U.S. patent application number 13/875370 was filed with the patent office on 2014-11-27 for conjoined gas turbine interface seal.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is General Electric Company. Invention is credited to Victor John Morgan, Neelesh Nandkumar Sarawate, David Wayne Weber.
Application Number | 20140348642 13/875370 |
Document ID | / |
Family ID | 51727560 |
Filed Date | 2014-11-27 |
United States Patent
Application |
20140348642 |
Kind Code |
A1 |
Weber; David Wayne ; et
al. |
November 27, 2014 |
CONJOINED GAS TURBINE INTERFACE SEAL
Abstract
A device including a conjoined laminate interface seal shaped
for reducing inter-seal gap (e.g., an angled gap, an `L`-shaped
gap, etc.) leakage in gas turbines is disclosed. In one embodiment,
a seal device for a gas turbine includes: a first flange shaped to
be disposed within a first slot of a first arcuate component and a
first adjacent slot of a second arcuate component; a conjoined
layer connected to a first surface of the first flange, the first
surface configured to face a working fluid flow of the gas turbine;
and a second flange shaped to be disposed within a second slot of
the first arcuate component and a second adjacent slot of the
second arcuate component, the second flange including a second
surface connected to the conjoined layer.
Inventors: |
Weber; David Wayne;
(Simpsonville, SC) ; Morgan; Victor John;
(Simpsonville, SC) ; Sarawate; Neelesh Nandkumar;
(Niskayuna, NY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company; |
|
|
US |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
51727560 |
Appl. No.: |
13/875370 |
Filed: |
May 2, 2013 |
Current U.S.
Class: |
415/170.1 ;
277/500 |
Current CPC
Class: |
F01D 11/005 20130101;
F05D 2250/75 20130101; F05D 2240/59 20130101; F05D 2240/11
20130101 |
Class at
Publication: |
415/170.1 ;
277/500 |
International
Class: |
F01D 11/00 20060101
F01D011/00; F01D 11/24 20060101 F01D011/24 |
Claims
1. A seal device, the seal device comprising: a first flange shaped
to be disposed within a first slot of a first arcuate component and
a first adjacent slot of a second arcuate component; a conjoined
layer connected to a first surface of the first flange, the first
surface configured to face a working fluid flow; and at least one
secondary flange shaped to be disposed within a second slot of the
first arcuate component and a second adjacent slot of the second
arcuate component, the at least one secondary flange including a
second surface connected to the conjoined layer.
2. The seal device of claim 1, wherein the first flange and the at
least one secondary flange include a plurality of layers.
3. The seal device of claim 1, wherein the conjoined layer is
integrated in to the first flange and the at least one secondary
flange.
4. The seal device of claim 1, wherein the conjoined layer is
shaped to continuously contact the first slot and the second
slot.
5. The seal device of claim 1, wherein the conjoined layer includes
a first portion connected to the first flange and a second portion
connected to the at least one secondary flange, and wherein the
first portion and the second portion are connected across a gap
between the first flange and the at least one secondary flange and
are shaped to form a continuous surface across both the first
flange and the at least one secondary flange.
6. The seal device of claim 1, wherein the at least one secondary
flange is oriented at an angle relative to the first flange.
7. The seal device of claim 1, wherein the conjoined layer is
substantially the same width as the first flange and the at least
one second flange, and wherein the conjoined layer forms the first
surface of the first flange and the second surface of the at least
one secondary flange.
8. A gas turbine, comprising: a first arcuate component including a
first slot and a second slot on an end of the first arcuate
component; a second arcuate component located adjacent to the first
arcuate component and including a first adjacent slot and a second
adjacent slot on an end of the first arcuate component, the first
adjacent slot and the second adjacent slot aligned with the first
slot and the second slot of the first arcuate component; and a seal
device including: a first flange disposed within the first slot of
the first arcuate component and the first adjacent slot of the
second arcuate component; a conjoined layer connected to a first
surface of the first flange, the conjoined layer facing a working
fluid flow of the gas turbine; and a second flange disposed within
the second slot of the first arcuate component and the second
adjacent slot of the second arcuate component, the second flange
including a second surface connected to the conjoined layer.
