U.S. patent application number 16/827200 was filed with the patent office on 2020-07-30 for bonded combustor wall for a turbine engine.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Grant O. Cook, III, Gary D. Roberge.
Application Number | 20200240639 16/827200 |
Document ID | 20200240639 / US20200240639 |
Family ID | 1000004753949 |
Filed Date | 2020-07-30 |
Patent Application | download [pdf] |
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United States Patent
Application |
20200240639 |
Kind Code |
A1 |
Roberge; Gary D. ; et
al. |
July 30, 2020 |
BONDED COMBUSTOR WALL FOR A TURBINE ENGINE
Abstract
A combustor wall is provided for a turbine engine. The combustor
wall includes a shell, a heat shield and a combustion chamber. The
heat shield is connected to the shell by a bonded connection, and
defines a portion of the combustion chamber. A cooling cavity is
defined between the shell and the heat shield.
Inventors: |
Roberge; Gary D.; (Tolland,
CT) ; Cook, III; Grant O.; (Spring, TX) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
1000004753949 |
Appl. No.: |
16/827200 |
Filed: |
March 23, 2020 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
15025012 |
Mar 25, 2016 |
10598378 |
|
|
PCT/US14/59486 |
Oct 7, 2014 |
|
|
|
16827200 |
|
|
|
|
61887744 |
Oct 7, 2013 |
|
|
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 2900/00018
20130101; F23R 3/007 20130101; F23R 3/06 20130101; F23R 3/002
20130101; F02C 7/18 20130101; F23R 2900/03042 20130101; F23R 3/005
20130101; F23R 2900/03044 20130101; F23R 2900/00017 20130101 |
International
Class: |
F23R 3/00 20060101
F23R003/00; F23R 3/06 20060101 F23R003/06; F02C 7/18 20060101
F02C007/18 |
Claims
1. An assembly for a turbine engine, comprising: a shell formed
from a first material comprising a nickel alloy; and a heat shield
connected to the shell by a bonded connection, the heat shield
formed from a second material that is different than the first
material, and the second material comprising composite material;
wherein a cavity is defined radially between the shell and the heat
shield.
2. The assembly of claim 1, wherein the bonded connection comprises
a partial transient liquid phase bonded connection.
3. The assembly of claim 1, wherein the bonded connection comprises
a transient liquid phase bonded connection.
4. The assembly of claim 1, further comprising: a combustor wall
for the turbine engine; the combustor wall comprising the shell and
the heat shield.
5. The assembly of claim 1, wherein the bonded connection directly
bonds the heat shield to the shell.
6. The assembly of claim 1, further comprising: an intermediate
element connected radially between the heat shield and the shell;
the bonded connection bonding the heat shield to the intermediate
element.
7. The assembly of claim 6, wherein the intermediate element is
bonded to the shell by a second bonded connection.
8. The assembly of claim 6, wherein the intermediate element
comprises a strain isolator.
9. The assembly of claim 1, further comprising: an intermediate
element connected radially between the heat shield and the shell;
the bonded connection bonding the intermediate element to the
shell.
10. The assembly of claim 9, wherein the heat shield is bonded to
the intermediate element by a second bonded connection.
11. The assembly of claim 9, wherein the intermediate element
comprises a strain isolator.
12. The assembly of claim 1, wherein the shell includes one or more
first cooling apertures that are fluidly coupled with the cavity;
and the heat shield includes one or more second cooling apertures
that are fluidly coupled with the cavity.
13. The assembly of claim 1, wherein the heat shield includes a
base plate and a protrusion; and the protrusion extends radially
out from the base plate, and is connected to the shell by the
bonded connection.
14. The assembly of claim 13, wherein the protrusion comprises a
rail.
15. An assembly for a turbine engine, comprising: a shell formed
from a first material comprising a nickel alloy; and a heat shield
connected to the shell by a bonded connection that comprises a
partial transient liquid phase bonded connection, the heat shield
formed from a second material that is different than the first
material, and the second material comprising composite material;
wherein a cavity is defined radially between the shell and the heat
shield.
16. The assembly of claim 15, further comprising: a combustor wall
for the turbine engine; the combustor wall comprising the shell and
the heat shield.
17. The assembly of claim 15, wherein the bonded connection
directly bonds the heat shield to the shell.
