U.S. patent application number 13/962244 was filed with the patent office on 2015-02-12 for systems and methods for reducing or limiting one or more flows between a hot gas path and a wheel space of a turbine.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is General Electric Company. Invention is credited to Guoqiang Lu, Jong Youn Pak, Xiaoqing Zheng.
Application Number | 20150040567 13/962244 |
Document ID | / |
Family ID | 52388987 |
Filed Date | 2015-02-12 |
United States Patent
Application |
20150040567 |
Kind Code |
A1 |
Lu; Guoqiang ; et
al. |
February 12, 2015 |
Systems and Methods for Reducing or Limiting One or More Flows
Between a Hot Gas Path and a Wheel Space of a Turbine
Abstract
A turbine assembly is disclosed herein. The turbine assembly may
include a rotor with at least one bucket extending radially
therefrom. The turbine assembly also may include a stator assembly
positioned adjacent to the at least one bucket. Moreover, the
turbine assembly may include a seal assembly. The seal assembly may
include a first flange extending in a substantially axial direction
from the at least one bucket. The seal assembly also may include a
second flange extending from the stator assembly in the
substantially axial direction opposite the first flange. The second
flange may include at least one protuberance projecting towards the
first flange.
Inventors: |
Lu; Guoqiang; (Watervliet,
NY) ; Zheng; Xiaoqing; (Schenectady, NY) ;
Pak; Jong Youn; (Oakland Township, MI) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
52388987 |
Appl. No.: |
13/962244 |
Filed: |
August 8, 2013 |
Current U.S.
Class: |
60/722 ; 277/301;
415/174.5 |
Current CPC
Class: |
F01D 11/001 20130101;
F01D 11/02 20130101 |
Class at
Publication: |
60/722 ;
415/174.5; 277/301 |
International
Class: |
F01D 11/02 20060101
F01D011/02 |
Claims
1. A turbine assembly, comprising: a rotor; at least one bucket
extending radially from the rotor; a stator assembly positioned
adjacent to the at least one bucket; and a seal assembly,
comprising: a first flange extending from the at least one bucket
in a substantially axial direction; and a second flange extending
from the stator assembly in a substantially axial direction
opposite the first flange, wherein the second flange comprises at
least one protuberance projecting towards the first flange.
2. The turbine assembly of claim 1, wherein the at least one
protuberance is disposed about a distal end of the second
flange.
3. The turbine assembly of claim 1, wherein the at least one
protuberance is disposed between a distal end of the second flange
and the stator assembly.
4. The turbine assembly of claim 1, further comprising a second at
least one protuberance projecting from the distal end of the second
flange in the substantially axial direction opposite the first
flange.
5. The turbine assembly of claim 1, wherein the second flange
comprises a discourager seal.
6. The turbine assembly of claim 1, wherein the first flange
comprises an angle wing seal.
7. The turbine assembly of claim 1, wherein the first flange and
the second flange define a gap therebetween.
8. The turbine assembly of claim 1, wherein the at least one
protuberance comprises one or more teeth, wings, nubs, or fins.
9. A turbine system, comprising: a compressor; a combustion system
in communication with the compressor; a turbine in communication
with the combustion system, wherein the turbine comprises: a rotor;
at least one bucket extending radially from the rotor; a stator
assembly positioned adjacent to the at least one bucket; and a seal
assembly, comprising: a first flange extending from the at least
one bucket in a substantially axial direction; and a second flange
extending from the stator assembly in a substantially axial
direction opposite the first flange, wherein the second flange
comprises at least one protuberance projecting towards the first
flange.
10. The system of claim 9, wherein the at least one protuberance is
disposed about a distal end of the second flange.
11. The system of claim 9, wherein the at least one protuberance is
disposed between a distal end of the second flange and the stator
assembly.
12. The system of claim 9, further comprising a second at least one
protuberance projecting from the distal end of the second flange in
the substantially axial direction opposite the first flange.
13. The system of claim 9, wherein the second flange comprises a
discourager seal.
14. The system of claim 9, wherein the first flange comprises an
angle wing seal.
15. The system of claim 9, wherein the first flange and the second
flange define a gap therebetween.
16. The system of claim 9, wherein the at least one protuberance
comprises one or more teeth, wings, nubs, or fins.
