheet comprises at least one of steel, titanium, titanium
alloy, cobalt, cobalt alloy, platinum, or platinum alloy.
5. The thermally driven spring valve of claim 1, wherein the
metallic sheet has a coefficient of thermal expansion of between
about 0.6.times.10.sup.-6/K to about 25.times.10.sup.-6/K.
6. The thermally driven spring valve of claim 1, wherein the
chamber is coupled to a baffle.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application is a divisional of, and claims priority to,
and the benefit of U.S. patent application Ser. No. 14/990,528,
entitled " THERMALLY DRIVEN SPRING VALVE FOR TURBINE GAS PATH
PARTS," filed on Jan. 7, 2016. The '528 Application is hereby
incorporated by reference in its entirety for all purposes.
FIELD
[0002] The present disclosure relates to gas turbine engines, and
more specifically, to turbine bleed air cooling systems for a gas
turbine engine components and turbine section stator cooling.
BACKGROUND
[0003] Static vane airfoils and other turbine parts may incorporate
a cooling circuit which passes coolant, typically compressor bleed
air, through the surface of the airfoil and into the turbine gas
path. The amount of compressor bleed air passed through a part is
typically determined by that part's hottest running condition to
ensure that the part will survive that condition. For a typical
operating cycle, a part spends little time at its maximum operating
temperature. Thus, for the majority of its operating time, more
compressor bleed air than is needed may be flowed through the part.
Engine efficiency typically decreases as compressor bleed air
through a part increases.
SUMMARY
[0004] In various embodiments, the present disclosure provides a
thermally driven spring valve comprising a bimetallic sheet
comprising a base, a first finger portion extending from the base
and a second finger portion extending from the base. In various
embodiments, the first finger portion has a first curvature vector
and the second finger portion has a second curvature vector,
wherein an exterior surface extends from the base through the first
finger portion and the second finger portion and an interior
surface extends from the base through the first finger portion and
the second finger portion. In various embodiments, the exterior
surface of the first finger portion is disposed proximate the
interior surface extending from the base, and the exterior surface
of the second finger portion is disposed proximate the interior
surface extending from the base.
[0005] In various embodiments, a finger portion comprises a
perforation. In various embodiments, the bimetallic sheet comprises
at least one of cobalt, cobalt alloy, platinum, or platinum alloy.
In various embodiments, the curvature vector of the first finger
portion is variable in accordance with temperature. In various
embodiments, the bimetallic sheet has a coefficient of thermal
expansion of between about 0.6.times.10.sup.-6/K and about
15.times.10.sup.-6/K.
[0006] In various embodiments, the present disclosure provides a
stator vane for a gas turbine engine comprising a platform, an
airfoil extending from the platform, and a thermally driven spring
valve disposed within the core and comprising a bimetallic sheet
comprising a base, a first finger portion extending from the base,
and a second finger portion extending from the base. In various
embodiments, the airfoil has a core configured to transmit coolant
and extending from the platform into the airfoil, and the core has
an axial inner wall and an outer sidewall defining a portion of the
airfoil and having a sidewall perforation therethrough configured
to allow a flow of coolant from the core through the airfoil. In
various embodiments, the first finger portion has a first curvature
vector and the second finger portion having a second curvature
vector, wherein an exterior surface extends from the base through
the first finger portion and the second finger portion and an
interior surface extends from the base through the first finger
portion and the second finger portion. In various embodiments, the
exterior surface of the first finger portion is disposed proximate
the interior surface extending from the base, and the exterior
surface of the second finger portion is disposed proximate the
interior surface extending from the base. In various embodiments,
the thermally driven spring valve is disposed within a core,
coupled to a core wall at the base, wherein the first finger
portion and the second finger portion of the thermally driven
spring valve are configured to restrict the flow of coolant through
the sidewall perforation.