18. The assembly of claim 15, further comprising: an intermediate
element connected radially between the heat shield and the shell;
the bonded connection bonding the heat shield or the shell to the
intermediate element.
19. An assembly for a turbine engine, comprising: a first turbine
engine component formed from a first material comprising a nickel
alloy; and a second turbine engine component connected to the first
turbine engine component by a bonded connection, the second turbine
engine component formed from a second material that is different
than the first material, and the second material comprising
composite material.
20. The assembly of claim 19, wherein the first turbine engine
component is configured as a shell, and the second turbine engine
component is configured as a heat shield lining the shell.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation of U.S. patent
application Ser. No. 15/025,012 filed Mar. 25, 2016, which is a
national stage application of PCT Patent Application No.
PCT/US14/59486 filed Oct. 7, 2014, which claims priority to U.S.
Provisional Application No. 61/887,744 filed Oct. 7, 2013, which
are hereby incorporated herein by reference in their
entireties.
BACKGROUND OF THE INVENTION
1. Technical Field
[0002] This disclosure relates generally to a turbine engine and,
more particularly, to a combustor for a turbine engine.
2. Background Information
[0003] A floating-wall combustor for a turbine engine typically
includes a bulkhead that extends radially between inner and outer
combustor walls. Each of the combustor walls includes a shell and a
heat shield, which defines a radial side of a combustion chamber.
The heat shield is mechanically fastened to the respective shell by
a plurality of threaded studs.
[0004] The shell and the heat shield are typically formed from
nickel alloy material. The melting point and thermal erosion
characteristics of this nickel alloy material, however, limit an
upper-temperature bound of gas within the combustion chamber and,
thus, may limit performance and efficiency of the turbine engine.
In addition, the shell and/or the heat shield may thermally warp
during engine operation causing gas leakage between the shell and
the heat shield. Such gas leakage may further reduce turbine engine
performance and efficiency.
[0005] There is a need in the art for an improved turbine engine
combustor.
SUMMARY OF THE DISCLOSURE
[0006] According to an aspect of the invention, a combustor wall
for a turbine engine is provided. The combustor wall includes a
combustor shell and a combustor heat shield. The shell extends
axially along a centerline. The heat shield extends axially along
the centerline, and is connected to the shell by a bonded
connection. A cooling cavity is defined radially between the shell
and the heat shield.
[0007] According to another aspect of the invention, a combustion
section is provided for a turbine engine. The combustion section
includes a combustor. This combustor includes a shell, a heat
shield and a combustion chamber. The heat shield is connected to
the shell by a bonded connection, and defines a portion of the
combustion chamber. A cooling cavity is defined between the shell
and the heat shield.
[0008] The bonded connection may be a transient liquid phase bonded
connection. The bonded connection may be a partial transient liquid
phase bonded connection. The bonded connection may be a brazed
connection. The bonded connection may be a welded connection.
[0009] The bonded connection may bond the heat shield to the
shell.
[0010] The combustor or the combustor wall may include an
intermediate element. This intermediate element may be connected
radially and/or axially between the heat shield and the shell. The
bonded connection may bond the heat shield to the intermediate
element. Alternatively, the bonded connection may bond the
intermediate element to the shell.
[0011] The heat shield may be bonded to the intermediate element by
a second bonded connection where the bonded connection bonds the
intermediate element to the shell. Alternatively, the intermediate
element may be bonded to the shell by a second bonded connection
where the bonded connection bonds heat shield to the intermediate
element.
[0012] The intermediate element may be configured as or otherwise
include a strain isolator and/or any other combustor wall
component.
[0013] The shell may be formed from a first material. The heat
shield may be formed from a second material. This second material
may be different than the first material. For example, the first
material may be or otherwise include metallic material. The second
material may be or otherwise include composite material.
Alternatively, the second material may be the same as the first
material.
[0014] The combustor or the combustor wall may include a combustor
first wall, a combustor second wall and a combustor bulkhead. The
bulkhead may be connected radially between the first wall and the
second wall. The first wall, the second wall and the bulkhead may
define a combustion chamber. The first wall may be an inner wall
and the second wall may be an outer wall. Alternatively, the first
wall may be an outer wall and the second wall may be an inner wall.