17. A method to reduce or limit a flow to a wheel space and a hot
gas path of a turbine, the method comprising: positioning a first
flange about at least one bucket extending radially from a rotor;
positioning a second flange about a stator assembly positioned
adjacent to the at least one bucket, wherein the first flange and
the second flange are radially spaced apart to at least partially
form a seal assembly; and reducing the flow to the wheel space and
the hot gas path of the turbine with at least one protuberance
projecting from the second flange towards the first flange.
18. The method of claim 17, further comprising disposing the at
least one protuberance about a distal end of the second flange.
19. The method of claim 17, further comprising disposing the at
least one protuberance between a distal end of the second flange
and the stator assembly.
20. The method of claim 17, further comprising reducing the flow to
the wheel space and the hot gas path of the turbine with a second
at least one protuberance projecting from the distal end of the
second flange in the substantially axial direction opposite the
first flange.
Description
FIELD
[0001] Embodiments of the disclosure relate generally to gas
turbine engines and more particularly relate to systems and methods
for reducing or limiting one or more flows between a hot gas path
and a wheel space of a turbine.
BACKGROUND
[0002] A gas turbine engine typically includes a compressor, a
combustor, and a turbine. The efficiency of the turbine depends in
part on the amount of cooling air flow from the compressor that is
used to cool components in the hot gas path in the turbine section.
The cooling air flow may be introduced into the wheel space of the
turbine to limit high-temperature gases from entering into the
wheel space. Excess ingestion flow of the hot gasses into the wheel
space may increase the wheel space temperature beyond material
capabilities, resulting in materials potentially exceeding
temperature limits, which may contribute to rotor creep and/or
rupture. On the other hand, excess cooling air and/or purge flow to
the wheel space to prevent hot gas ingestion may decrease turbine
efficiency since the cooling air flow may not be available to the
entire turbine for work production.
BRIEF DESCRIPTION
[0003] Some or all of the above needs and/or problems may be
addressed by certain embodiments of the disclosure. According to
one embodiment, there is disclosed a turbine assembly. The turbine
assembly may include a rotor with at least one bucket extending
radially therefrom. The turbine assembly also may include a stator
assembly having at least one stationary nozzle vane positioned
adjacent to the at least one bucket. Moreover, the turbine assembly
may include a seal assembly. The seal assembly may include a first
flange extending from the at least one bucket in a substantially
axial direction. The seal assembly also may include a second flange
extending from the stator assembly in a substantially axial
direction opposite the first flange. The second flange may include
at least one protuberance projecting towards the first flange.
[0004] According to another embodiment, there is disclosed a
turbine system. The system may include a compressor. The system
also may include a combustion system in communication with the
compressor. Moreover, the system may include a turbine in
communication with the combustion system. The turbine may include a
rotor having at least one bucket extending radially therefrom. The
turbine also may include a stator assembly having at least one
stationary nozzle vane positioned adjacent to the at least one
bucket. Further, the turbine may include a seal assembly. The seal
assembly may include a first flange extending from the at least one
bucket in a substantially axial direction. The seal assembly also
may include a second flange extending from the stator assembly in a
substantially axial direction opposite the first flange. The second
flange may include at least one protuberance projecting towards the
first flange.
[0005] Further, according to another embodiment, there is disclosed
a method to reduce or limit a flow to a wheel space and a hot gas
path of a turbine. The method may include positioning a first
flange about at least one bucket extending radially from a rotor.
Moreover, the method may include positioning a second flange about
a stator assembly positioned adjacent to the at least one bucket.
The first flange and the second flange may be radially spaced apart
to at least partially form a seal assembly. Further, the method may
include reducing the flow to the wheel space and the hot gas path
of the turbine with at least one protuberance projecting from the
second flange towards the first flange.
[0006] Other embodiments, aspects, and features of the invention
will become apparent to those skilled in the art from the following
detailed description, the accompanying drawings, and the appended
claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] Reference will now be made to the accompanying drawings,
which are not necessarily drawn to scale.
[0008] FIG. 1 schematically depicts an example view of a gas
turbine engine assembly, according to an embodiment of the
disclosure.
[0009] FIG. 2 schematically depicts an example view of a portion of
a turbine assembly, according to an embodiment of the
disclosure.
[0010] FIG. 3 schematically depicts an example view of a seal
assembly within a turbine assembly, according to an embodiment of
the disclosure.
[0011] FIG. 4 schematically depicts an example view of a seal
assembly within a turbine assembly, according to an embodiment of
the disclosure.
[0012] FIG. 5 schematically depicts an example view of a seal
assembly within a turbine assembly, according to an embodiment of
the disclosure.