9. The gas turbine of claim 8, wherein the first flange and the
second flange include a plurality of layers.
10. The gas turbine of claim 8, wherein the conjoined layer is
integrated in to the first flange and the second flange.
11. The gas turbine of claim 8, wherein the conjoined layer is
shaped to continuously contact the first slot and the second
slot.
12. The gas turbine of claim 8, wherein the conjoined layer
includes a first portion connected to the first flange and a second
portion connected to the second flange, and wherein the first
portion and the second portion are connected across a gap between
the first flange and the second flange and are shaped to form a
continuous surface across both the first flange and the second
flange.
13. The gas turbine of claim 8, wherein the second flange is
oriented at an angle relative to the first flange.
14. The gas turbine of claim 8, wherein the conjoined layer is
substantially the same width as the first flange and the second
flange, and wherein the conjoined layer forms the first surface of
the first flange and the second surface of the second flange.
15. A gas turbine, comprising: a first arcuate component including
a first slot and a second slot on an end of the first arcuate
component, wherein an inner surface of the first arcuate component
is exposed to a working fluid flow and an outer surface of the
first arcuate component is exposed to a coolant flow; a second
arcuate component located adjacent to the first arcuate component
and including a first adjacent slot and a second adjacent slot on
an end of the first arcuate component, the first adjacent slot and
the second adjacent slot aligned with the first slot and the second
slot of the first arcuate component, wherein the second arcuate
component includes an adjacent outer surface and an adjacent inner
surface, the adjacent inner surface exposed to the working fluid
flow and the adjacent outer surface exposed to the coolant flow;
and a first flange disposed within the first slot of the first
arcuate component and the first adjacent slot of the second arcuate
component; a conjoined layer connected to the first flange and
facing the working fluid flow of the gas turbine; and a second
flange connected to the conjoined layer and disposed within the
second slot of the first arcuate component and the second adjacent
slot of the second arcuate component.
16. The gas turbine of claim 15, wherein the conjoined layer is
integrated in to the first flange and the second flange.
17. The gas turbine of claim 15, wherein the conjoined layer is
shaped to continuously contact the first slot and the second
slot.
18. The gas turbine of claim 15, wherein the second flange is
oriented at an angle relative to the first flange.
19. The gas turbine of claim 15, wherein conjoined layer includes a
first portion connected to the first flange and a second portion
connected to the second flange, and wherein the first portion and
the second portion are connected across a gap between the first
flange and the second flange and are shaped to form a continuous
surface across both the first flange and the second flange.
20. The gas turbine of claim 15, wherein the conjoined layer is
substantially the same width as the first flange and the second
flange, and wherein the conjoined layer forms the first surface of
the first flange and the second surface of the second flange.
Description
FIELD OF THE INVENTION
[0001] This invention relates generally to power plant systems and,
more particularly, to conjoined seal systems (e.g., a conjoined
laminate seal system) and devices for reducing interface leakage
losses in gas turbines.
BACKGROUND OF THE INVENTION
[0002] The operation of some power plant systems, for example
certain simple-cycle and combined-cycle power plant systems,
include the use of gas turbines. The operation of these gas
turbines includes the use of pressurized fluid flows at extreme
temperatures traveling through flowpaths of the gas turbine, these
pressurized fluid flows regulating operation of the turbine and
driving a rotor of the turbine (e.g., power generation). The
working fluid flow path (e.g., the main gas-flow path) in a gas
turbine commonly includes the operational components of a
compressor inlet, a compressor, a turbine section and a gas
outflow. There are also secondary flows that are used to cool the
various heated components of the turbine, these secondary flows
passing about an outside surface of the turbine components and
remaining substantially isolated from the main gas-flow path.
Mixing of these flows and gas leakage in general, from or into the
gas-flow path, may be detrimental to turbine performance.