[0007] In various embodiments, a finger portion of the thermally
driven spring valve comprises a perforation. In various
embodiments, the base of the thermally driven spring valve is
coupled to the core by at least one of brazing or welding. In
various embodiments, the coolant is bleed air. In various
embodiments, the bimetallic sheet comprises at least one of cobalt,
cobalt alloy, platinum, or platinum alloy. In various embodiments,
the first finger portion has a first coefficient of thermal
expansion and the second finger portion has a second coefficient of
thermal expansion, the first coefficient of thermal expansion being
different from the second coefficient of thermal expansion. In
various embodiments, the bimetallic sheet has a coefficient of
thermal expansion of between 0.6.times.10.sup.-6/K and about
15.times.10.sup.-6/K. In various embodiments, the curvature vector
of the first finger portion is variable in accordance with
temperature. In various embodiments, a gas path airflow against the
stator vane has a temperature of about 1000.degree. F./537.degree.
C. to about 2000.degree. F./1093.degree. C.
[0008] In various embodiments, the present disclosure provides a
thermally driven spring valve comprising a metallic sheet
comprising a base mount portion and a floating portion having a
curvature vector, wherein the base mount portion is coupled to a
wall of a chamber, wherein the floating portion is disposed
proximate an aperture in the wall. In various embodiments, the
metallic sheet is coupled to the wall of the chamber by at least
one of brazing or welding. In various embodiments, the metallic
sheet is a bimetallic sheet. In various embodiments, the metallic
sheet comprises at least one of steel, titanium, titanium alloy,
cobalt, cobalt alloy, platinum, or platinum alloy. In various
embodiments, the metallic sheet has a coefficient of thermal
expansion of between about 0.6.times.10.sup.-6/K to about
25.times.10.sup.-6/K. In various embodiments, the chamber is
coupled to a baffle.
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. 1 is a schematic view of a gas turbine engine;
[0011] FIG. 2A illustrates a typical turbine section stator vane,
in accordance with various embodiments;
[0012] FIG. 2B illustrates a turbine section stator vane
incorporating a thermally driven spring valve, in accordance with
various embodiments;
[0013] FIG. 3A is a section through the turbine stator vane
incorporating a thermally driven spring valve showing the valve in
the open condition, in accordance with various embodiments;
[0014] FIG. 3B is a section through the turbine stator vane
incorporating a thermally driven spring valve showing the valve in
the closed condition, in accordance with various embodiments;
[0015] FIG. 4 illustrates a thermally driven spring valve in
accordance with various embodiments;
[0016] FIG. 5A illustrates a thermally driven spring valve in
accordance with various embodiments;
[0017] FIG. 5B illustrates a thermally driven spring valve in the
closed positon, in accordance with various embodiments;
[0018] FIG. 5C illustrates a thermally driven spring valve in the
open positon, in accordance with various embodiments;
[0019] FIG. 5D illustrates a thermally driven spring valve in
accordance with various embodiments;
[0020] FIG. 5E illustrates a thermally driven spring valve in the
open positon, in accordance with various embodiments; and
[0021] FIG. 5F illustrates a thermally driven spring valve in the
closed positon, in accordance with various embodiments.
DETAILED DESCRIPTION
[0022] The detailed description of exemplary embodiments herein
makes reference to the accompanying drawings, which show exemplary
embodiments by way of illustration. While these exemplary
embodiments are described in sufficient detail to enable those
skilled in the art to practice the disclosure, it should be
understood that other embodiments may be realized and that logical
changes and adaptations in design and construction may be made in
accordance with this disclosureand the teachings herein. Thus, the
detailed description herein is presented for purposes of
illustration only and not of limitation. The scope of the
disclosure is defined by the appended claims. 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. Surface shading lines may be used throughout the figures
to denote different parts but not necessarily to denote the same or
different materials. In some cases, reference coordinates may be
specific to each figure.
[0023] All ranges and ratio limits disclosed herein may be
combined. It is to be understood that unless specifically stated
otherwise, references to "a," "an," and/or "the" may include one or
more than one and that reference to an item in the singular may
also include the item in the plural.