DETAILED DESCRIPTION
[0013] Illustrative embodiments will now be described more fully
hereinafter with reference to the accompanying drawings, in which
some, but not all embodiments are shown. The disclosure may be
embodied in many different forms and should not be construed as
limited to the embodiments set forth herein. Like numbers refer to
like elements throughout.
[0014] FIG. 1 shows a schematic view of gas turbine engine 10 as
may be used herein. The gas turbine engine 10 may include a
compressor 15. The compressor 15 compresses an incoming flow of air
20. The compressor delivers the compressed flow of air 20 to a
combustor 25. The combustor 25 mixes the compressed flow of air 20
with a compressed flow of fuel 30 and ignites the mixture to create
a flow of combustion gases 35. Although only a single combustor 25
is shown, the gas turbine engine 10 may include any number of
combustors 25. The flow of combustion gases 35 is in turn delivered
to a downstream turbine 40. The flow of combustion gases 35 drives
the turbine 40 to produce mechanical work. The mechanical work
produced in the turbine 40 drives the compressor 15 via a shaft 45
and an external load 50, such as an electrical generator or the
like.
[0015] The gas turbine engine 10 may use natural gas, various types
of syngas, and/or other types of fuels. The gas turbine engine 10
may be anyone of a number of different gas turbine engines such as
those offered by General Electric Company of Schenectady, N.Y. and
the like. The gas turbine engine 10 may have different
configurations and may use other types of components. Other types
of gas turbine engines also may be used herein. Multiple gas
turbine engines, other types of turbines, and other types of power
generation equipment also may be used herein together.
[0016] FIG. 2 schematically depicts one example embodiment of a
portion of the turbine 40. The turbine 40 may include a rotor 52
positioned about a longitudinal axis. A number of buckets 54 may be
mounted to the rotor 52. For example, the buckets 54 may be
circumferentially spaced apart from one another and extend radially
outward from the rotor 52. The buckets 54 may form one or more
stages in the turbine 40. The buckets 54 may include a shank
portion 56 and an airfoil portion 58.
[0017] A stationary outer casing 60 may be disposed about the
buckets 54 to define a hot gas passage through the turbine 40 for
the flow of combustion gases 35. In addition, a number of stator
assemblies 62 may be positioned adjacent to the buckets 54. For
example, the stator assemblies 62 may be positioned upstream and/or
downstream of each bucket 54. Each of the stator assemblies 62 may
include a stationary nozzle vane 64. A wheel space 66 may be formed
between each stator assembly 62 and bucket 54.
[0018] A seal assembly 68 may be positioned between each stator
assembly 62 and bucket 54. The seal assembly 68 may prevent,
reduced, and/or limit the flow of combustion gases 35 from entering
the wheel space 66. Further, the seal assembly 68 may reduce the
amount of purge air and/or cooling air needed to limit hot gases
from entering the wheel space 66.
[0019] The seal assembly 68 may include a first flange 70 extending
from the bucket 54 in a substantially axial direction. In some
instances, the first flange 70 may be an angel wing seal. The first
flange 70 may extend axially from the upstream and/or downstream
surfaces of the shank portion 56 of the bucket 54. In some
instances, the first flange 70 may terminate at a radially
outwardly extending tip 72, which may include teeth or fins. In
other instances, the radially outwardly extending tip 72 may be
omitted.
[0020] The seal assembly also may include a second flange 74
extending from the stator assembly 62 in a substantially axial
direction opposite the first flange 70. In some instances, the
second flange 74 may be a discourager seal. Any number of
discourager seals may be used herein. The second flange 74 may
extend axially from the upstream and/or downstream surfaces of the
stator assembly 62. In some instances, the second flange 74 may be
positioned radially outward of the first flange 70. For example,
the second flange 74 may be radially spaced apart from the first
flange 70 so as to form a gap therebetween. Other components and
other configurations may be used herein.
[0021] FIG. 3 depicts an example embodiment of a seal assembly 100
as may be used herein. The seal assembly 100 may include a first
flange 102 extending from the shank portion 56 of the bucket 54. In
some instances, the first flange 102 may be an angel wing seal. For
example, the first flange 102 may terminate at a radially outwardly
extending tip 104. In other instances, the radially outwardly
extending tip 104 may be omitted. The seal assembly 100 also may
include a second flange 106 extending from the stator assembly 62.
In some instances, the second flange 106 may be a discourager seal.