[0003] The operational components of a gas turbine are contained in
a casing. The turbine is commonly surrounded annularly by adjacent
arcuate components. As used herein, the term "arcuate" may refer to
a member, component, part, etc. having a curved or partially curved
shape. The adjacent arcuate components include outer shrouds, inner
shrouds, nozzle blocks, and diaphragms. Arcuate components may
provide a container for the gas-flow path in addition to the casing
alone. Arcuate components may secure other components of the
turbine and define spaces within the turbine. Between each adjacent
pair of arcuate components is an interface (e.g., a space, a gap,
etc.) that permits thermal expansion of the arcuate components of
the gas turbine. During operation, working fluid (e.g., a high
temperature flow) may flow through an interior of the container
formed by an inside surface of the arcuate components, and cooling
flows may pass across an outer surface of the arcuate
components.
[0004] Slots are defined on the sides of each arcuate component for
receiving a set of seals in cooperation with an adjacent slot of an
adjacent arcuate component. The set of seals are placed in the slot
to prevent leakage across the interface (e.g., between the areas of
the turbine on either side of the seal). These areas include the
main gas-flow path and secondary cooling flows which pass across
the outer surface of the turbine components (e.g., arcuate
components) to thermally regulate the gas turbine. These secondary
cooling flows substantially surround the main gas-flow path at a
high pressure relative to a pressure of the main gas-flow path.
[0005] The slots within the end of a particular arcuate component
may be connected and be angled in orientation relative to one
another. As a result, when a set of planar seals is inserted in to
the slots of a given arcuate component, a gap is formed between the
set of planar seals. This gap permits leakage between the internal
and external areas of the gas turbine (e.g., between secondary
cooling flows and the main gas-flow path). Reducing this gap
improves gas turbine performance. In some systems, a third seal may
be connected on a top surface of adjacent planar seals to span the
gap there between and partially obstruct leakage flow through the
gap. However, this third seal may cover the gap from the high
pressure side but not seal the gap between the set of planar seals.
During operation fluid may still flow along the length of the set
of planar seals on the low pressure side beneath the third
seal.
BRIEF DESCRIPTION OF THE INVENTION
[0006] A first aspect of the disclosure provides a seal device for
a gas turbine including: a first flange shaped to be disposed
within a first slot of a first arcuate component and a first
adjacent slot of a second arcuate component; a conjoined layer
connected to a first surface of the first flange, the first surface
configured to face a working fluid flow of the gas turbine; and a
second flange shaped to be disposed within a second slot of the
first arcuate component and a second adjacent slot of the second
arcuate component, the second flange including a second surface
connected to the conjoined layer.
[0007] A second aspect of the disclosure provides a gas turbine,
including: a first arcuate component including a first slot and a
second slot on an end of the first arcuate component; a second
arcuate component located adjacent to the first arcuate component
and including a first adjacent slot and a second adjacent slot on
an end of the first arcuate component, the first adjacent slot and
the second adjacent slot aligned with the first slot and the second
slot of the first arcuate component; and a seal device including: a
first flange disposed within the first slot of the first arcuate
component and the first adjacent slot of the second arcuate
component; a conjoined layer connected to a first surface of the
first flange, the conjoined layer facing a working fluid flow of
the gas turbine; and a second flange disposed within the second
slot of the first arcuate component and the second adjacent slot of
the second arcuate component, the second flange including a second
surface connected to the conjoined layer.
[0008] A third aspect of the disclosure provides a gas turbine,
including: a first arcuate component including a first slot and a
second slot on an end of the first arcuate component, wherein an
inner surface of the first arcuate component is exposed to a
working fluid flow and an outer surface of the first arcuate
component is exposed to a coolant flow; a second arcuate component
located adjacent to the first arcuate component and including a
first adjacent slot and a second adjacent slot on an end of the
first arcuate component, the first adjacent slot and the second
adjacent slot aligned with the first slot and the second slot of
the first arcuate component, wherein the second arcuate component
includes an adjacent outer surface and an adjacent inner surface,
the adjacent inner surface exposed to the working fluid flow and
the adjacent outer surface exposed to the coolant flow; and a first
flange disposed within the first slot of the first arcuate
component and the first adjacent slot of the second arcuate
component; a conjoined layer connected to the first flange and
facing the working fluid flow of the gas turbine; and a second
flange connected to the conjoined layer and disposed within the
second slot of the first arcuate component and the second adjacent
slot of the second arcuate component.