[0024] With reference to FIG. 1, an exemplary gas turbine engine 2
is provided. Gas turbine engine 2 is a two-spool turbofan that
generally incorporates a fan section 4, a compressor section 6, a
combustor section 8 and a turbine section 10. Vanes 51 may be
disposed throughout the gas turbine engine 2. Alternative engines
include, for example, an augmentor section among other systems or
features. In operation, fan section 4 drives air along a bypass
flow-path B while compressor section 6 drives air along a core
flow-path C for compression and communication into combustor
section 8 then expansion through turbine section 10. Although
depicted as a turbofan gas turbine engine 2 herein, it should be
understood that the concepts described herein are not limited to
use with turbofans as the teachings is applicable to other types of
turbine engines including three-spool architectures. A gas turbine
engine may comprise an industrial gas turbine (IGT) or a geared
aircraft engine, such as a geared turbofan, or non-geared aircraft
engine, such as a turbofan, or may comprise any gas turbine engine
as desired.
[0025] Gas turbine engine 2 generally comprises a low speed spool
12 and a high speed spool 14 mounted for rotation about an engine
central longitudinal axis X-X' relative to an engine static
structure 16 via several bearing systems 18-1, 18-2, and 18-3. It
should be understood that bearing systems is alternatively or
additionally provided at locations, including for example, bearing
system 18-1, bearing system 18-2, and bearing system 18-3.
[0026] Low speed spool 12 generally comprises an inner shaft 20
that interconnects a fan 22, a low pressure compressor section 24,
e.g., a first compressor section, and a low pressure turbine
section 26, e.g., a second turbine section. Inner shaft 20 is
connected to fan 22 through a geared architecture 28 that drives
the fan 22 at a lower speed than low speed spool 12. Geared
architecture 28 comprises a gear assembly 42 enclosed within a gear
housing 44. Gear assembly 42 couples the inner shaft 20 to a
rotating fan structure. High speed spool 14 comprises an outer
shaft 80 that interconnects a high pressure compressor section 32,
e.g., second compressor section, and high pressure turbine section
34, e.g., first turbine section. A combustor 36 is located between
high pressure compressor section 32 and high pressure turbine
section 34. A mid-turbine frame 38 of engine static structure 16 is
located generally between high pressure turbine section 34 and low
pressure turbine section 26. Mid-turbine frame 38 supports one or
more bearing systems 18, such as 18-3, in turbine section 10. Inner
shaft 20 and outer shaft 80 are concentric and rotate via bearing
systems 18 about the engine central longitudinal axis X-X', 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.
[0027] The core airflow C is compressed by low pressure compressor
section 24 then high pressure compressor section 32, mixed and
burned with fuel in combustor 36, then expanded over high pressure
turbine section 34 and low pressure turbine section 26. Mid-turbine
frame 38 includes surface structures 40, which are in the core
airflow path. Turbines 26, 34 rotationally drive the respective low
speed spool 12 and high speed spool 14 in response to the
expansion.
[0028] Gas turbine engine 2 is, for example, a high-bypass geared
aircraft engine. The bypass ratio of gas turbine engine 2 is
optionally greater than about six (6). The bypass ratio of gas
turbine engine 2 is optionally greater than ten (10). Geared
architecture 28 is an epicyclic gear train, such as a star gear
system, e.g., 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 28 has a gear
reduction ratio of greater than about 2.3 and low pressure turbine
section 26 has a pressure ratio that is greater than about five
(5). The bypass ratio of gas turbine engine 2 is greater than about
ten (10:1). The diameter of fan 22 is significantly larger than
that of the low pressure compressor section 24, and the low
pressure turbine section 26 has a pressure ratio that is greater
than about 5:1. Low pressure turbine section 26 pressure ratio is
measured prior to inlet of low pressure turbine section 26 as
related to the pressure at the outlet of low pressure turbine
section 26 prior to an exhaust nozzle. It should be understood,
however, that the above parameters are exemplary of a suitable
geared architecture engine and that the present disclosure
contemplates other turbine engines including direct drive
turbofans.