The first wall, the second wall or the bulkhead may be formed by
the shell and the heat shield.
[0015] The shell may include one or more cooling apertures (e.g.,
impingement apertures) that are fluidly coupled with the cooling
cavity. The heat shield may also or alternatively include one or
more cooling apertures (e.g., effusion apertures) that are fluidly
coupled with the cooling cavity.
[0016] The heat shield may include a base plate and a protrusion.
The protrusion may extend radially and/or axially out from the base
plate, and may be connected to the shell by the bonded connection.
The protrusion may be configured as or otherwise include a
rail.
[0017] The foregoing features and the operation of the invention
will become more apparent in light of the following description and
the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0018] FIG. 1 is a side cutaway illustration of a geared turbine
engine;
[0019] FIG. 2 is a side sectional illustration of a portion of a
combustor section;
[0020] FIG. 3 is a perspective illustration of a portion of a
combustor;
[0021] FIG. 4 is a side sectional illustration of a portion of a
combustor;
[0022] FIG. 5 is a side sectional illustration of a portion of a
combustor wall; and
[0023] FIG. 6 is another side sectional illustration of a portion
of a combustor wall.
DETAILED DESCRIPTION OF THE INVENTION
[0024] FIG. 1 is a side cutaway illustration of a geared turbine
engine 20. This engine 20 extends along an axial centerline 22
between an upstream airflow inlet 24 and a downstream airflow
exhaust 26. The engine 20 includes a fan section 28, a compressor
section 29, a combustor section 30 and a turbine section 31. The
compressor section 29 includes a low-pressure compressor (LPC)
section 29A and a high-pressure compressor (HPC) section 29B. The
turbine section 31 includes a high-pressure turbine (HPT) section
31A and a low-pressure turbine (LPT) section 31B. The engine
sections 28-31 are arranged sequentially along the centerline 22
within an engine housing 34, which includes a first engine case 36
(e.g., a fan nacelle) and a second engine case 38 (e.g., a core
nacelle).
[0025] Each of the engine sections 28, 29A, 29B, 31A and 31B
includes a respective rotor 40-44. Each of the rotors 40-44
includes a plurality of rotor blades arranged circumferentially
around and connected to (e.g., formed integral with or mechanically
fastened, welded, brazed, adhered or otherwise bonded to) one or
more respective rotor disks. The fan rotor 40 is connected to a
gear train 46 (e.g., an epicyclic gear train) through a shaft 47.
The gear train 46 and the LPC rotor 41 are connected to and driven
by the LPT rotor 44 through a low speed shaft 48. The HPC rotor 42
is connected to and driven by the HPT rotor 43 through a high-speed
shaft 50. The shafts 47, 48 and 50 are rotatably supported by a
plurality of bearings 52. Each of the bearings 52 is connected to
the second engine case 38 by at least one stator such as, for
example, an annular support strut.
[0026] Air enters the engine 20 through the airflow inlet 24, and
is directed through the fan section 28 and into an annular core gas
path 54 and an annular bypass gas path 56. The air within the core
gas path 54 may be referred to as "core air". The air within the
bypass gas path 56 may be referred to as "bypass air".
[0027] The core air is directed through the engine sections 29-31
and exits the engine 20 through the airflow exhaust 26. Within the
combustor section 30, fuel is injected into an annular combustion
chamber 58 and mixed with the core air. This fuel-core air mixture
is ignited to power the engine 20 and provide forward engine
thrust. The bypass air is directed through the bypass gas path 56
and out of the engine 20 through a bypass nozzle 60 to provide
additional forward engine thrust. Alternatively, the bypass air may
be directed out of the engine 20 through a thrust reverser to
provide reverse engine thrust.
[0028] Referring to FIGS. 2 and 3, the combustor section 30
includes a combustor 62 arranged within an annular plenum 64. This
plenum 64 receives compressed core air from the compressor section
29 (see FIG. 1), and provides the core air to the combustor 62 as
described below in further detail.