The second flange 106 may include at least one protuberance 108
projecting towards the first flange 102. In some instances, the at
least one protuberance 108 may be disposed about a distal end 110
of the second flange 106. The at least one protuberance 108 may
include a number of protuberances projecting towards the first
flange 102. The at least one protuberance 108 may be a tooth, wing,
nub, fin, or combination thereof. Other components and other
configurations may be used herein. The at least one protuberance
108 and the first flange 102 may cooperate to define a more
tortuous path for cooling flow to go through and limit hot gas
ingest into the wheel space. In some instances, the second flange
106 may be inserted into the stator assembly 62. In other
instances, the second flange 106 can be caulked in, welded on, or
form an integral part of the stator assembly 62.
[0022] FIG. 4 depicts an example embodiment of a seal assembly 112
as may be used herein. The seal assembly 112 may include a first
flange 114 extending from the shank portion 56 of the bucket 54. In
some instances, the first flange 114 may be an angel wing seal. For
example, the first flange 114 may terminate at a radially outwardly
extending tip 116. In other instances, the radially outwardly
extending tip 116 may be omitted. The seal assembly 112 also may
include a second flange 118 extending from the stator assembly 62.
In some instances, the second flange 118 may be a discourager seal.
The second flange 118 may include at least one protuberance 120
projecting towards the first flange 114. The at least one
protuberance 120 may include a number of protuberances projecting
towards the first flange 114. In some instances, the at least one
protuberance 120 may be disposed between a distal end 122 of the
second flange 118 and the stator assembly 62. The at least one
protuberance 120 may be a tooth, wing, nub, fin, or combination
thereof. Other components and other configurations may be used
herein. The at least one protuberance 120 and the first flange 114
may cooperate to define a more tortuous path for cooling flow to go
through and limit hot gas ingest into the wheel space. In some
instances, the second flange 118 may be inserted into the stator
assembly 62. In other instances, the second flange 118 can be
caulked in, welded on, or form an integral part of the stator
assembly 62.
[0023] FIG. 5 depicts an example embodiment of a seal assembly 124
as may be used herein. The seal assembly 124 may include a first
flange 126 extending from the shank portion 56 of the bucket 54. In
some instances, the first flange 126 may be an angel wing seal. For
example, the first flange 126 may terminate at a radially outwardly
extending tip 128. In other instances, the radially outwardly
extending tip 128 may be omitted. The seal assembly 124 also may
include a second flange 130 extending from the stator assembly 62.
In some instances, the second flange 130 may be a discourager seal.
The second flange 130 may include at least one protuberance 132
projecting from a distal end 134 of the second flange 130. In some
instances, the at least one protuberance 132 may include two
protuberances extending in opposite directions. For example, in an
embodiment, the second flange 130 and the at least one protuberance
132 may collectively form a T-shaped member. In other instances,
the at least one protuberance 132 may extend in an axial direction
opposite the first flange 126. The at least one protuberance 132
may include a number of protuberances. The at least one
protuberance 132 may be a tooth, wing, nub, fin, or combination
thereof Other components and other configurations may be used
herein. The at least one protuberance 132 and the first flange 126
may cooperate to define a more tortuous path for cooling flow to go
through and limit hot gas ingest into the wheel space. In some
instances, the second flange 130 may be inserted into the stator
assembly 62. In other instances, the second flange 130 can be
caulked in, welded on, or form an integral part of the stator
assembly 62
[0024] The protuberances extending from the second flange may
prevent, reduced, and/or limit the flow of combustion gases 35 from
entering the wheel space 66. Further, the protuberances extending
from the second flange may prevent, reduced, and/or limit purge air
and/or cooling air from entering the hot gas passage. The second
flange may include multiple protuberances projecting in various
directions. For example, the second flange may include one or more
protuberances disposed about the distal end of the second flange,
one or more protuberances disposed between the distal end of the
second flange and the stator assembly, one or more protuberances
projecting from the distal end of the second flange in the axial
direction opposite the first flange, and/or a combination
thereof.
[0025] Although embodiments have been described in language
specific to structural features and/or methodological acts, it is
to be understood that the disclosure is not necessarily limited to
the specific features or acts described. Rather, the specific
features and acts are disclosed as illustrative forms of
implementing the embodiments. For example, the various embodiments
described in FIGS. 1-5 may be combined. That is, the second flange
may include multiple protuberances projecting in various
directions.
* * * * *