[0029] An engine 2 may comprise a rotor blade 68 or a stator vane
51. Stator vanes 51 may be arranged circumferentially about the
engine central longitudinal axis X-X'. Stator vanes 51 may be
variable, meaning the angle of attack of the airfoil of the stator
vane may be variable relative to the airflow proximate to the
stator vanes 51. The angle of attack of the variable stator vane 51
may be variable during operation, or may be fixable for operation,
for instance, being variable during maintenance or construction and
fixable for operation. In various embodiments, it may be desirable
to affix a variable vane 51 in fixed position (e.g., constant angle
of attack).
[0030] A thermally driven spring valve, according to various
embodiments, may comprise a metallic or bimetallic sheet comprising
one or more finger portions, each having a curvature vector. A
metallic sheet (for example, a sheet of metal, a sheet of metal
having varying thickness, and/or a bimetallic sheet) may have a
coefficient of thermal expansion (CTE) which describes fractional
change in length of the sheet with respect to the change in
material temperature. Stated another way, the metal may expand
lengthways as temperature is increased. In that regard, the CTE may
be used to create motion along the length of the metallic or
bimetallic sheet as temperature changes.
[0031] In various embodiments, a thermally driven spring valve may
be disposed in a combustor bleed air gas path, such as in a core of
an airfoil (e.g., a stator vane), that is configured to actuate in
response to temperature change. In that regard, the amount of
combustor bleed air that passes through an airfoil, and thus enters
the gas path, may be controlled based upon temperature, for
example, the temperature of the airfoil. During operating
conditions that result in a relatively higher temperature for an
airfoil, the thermally driven spring valve may at least partially
open to allow for a greater flow rate of bleed air through the
airfoil, thereby increasing cooling capacity during an operating
condition that benefits from increased cooling capacity. During
operating conditions that result in a relatively lower temperature
for an airfoil, the thermally driven spring valve may at least
partially close to allow for a reduced flow rate of bleed air
through the airfoil, thereby decreasing cooling capacity during an
operating condition that benefits from such decreased cooling
capacity and reducing the amount of bleed air that flows through
the airfoil per unit time.
[0032] With reference now to FIG. 4, a thermally driven spring
valve 300 is formed from a rectangular bimetallic sheet 301 having
a base 302 and an interior surface 308 and an exterior surface 307.
The bimetallic sheet may have cutouts forming a first finger
portion 304 and a second finger portion 306. The bimetallic sheet
may be rolled about the base 302 such that interior surface 308 and
the exterior surface 307 of the bimetallic sheet 301 extend from
the base 302 into the first finger portion 304 and the second
finger portion 306 such that the first finger portion 304 have a
first exterior surface 310 and the second finger portion 306 has a
second exterior surface 312. The fingers are curled to have a
desired curvature vector which may vary between fingers such that
the first finger portion 304 has a first curvature vector 316 and
the second finger portion has a second curvature vector 318. The
fingers extend along their individual curvature vectors such that
the first exterior surface 310 of first finger portion 304 is
disposed proximate to the interior surface 308 extending from the
base 302 and the exterior surface 312 is disposed in a similar
manner proximate the interior surface 308 extending from the base
302. In various embodiments, one or more finger portions may have
perforations 314.
[0033] In various embodiments, the bimetallic sheet 301 may be
comprised of one or more of platinum, platinum alloy, cobalt,
cobalt alloy, other suitable metal, or other suitable metal alloy.
In various embodiments, the metallic composition ratio of the
bimetallic sheet may vary along a curvature vector of a finger to
tailor the CTE. The CTE may be in the range of about
0.6.times.10.sup.-6/K to about 15.times.10.sup.-6/K, where the term
about in this context only refers to +/-0.1.times.10.sup.-6/K.