[0029] The combustor 62 includes an annular combustor bulkhead 66,
a tubular combustor inner wall 68, a tubular combustor outer wall
70, and a plurality of fuel injector assemblies 72. The bulkhead 66
extends radially between and is connected to the inner wall 68 and
the outer wall 70. The inner wall 68 and the outer wall 70 each
extends axially along the centerline 22 from the bulkhead 66
towards the turbine section 31 (see FIG. 1), thereby defining the
combustion chamber 58. The fuel injector assemblies 72 are disposed
around the centerline 22, and mated with the bulkhead 66. Each of
the fuel injector assemblies 72 includes a fuel injector 74 mated
with a swirler 76. The fuel injector 74 injects the fuel into the
combustion chamber 58. The swirler 76 directs some of the core air
from the plenum 64 into the combustion chamber 58 in manner that
facilitates mixing the core air with the injected fuel. Quench
apertures 78 and 80 in the inner and/or the outer walls 68 and 70
direct additional core air into the combustion chamber 58 for
combustion.
[0030] Referring to FIG. 4, the inner wall 68 and/or the outer wall
70 each have a multi-walled structure; e.g., a hollow dual-walled
structure. The inner wall 68 and the outer wall 70 of FIG. 4, for
example, each respectively includes a tubular combustor shell 82,
84, a tubular combustor heat shield 86, 88 and one or more inner
wall cooling cavities 90, 92.
[0031] Each shell 82, 84 respectively extends axially along the
centerline 22 between an upstream end 94, 96 and a downstream end
98, 100. Each shell 82, 84 is connected to the bulkhead 66 at the
upstream end 94, 96. Each shell 82, 84 may be connected to a stator
vane assembly 102 (see FIG. 2) at the downstream end 98, 100.
[0032] Each shell 82, 84 may be cast, forged, machined and/or
otherwise formed from metallic material (e.g., sheet metal) such
as, for example, nickel (Ni) alloy. Examples of high-temperature
nickel alloy include, but are not limited to, IN625 alloy
(manufactured by Inco Alloys International, Inc. of Huntington, W.
Va., United States) and Hastelloy.RTM. X alloy (manufactured by
Haynes International, Inc. of Kokomo, Ind., United States). Each
shell 82, 84, of course, may also be formed from metallic and/or
non-metallic materials other than those described above.
[0033] Each heat shield 86, 88 respectively extends axially along
the centerline 22 between an upstream end 104, 106 and a downstream
end 108, 110. Each heat shield 86, 88 may respectively include a
plurality of heat shield panels 112, 114. The panels 112 may be
arranged into one or more axial sets 116 and 118, where the panels
112 in each set 116, 118 are disposed around the centerline 22 and
forming a hoop. The panels 114 may be arranged into one or more
axial sets 120 and 122, where the panels 114 in each set 120, 122
are disposed around the centerline 22 and forming a hoop.
Alternatively, the heat shield 86 and/or 88 may be configured from
one or more tubular bodies.
[0034] One or more of the panels 112, 114 may each include a panel
base 124 and one or more protrusions 126. The panel base 124 may be
configured as a generally curved (e.g., arcuate) plate that extends
axially along and circumferentially around the centerline 22. The
protrusions 126 extend radially outward or inward from the panel
base 124. Each of the protrusions 126 of FIG. 4 is configured as a
circumferentially extending rail. However, one or more of the
panels 112, 114 may also or alternatively include one or more other
types of protrusions; e.g., axially extending rails, discrete
pedestals, etc.
[0035] Each heat shield 86, 88 and its panels 112, 114 may be cast,
forged, machined and/or otherwise formed from metallic and/or
non-metallic materials. Examples of high-temperature metallic
materials include, but are not limited to, nickel alloy,
nickel-aluminum alloy and molybdenum alloy. Examples of
high-temperature non-metallic materials include, but are not
limited to, monolithic ceramic and ceramic matrix composite.
Examples of a monolithic ceramic include, but are not limited to,
monolithic Si.sub.3N.sub.4, Al.sub.2O.sub.3, SiC, WC, and
ZrO.sub.2. An example of a ceramic matrix composite is
melt-infiltrated SiC/SiC. Each heat shield 86, 88, of course, may
also be formed from metallic and/or non-metallic materials other
than those described above. In addition, one or more of the panels
112, 114 may be formed from different materials.
[0036] The heat shield 86 circumscribes the shell 82, and defines
an inner side of the combustion chamber 58. The heat shield 88 is
arranged radially within the shell 84, and defines an outer side of
the combustion chamber 58.