[0009] These and other aspects, advantages and salient features of
the invention will become apparent from the following detailed
description, which, when taken in conjunction with the annexed
drawings, where like parts are designated by like reference
characters throughout the drawings, disclose embodiments of the
invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0010] The above and other aspects, features and advantages of the
invention will be better understood by reading the following more
particular description of the invention in conjunction with the
accompanying drawings.
[0011] FIG. 1 shows a perspective partial cut-away view of a known
gas turbine.
[0012] FIG. 2 shows a perspective view of known arcuate components
in an annular arrangement.
[0013] FIG. 3 shows a cross-sectional longitudinal view of a known
turbine of a gas turbine.
[0014] FIG. 4 shows a cross-sectional end view of an arcuate
component including a seal device disposed in connected slots in
accordance with embodiments of the invention.
[0015] FIG. 5 shows a cross-sectional end view of an arcuate
component including a seal device disposed in connected slots in
accordance with embodiments of the invention.
[0016] FIG. 6 shows a cross sectional axial view along line A-A in
FIG. 5 of one embodiment of two adjacent arcuate components with a
seal device disposed in the slots in accordance with embodiments of
the invention.
[0017] FIG. 7 shows a schematic view of portions of a multi-shaft
combined cycle power plant in accordance with an aspect of the
invention.
[0018] FIG. 8 shows a schematic view of portions of a single-shaft
combined cycle power plant in accordance with an aspect of the
invention.
[0019] It is noted that the drawings of the disclosure may not
necessarily be to scale. The drawings are intended to depict only
typical aspects of the disclosure, and therefore should not be
considered as limiting the scope of the disclosure. It is
understood that elements similarly numbered between the FIGURES may
be substantially similar as described with reference to one
another. Further, in embodiments shown and described with reference
to FIGS. 1-8, like numbering may represent like elements. Redundant
explanation of these elements has been omitted for clarity.
Finally, it is understood that the components of FIGS. 1-8 and
their accompanying descriptions may be applied to any embodiment
described herein.
DETAILED DESCRIPTION OF THE INVENTION
[0020] As indicated herein, aspects of the invention provide for
systems and devices shaped to reduce interface leakage through gaps
between adjacent arcuate components in a gas turbine. These systems
and devices include a unitary seal device (e.g., a conjoined seal
device) which includes a first flange shaped to connect to/be
disposed within a first slot of a first arcuate component and a
first adjacent slot of a second arcuate component, and second
flange shaped to connect to/be disposed within a second slot of the
first arcuate component and a second adjacent slot of the second
arcuate component. The first flange and the second flange are
connected by a conjoined layer which forms a continuous surface
across both the first flange and the second flange. The conjoined
layer is integrated with/in to the first and second flanges and
extends across a gap between the first arcuate component and the
second arcuate component. The conjoined layer is located proximate
a low pressure or hot gas path side of the seal and closes the gap
between the first and second arcuate components, thereby forming a
low pressure surface for both the first flange and the second
flange on the hot gas path side. During operation of the gas
turbine, the seal device/conjoined layer is forced toward (e.g.,
pressure loaded) the hot gas path of the gas turbine by a high
pressure secondary cooling flow and sealingly engages/connects with
portions of the first slot and the second slot. In contrast to
conventional systems, which may include a third seal formed on top
of adjacent planar seals disposed in the first and second arcuate
components, embodiments of the current invention provide for a
conjoined layer which is integral to both first and second flanges
and is located on a low pressure side of the unitary seal device.
The conjoined layer forms a continuous seal surface across/for the
first and second flanges which spans the gap between the first and
second arcuate components.