[0034] In various embodiments and with reference to FIG. 2A and 2B,
a gas turbine stator vane 100 is illustrated. The stator vane
airfoil 104 extends from platform 102 into the gas path of the gas
turbine engine. The gas path airflow may have an extremely high
temperature (e.g., 1000.degree. F./537.degree. C. to 2000.degree.
F./1093.degree. C. or higher). Cores 105 include core 106. Core 106
has outer sidewall 108, as shown in FIG. 3A, defining a portion of
the surface of the stator vane airfoil 104 extending from the
platform 102 into the gas turbine stator vane 100. Cores 105 are
divided from each other along the airfoil chord by a member between
cores, for example, axial inner wall 110 of the core 106. Coolant
flows within the cores 105 and exits into the gas path at the
surface of the airfoil 104 via perforations such as perforations
202 through the surface of the airfoil 104. A thermally driven
spring valve 300 is disposed within core 106 and is configured to
regulate coolant flow from the core 106 through the perforations
202.
[0035] With reference now to FIGS. 3B and 4, in various
embodiments, the thermally driven spring valve 300 disposed within
core 106. Base 302 is coupled to axial inner wall 110 by, for
example, brazing. Thermally driven spring valve 300 may be coupled
to axial inner sidewall 110 by any suitable means, for example, by
brazing. Brazing surface 204 thus may couple thermally driven
spring valve 300 with axial inner wall 110. In various embodiments,
however, a brazing surface may couple thermally driven spring valve
300 with outer sidewall 108. In that regard, the heat received by
thermally driven spring valve 300 via conduction may be controlled
by either brazing to inner sidewall 110 or outer sidewall 108, as
outer sidewall 108 typically reaches higher temperatures than inner
sidewall 110 during operation. The thermally driven spring valve
300 has first finger portion 304 and second finger portion 306 with
first exterior surface 310 and second exterior surface 312, which
are configured to be disposed within core 106 and to selectably
obstruct the perforations 202. Such obstruction tends to restrict
coolant flow through the perforations 202. As heat flows along the
axial inner wall 110 into the first finger portion 304 and second
finger portion 306, the first curvature vector 316 and second
curvature vector 318 of the fingers are altered in proportion to
the finger material coefficient of thermal expansion (CTE).
Thermally driven spring valve 300 is shown in FIG. 3B in an
expanded state.
[0036] With reference now to FIGS. 3A and 4, in various
embodiments, the change in first curvature vector 316 and second
curvature vector 318 driven by thermal flux causes the thermally
driven spring valve 300 disposed within core 106 to retract into
core 106, away from the outer sidewall 108, thereby allowing
coolant to flow from core 106 through perforations 202. Thermally
driven spring valve 300 is shown in FIG. 3A in a contracted
state.
[0037] In various embodiments, one or more finger portions may have
perforations 314, as depicted in FIG. 4, to allow coolant to pass
through a finger portion, as depicted in FIG. 3B, when the finger
portion is an expanded state and would otherwise obstruct coolant
flow through one or more perforations in a vane. The perforations
314 may be configured to allow additional coolant flow where
thermal conditions do not cause a finger portion to be in a
contracted state.
[0038] With reference now to FIGS. 5A thru 5C, thermally driven
spring valve 400 is illustrated. A metallic sheet 402 having a
curvature vector 410, a floating portion 412 and a base mount
portion 406 is coupled to an outer surface of wall 408 of a chamber
404. A metallic sheet 402 thus is disposed at least partially
circumferentially about wall 408 of a chamber 404. The chamber 404
has aperture 414 in the wall 408 to provide for the flow of coolant
in or out of the chamber 404, which may be coupled to and in fluid
communication with a baffle 416 (also referred to as plenum 416).