[0037] The heat shields 86 and 88 are respectively connected to the
shells 82 and 84, thereby defining the cooling cavities 90 and 92.
The cooling cavities 90 and 92 extend circumferentially and axially
between the protrusions 126; e.g., the circumferentially and
axially extending rails. The cooling cavities 90 and 92 extend
radially between the panel bases 124 and the respective shells 82
and 84. One or more of the cooling cavities 90 and 92 may each be a
discrete cavity. One or more of the cooling cavities 90 and 92 may
also or alternatively be fluidly coupled to one or more adjacent
cooling cavities.
[0038] The heat shields 86 and 88 are connected to the shells 82
and 84 by one or more bonded connections. One or more of the
protrusions 126, for example, may each be connected directly to the
respective shell 82, 84 by a transient liquid phase (TLP) or a
partial transient liquid phase (PTLP) bond; i.e., the respective
protrusions 126 are TLP-bonded or PTLP-bonded to the shell 82, 84.
Notably, such a TLP-bonded connection or a PTLP-bonded connection
may connect dissimilar and/or non-weldable materials together. One
or more of the panels 112 and 114 therefore may be formed from
non-weldable materials such as the high-temperature non-metallic
materials described above, and one or more of the shells 82 and 84
may be formed from the metallic materials described above. Of
course, the TLP-bonded connection or the PTLP-bonded connection may
also be used to connect similar and/or weldable materials together.
In addition, the (e.g., TLP or PTLP) bonded connection may reduce
or substantially eliminate gas leakage between the shell 82, 84 and
the protrusions 126.
[0039] TLP bonding may be described as a hybrid of brazing and
diffusion bonding processes that produces bonds at comparatively
lower temperatures than brazing and lower temperatures and/or
pressures than diffusion bonding. In TLP bonding, one or more
interlayers are disposed in joints between components (e.g., the
shell 82, 84 and the heat shield 86, 88) that are to be bonded
together. The components are then heated to a bonding temperature
to melt the interlayer(s), which fills gaps between the components.
Certain alloying elements of the interlayer(s) inter-diffuse with
the materials of the components, causing a compositional change in
the joint which isothermally solidifies and creates a bond between
the two components. The bonding temperature can be held for an
additional period of time to allow more homogenous diffusion. TLP
bonding may apply little or no pressure to the components as
compared to diffusion bonding, and thus may mitigate or
substantially prevents distortion of the components during the
bonding process. The composition of the interlayer(s) can be
selected according to the compositions of the materials that are
being bonded together.
[0040] PTLP bonding is a variation of TLP bonding which may be used
for joining non-metallic materials together. In PTLP bonding, a
multi-layer interlayer may be disposed in joints between components
(e.g., the shell 82, 84 and the heat shield 86, 88) that are to be
bonded together. This multi-layer interlayer may include three
layers: a thick refractory layer that does not melt during the
process, and two thinner layers on each side of the thick
refractory core layer. These layers may be formed of pure elements,
though alloys can alternatively be used for one or more of the
layers. The components are then heated to a bonding temperature to
melt the thin layers of the multi-layer interlayer. These thin
layers diffuse into the thick refractory layer of the interlayer,
causing a compositional change in the joint which isothermally
solidifies and creates a bond between the two components.
Substantially simultaneously, the thin liquid layers wet (adhere
to) the non-metallic components. The wetting is brought about by
the thin layers' composition(s) and/or an alloy of the thin
layer(s) with the refractory core layer. The bonding temperature
can be held for an additional period of time to allow more
homogenization of the resulting PTLP bond, further increasing the
bond's re-melting temperature. PTLP bonding may apply little or no
pressure to the components as compared to diffusion bonding, and
thus may mitigate or substantially prevents distortion of the
components during the bonding process. The composition of the
interlayer(s) can be selected according to the compositions of the
materials of the segments that are being bonded together. Thus, the
selection of first and second materials for bonded segments can be
subject to a mutually compatible interlayer or interlayers.
[0041] Various bonding material formats may be employed for TLP
bonding or PTLP bonding. Suitable bonding material formats may
include, but are not limited to, an alloy foil, a foil formed from
a pure metal, multiple layers of elemental foils, or combinations
thereof. Other formats such as, but not limited to, powder, powder
compact, braze paste, or one or more metallic layers applied by
electroplating, physical vapor deposition, or another suitable
metal deposition process, may also be used.