[0021] As used herein, the terms "axial" and/or "axially" refer to
the relative position/direction of objects along axis A, which is
substantially perpendicular to the axis of rotation of the
turbomachine (in particular, the rotor section). As further used
herein, the terms "radial" and/or "radially" refer to the relative
position/direction of objects along axis (r), which is
substantially perpendicular with axis A and intersects axis A at
only one location. Additionally, the terms "circumferential" and/or
"circumferentially" refer to the relative position/direction of
objects along a circumference which surrounds axis A but does not
intersect the axis A at any location.
[0022] Referring to FIG. 1, a perspective view of one embodiment of
a gas turbine 2 is shown. In this embodiment, gas turbine 2
includes a compressor inlet 4, a compressor 6, a plurality of
combustors 8, a compressor discharge 10, a turbine section 12
including a plurality of turbine blades 14, a rotor 16 and a gas
outflow 18. Compressor inlet 4 supplies air to compressor 6.
Compressor 6 supplies compressed air to combustors 8 where it mixes
with fuel. Combustion gases from combustors 8 propels turbine
blades 14 which rotate rotor 16 (generating power). A casing 20
forms an outer enclosure that encloses compressor inlet 4,
compressor 6, plurality of combustors 8, compressor discharge 10,
turbine section 12, turbine blades 14, rotor 16 and gas outflow 18.
Gas turbine 2 is only illustrative; teachings of the invention may
be applied to a variety of gas turbines.
[0023] Referring to FIG. 2, a perspective view of one embodiment of
an annular arrangement 22 of arcuate components 24 of turbine
section 12 of gas turbine 2 is shown. This view shows seven arcuate
components 24 with one arcuate component removed for illustrative
purposes. The end of each arcuate component 24 includes slots 26.
Between each arcuate component 22 is a gap 28. A person skilled in
the art will readily recognize that annular arrangement 22 may have
any number of arcuate components 24; that arcuate components 24 may
be of varying shapes and sizes; and that arcuate components 24 may
serve different functions in gas turbine 2. For example, arcuate
components in a turbine may include, but are not limited to, outer
shrouds, inner shrouds, nozzle blocks, and diaphragms as discussed
below.
[0024] Referring to FIG. 3, a cross-sectional view of one
embodiment of turbine section 12 of gas turbine 2 (FIG. 1) is
shown. In this embodiment, casing 20 encloses a plurality of outer
shrouds 30, an inner shroud 32, a plurality of nozzle blocks 34, a
plurality of diaphragms 36, and turbine blades 14. Each of the
outer shrouds 30, inner shroud 32, nozzle blocks 34 and diaphragms
36 are arcuate components 24. Each of the outer shrouds 30, inner
shrouds 32, nozzle blocks 34 and diaphragms 36 have slots 26 in a
side thereof. In this embodiment, outer shrouds 30 connect to
casing 20; inner shroud 32 connects to outer shrouds 30; nozzle
blocks 34 connect to outer shrouds 30; and diaphragms 28 connect to
nozzle blocks 34. A person skilled in the art will readily
recognize that many different arrangements and geometries of
arcuate components are possible. Alternative embodiments may
include different arcuate components, more arcuate components, or
less arcuate components.
[0025] Turning to FIG. 4, an end view of a first arcuate component
110 including a conjoined seal device 130 disposed in a first slot
120 and a second slot 122 on an end of first arcuate component 110
is shown according to embodiments of the invention. First slot 120
and second slot 122 connect to one another and are oriented at an
angle `.alpha.` relative to one another. Conjoined seal device 130
may include a first flange 132 (e.g., a shim) shaped to be disposed
in first slot 120 and a second flange 134 (e.g., a shim) shaped to
be disposed in second slot 122. First flange 132 and second flange
134 may be connected by a conjoined layer 136 which may contact
first component surfaces 128 of first arcuate component 110. In an
embodiment, conjoined seal device 130 and/or conjoined layer 136
may be pressed against first component surfaces 128 by a
pressurized coolant flow 150 which has a pressure value which is
higher than a pressure in a working fluid passage of turbine 2
(shown in FIG. 1). Conjoined layer 136 may span a gap 138 between
first flange 132 and second flange 134 and form a substantially
continuous surface across first flange 132 and second flange 134.