The metallic sheet 402 is coupled at the base mount portion 406 to
the wall 408 by brazing or by a weld such that the floating portion
412 is disposed proximate to the aperture 414. As shown in FIG. 5B,
thermally driven spring valve 400 is in a contracted state. In that
regard, floating portion 412 obstructs aperture 414 and thereby
prevents coolant from flowing into aperture 414. As shown in FIGS.
5A and 5C, thermally driven spring valve 400 is in an expanded
state. In that regard, in response to a change in temperature,
floating portion 412 moves away from aperture 414 and thereby
allows coolant to flow into aperture 414, thereby allowing coolant
to flow into baffle 416.
[0039] With reference now to FIGS. 5D thru 5F, thermally driven
spring valve 500 is illustrated. A metallic sheet 502 having a
curvature vector 510, a floating portion 512 and a base mount
portion 506 is coupled to an inner surface of wall 508 of a chamber
504. A metallic sheet 502 thus is disposed at least partially
circumferentially within wall 508 of a chamber 504. Cap 582 is
disposed on top of chamber 504 but is illustrated transparently for
the sake of clarity. The chamber 504 has aperture 514 in the wall
508 to provide for the flow of coolant in or out the chamber 504,
which may be coupled to and in fluid communication with a baffle
516 (also referred to as plenum 516). The metallic sheet 502 is
coupled at the base mount portion 506 to the wall 508 by brazing or
by a weld such that the floating portion 512 is disposed proximate
to the aperture 514. As shown in FIG. 5E, thermally driven spring
valve 500 is in a contracted state. In that regard, floating
portion 512 obstructs aperture 514 and thereby prevents coolant
from flowing into aperture 514. As shown in FIGS. 5D and 5F,
thermally driven spring valve 500 is in an expanded state. In that
regard, in response to a change in temperature, floating portion
512 moves away from aperture 514 and thereby allows coolant to flow
into aperture 514, thereby allowing coolant to flow into baffle
516.
[0040] In various embodiments, to form a thermally driven spring
valve such as thermally driven spring valve 300 or thermally driven
spring valve 400 or thermally driven spring valve 500, a flat
metallic sheet is rolled such that it possesses a curvature vector,
then the linear expansion will follow the curvature vector of the
rolled sheet. In various embodiments, to form a thermally driven
spring valve such as thermally driven spring valve 300, a
bimetallic sheet may comprise two metals that have different CTEs.
In that regard, the difference in CTE may be used to create motion
along a curvature vector during temperature changes as a first
metal expands or contracts at a different rate than a second metal,
in response to temperature change. Stated another way, a flat
bimetallic sheet will expand along a natural curvature vector
defined by the difference between the CTEs (e.g. between about
0.6.times.10.sup.-6/K to about 25.times.10.sup.-6/K, where the term
about in this context only refers to +/-0.1.times.10.sup.-6/K) of
the selected metals with the curvature vector expansion being
larger than the small lengthways expansion. Rolling the bimetallic
sheet along this curvature vector may amplify the expansion.
Furthermore, by altering the CTE along the bimetallic sheet through
use of differing metals or metal compositions at different lengths,
the curvature vector may be altered with respect to itself.
[0041] In various embodiments the metallic sheet may be steel,
titanium, titanium alloy, platinum, platinum alloy, cobalt, cobalt
alloy, or a metal. In various embodiments, the metallic sheet may
be a bimetallic sheet. The metallic composition ratio of the
metallic sheet may vary along the curvature vector of the sheet to
tailor the CTE. The CTE of the metallic sheet may be in the range
of about thermal expansion in the range of about
0.6.times.10.sup.-6/K to about 25.times.10.sup.-6/K.
[0042] 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 disclosure. The scope of the disclosure 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
[0043] Systems, methods and apparatus are provided herein. In the
detailed description herein, references to "one embodiment", "an
embodiment", "various embodiments", 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
embodiments.
[0044] 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 herein is to be
construed under the provisions of 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.
* * * * *