[0042] While the heat shields 86 and 88 are described above as
being TLP-bonded or PTLP-bonded to the shells 82 and 84, the
present invention is not limited to such a bonding technique. In
some embodiments, for example, one or more of the protrusions 126
may each be connected to the respective shell 82, 84 by a brazed
connection. In some embodiments, one or more of the protrusions 126
may each be connected to the respective shell 82, 84 by a welded
connection.
[0043] In some embodiments, one or more of the panels 112 and 114
may each include one or more cooling features. One or more of the
shells 82 and 84 may also or alternatively include one or more
cooling features. Examples of a cooling feature include, but are
not limited to, a pedestal, a chevron, a rib and a dimple. One or
more of these cooling features may be arranged within or outside of
one or more respective cooling cavities 90 and 92.
[0044] In some embodiments, one or more of the shells 82 and 84 may
each include a plurality of protrusions (e.g., rails) to which the
panels 112 and 114 may be bonded. In such embodiments, the
protrusions 126 may be respectively bonded to the protrusions of
the respective shell 82, 84. Alternatively, the protrusions 126 may
be omitted and the protrusions of the respective shell 82, 84 may
be bonded to the panel bases 124.
[0045] Referring to FIG. 5, one or more of the shells 82 and 84 may
each include one or more cooling apertures 128 that are fluidly
coupled with the respective cooling cavities 90, 92. These cooling
apertures 128 may be configured as impingement apertures, which
direct air from the plenum 64 to impinge against the respective
panels 112, 114. One or more of the panels 112 and 114 may also or
alternatively each include one or more cooling apertures 130 and
132 that are fluidly coupled with the respective cooling cavities
90, 92. The cooling apertures 130 may be configured as effusion
apertures, which provide film cooling within the combustion chamber
58 for the respective heat shield 86, 88. The cooling apertures 132
may be configured as channels that direct air axially and/or
circumferentially through respective protrusions 126 (e.g.,
rails).
[0046] Referring to FIG. 6, one or more of the panels 112 and 114
may be connected to the respective shell 82, 84 through one or more
intermediate elements 134. Each protrusion 126, for example, may be
TLP-bonded to the respective intermediate element 134, which may be
TLP-bonded to the respective shell 82, 84. An example of an
intermediate element is a porous metallic strain isolator. The
present invention, however, is not limited to the foregoing
intermediate element example.
[0047] In some embodiments, the bulkhead 66 may also or
alternatively be configured with a multi-walled structure; e.g., a
hollow dual-walled structure. The bulkhead 66, for example, may
include a shell and a heat shield that is directly or indirectly
connected to the shell by a bonded connection in a similar manner
as described above with respect to the inner and the outer walls 68
and 70.
[0048] The terms "upstream", "downstream", "inner" and "outer" are
used to orientate the components of the combustor 62 described
above relative to the turbine engine 20 and its axis 22. A person
of skill in the art will recognize, however, one or more of these
components may be utilized in other orientations than those
described above. The present invention therefore is not limited to
any particular combustor spatial orientations.
[0049] The combustor 62 may be included in various turbine engines
other than the one described above. The combustor 62, for example,
may be included in a geared turbine engine where a gear train
connects one or more shafts to one or more rotors in a fan section,
a compressor section and/or any other engine section.
Alternatively, the combustor 62 may be included in a turbine engine
configured without a gear train. The combustor 62 may be included
in a geared or non-geared turbine engine configured with a single
spool, with two spools (e.g., see FIG. 1), or with more than two
spools. The turbine engine may be configured as a turbofan engine,
a turbojet engine, a propfan engine, or any other type of turbine
engine. The present invention therefore is not limited to any
particular types or configurations of turbine engines.
[0050] While various embodiments of the present invention have been
disclosed, it will be apparent to those of ordinary skill in the
art that many more embodiments and implementations are possible
within the scope of the invention. For example, the present
invention as described herein includes several aspects and
embodiments that include particular features. Although these
features may be described individually, it is within the scope of
the present invention that some or all of these features may be
combined within any one of the aspects and remain within the scope
of the invention. Accordingly, the present invention is not to be
restricted except in light of the attached claims and their
equivalents.
* * * * *