In one embodiment, conjoined seal device 130 may include a laminate
seal where conjoined layer 136 includes an outermost layer of the
laminate seal. In another embodiment, first flange 132, second
flange 134, and conjoined layer 136 may be formed as a unitary
body. Conjoined layer 136 may include a first portion 170 connected
to first flange 132 and a second portion 172 connected to second
flange 134.
[0026] In an embodiment, a set of high pressure surfaces 127 (e.g.,
surfaces oriented to face a high pressure fluid flow, surfaces
oriented to face secondary coolant flow, etc.) on first flange 132
and second flange 134 may be oriented at any angle `.alpha.`
relative to one another. In one embodiment, first portion 170 and
second portion 172 of conjoined layer 136 may be oriented at any
angle `.omega.` relative to one another. In an embodiment, angle
.alpha. may be less than about 90 degrees and angle .omega. may be
greater than about 180 degrees.
[0027] As shown in FIG. 5, first flange 132 and second flange 134
may be oriented at any angle `.alpha.` relative to one another and
be connected by conjoined layer 136 in accordance with embodiments
of the invention. In an embodiment, first flange 132 and second
flange 134 may have a length of about 0.2 inches to about 24
inches. During operation, conjoined seal device 130 may contact
first component surfaces 128 (shown in FIG. 4) forming a pressure
boundary 180 (shown in phantom) between pressurized secondary
coolant flows 150 and a working fluid flow 154 in the main gas path
flow of turbine 2. Pressure boundary 180 may be formed between
first arcuate component 110 and conjoined seal device 130 and may
extend across an entirety of conjoined seal device 130. In an
embodiment, a single continuous pressure boundary may be formed
between conjoined layer 136 and first component surfaces 128 (e.g.,
locating contact between conjoined seal device 130 and first
arcuate component 110 at pressure boundary 180). In an embodiment,
conjoined seal device 130 may include a plurality of
apertures/slots/features/tunnels configured to circulate a coolant
flow through conjoined seal device 130.
[0028] Turning to FIG. 6, a cross sectional axial view along line
A-A of FIG. 5 of first arcuate component 110 adjacent to a second
arcuate component 210 is shown in accordance with embodiments of
the invention. In an embodiment, gap 28 (e.g., an interface) is
formed between first arcuate component 110 and second arcuate
component 210 as a part of a thermal clearance. A first adjacent
slot 222 and a second adjacent slot 220 (shown in phantom) on
second arcuate component 210 are aligned with first slot 120 (shown
in phantom) and second slot 122 such that conjoined seal device 130
may be disposed within first slot 120, second slot 122, first
adjacent slot 220, and second adjacent slot 222 simultaneously. The
disposition of first flange 132 and second flange 134 leaves a gap
138 (shown in phantom) between first flange 132 and second flange
134 which is spanned by conjoined layer 136 thereby forming a
continuous surface as shown in FIG. 6. Gap 138 may be substantially
defined by a bottom of first flange 132, a bottom of second flange
134 and conjoined layer 136. The continuous surface of conjoined
layer 136 sealingly contacts inner surfaces 128 of slots 120, 122,
220, and 222, preventing leakage flow directly through gap 28
and/or slots 120, 122, 220, and 222. FIG. 6 shows first flange 132
disposed in first slot 120 and first adjacent slot 220; and second
flange 134 disposed in second slot 122 and second adjacent slot
222. As can be seen in FIG. 6, conjoined layer 136 spans gap 28 and
connects first flange 132 and second flange 134 across a
substantially radially inward surface 128 of arcuate components 110
and 210.
[0029] In one embodiment, conjoined layer 136, first flange 132 and
second flange 134 are integral to one another (e.g., formed as a
substantially uniform body) and include at least one of laminate,
silicate, ceramic, metal, a cloth-layer, a cloth-layer assemblage,
and/or a foil-layer assemblage. For example metal, may include
stainless steel and/or Inconel.RTM. from Huntington Alloys
Corporation. A cloth layer comprises (and preferably consists
essentially of) metal, ceramic, and/or polymer fibers which have
been woven, knitted or pressed into a layer of fabric. The choice
of layer construction (i.e. woven, knitted or pressed), the choice
of materials for the cloth, and the choice of the thickness for a
layer are made to meet the wear resistance, flexibility, and
sealing requirements of a particular seal or connector application.
In an embodiment, conjoined sealing device 130 may include
intermittent layers of any materials now known or later developed.
A person skilled in the art will readily recognize that conjoined
layer 136, first flange 132 and second flange 134 may be composed
of many materials.
[0030] Gas turbine 2 is only illustrative; teachings of the
invention may be applied to any machine that disposes two or more
seal components leaving a gap.
[0031] Turning to FIG. 7, a schematic view of portions of a
multi-shaft combined-cycle power plant 900 is shown. Combined-cycle
power plant 900 may include, for example, a gas turbine 980
operably connected to a generator 970. Generator 970 and gas
turbine 980 may be mechanically coupled by a shaft 915, which may
transfer energy between a gas turbine 980 and generator 970. Also
shown in FIG. 7 is a heat exchanger 986 operably connected to gas
turbine 980 and a steam turbine 992. Heat exchanger 986 may be
fluidly connected to both gas turbine 980 and steam turbine 992 via
conventional conduits (numbering omitted). Heat exchanger 986 may
be a conventional heat recovery steam generator (HRSG), such as
those used in conventional combined-cycle power systems. As is
known in the art of power generation, HRSG 986 may use hot exhaust
from gas turbine 980, combined with a water supply, to create steam
which is fed to steam turbine 992. Steam turbine 992 may optionally
be coupled to a second generator system 970 (via a second shaft
915). Any of generator system 970, gas turbine 980, HRSG 986, and
steam turbine 992 may be connected to conjoined seal device 130 of
FIG. 4 or other embodiments described herein. It is understood that
generators 970 and shafts 915 may be of any size or type known in
the art and may differ depending upon their application or the
system to which they are connected. Common numbering of the
generators and shafts is for clarity and does not necessarily
suggest these generators or shafts are identical. Generator system
970 and second shaft 915 may operate substantially similarly to
generator system 970 and shaft 915 described above. In one
embodiment of the present invention (shown in phantom), purge flow
control system 107 may be used, via computing device 110 to operate
either or both of steam turbine 992 and gas turbine 980. In another
embodiment, shown in FIG. 8, a single-shaft combined-cycle power
plant 990 may include a single generator 970 coupled to both gas
turbine 980 and steam turbine 992 via a single shaft 915. Gas
turbine 980 and steam turbine 992 may be operably connected to
conjoined seal device 130 of FIG. 4 or other embodiments described
herein.
[0032] The conjoined laminate seal device of the present disclosure
is not limited to any one power generation system, combined cycle
power generation system, turbine or other system, and may be used
with other power systems. Additionally, the device of the present
invention may be used with other systems not described herein that
may benefit from the sealing and leakage reduction provided by the
conjoined laminate seal device described herein. While various
embodiments are described herein, it will be appreciated from the
specification that various combinations of elements, variations or
improvements therein may be made by those skilled in the art, and
are within the scope of the invention. In addition, many
modifications may be made to adapt a particular situation or
material to the teachings of the invention without departing from
essential scope thereof. Therefore, it is intended that the
invention not be limited to the particular embodiment disclosed as
the best mode contemplated for carrying out this invention, but
that the invention will include all embodiments falling within the
scope of the appended claims.
[0033] The terminology used herein is for the purpose of describing
particular embodiments only and is not intended to be limiting of
the disclosure. As used herein, the singular forms "a", "an" and
"the" are intended to include the plural forms as well, unless the
context clearly indicates otherwise. It will be further understood
that the terms "comprises" and/or "comprising," when used in this
specification, specify the presence of stated features, integers,
steps, operations, elements, and/or components, but do not preclude
the presence or addition of one or more other features, integers,
steps, operations, elements, components, and/or groups thereof.
[0034] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they have structural elements that do not differ
from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal languages of the claims.
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