U.S. patent application number 12/902561 was filed with the patent office on 2012-04-12 for axial retention device for turbine system.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to Thomas Raymond Farrell, Gary Charles Liotta.
Application Number | 20120087799 12/902561 |
Document ID | / |
Family ID | 45872519 |
Filed Date | 2012-04-12 |
United States Patent
Application |
20120087799 |
Kind Code |
A1 |
Farrell; Thomas Raymond ; et
al. |
April 12, 2012 |
AXIAL RETENTION DEVICE FOR TURBINE SYSTEM
Abstract
An axial retention device for a turbine is disclosed. The axial
retention device includes a latch associated with a mating surface
of one of a turbine component and a support structure. The latch
has an outward bias and includes an axial load surface. The axial
retention device further includes a pocket defined in a mating
surface of the other of the turbine component and the support
structure. The pocket is configured to accept the latch therein and
includes a mating axial load surface. Engagement of the latch and
the pocket allows the axial load surface and the mating axial load
surface to interact, preventing axial movement of the turbine
component with respect to the support structure in at least one
direction.
Inventors: |
Farrell; Thomas Raymond;
(Simpsonville, SC) ; Liotta; Gary Charles;
(Simpsonville, SC) |
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
45872519 |
Appl. No.: |
12/902561 |
Filed: |
October 12, 2010 |
Current U.S.
Class: |
416/220R |
Current CPC
Class: |
F01D 11/02 20130101;
F01D 5/326 20130101; F01D 5/3007 20130101 |
Class at
Publication: |
416/220.R |
International
Class: |
F04D 29/34 20060101
F04D029/34 |
Claims
1. An axial retention device for a turbine, the axial retention
device comprising: a latch associated with a mating surface of one
of a turbine component and a support structure, the latch having an
outward bias, the latch including an axial load surface; and a
pocket defined in a mating surface of the other of the turbine
component and the support structure, the pocket configured to
accept the latch therein, the pocket including a mating axial load
surface, wherein engagement of the latch and the pocket allows the
axial load surface and the mating axial load surface to interact,
preventing axial movement of the turbine component with respect to
the support structure in at least one direction.
2. The axial retention device of claim 1, the mating surface of the
one of the turbine component and the support structure associated
with the latch defining a cavity therein, and wherein the latch is
mounted in the cavity.
3. The axial retention device of claim 1, wherein the latch is
pivotable about a pivot point.
4. The axial retention device of claim 1, further comprising a
spring, the spring providing the outward bias.
5. The axial retention device of claim 4, wherein the spring is a
plurality of springs.
6. The axial retention device of claim 1, further comprising a stop
associated with one of the turbine component and the support
structure, the stop configured to interact with the other of the
turbine component and the support structure such that axial
movement of the turbine component with respect to the support
structure is prevented in two directions.
7. The axial retention device of claim 1, wherein the axial load
surface is a plurality of axial load surfaces and the mating axial
load surface is a plurality of mating axial load surfaces, and
wherein engagement of the latch and the pocket allows the plurality
of axial load surfaces and the plurality of mating axial load
surfaces to interact, preventing axial movement of the turbine
component with respect to the support structure in two
directions.
8. The axial retention device of claim 1, the other of the turbine
component and the support structure defining an access hole, the
access hole providing access to the latch for releasing the latch
from the pocket, allowing axial movement of the turbine component
with respect to the support structure in the at least one
direction.
9. The axial retention device of claim 8, the latch including a
sealing surface configured to seal the access hole when the latch
and pocket are engaged.
10. The axial retention device of claim 1, wherein the latch is
associated with the mating surface of the support structure and the
pocket is defined in the mating surface of the turbine
component.
11. The axial retention device of claim 1, wherein the turbine
component is a sealing device and the support structure is a spacer
rim structure.
12. The axial retention device of claim 1, wherein the turbine
component is a bucket and the support structure is a rotor
disk.
13. A turbine, comprising: a support structure, the support
structure having a mating surface; at least one turbine component,
the turbine component having a mating surface; a latch associated
with the mating surface of one of the at least one turbine
component and the support structure, the latch having an outward
bias, the latch including an axial load surface; and a pocket
defined in the mating surface of the other of the at least one
turbine component and the support structure, the pocket configured
to accept the latch therein, the pocket including a mating axial
load surface, wherein engagement of the latch and the pocket allows
the axial load surface and the mating axial load surface to
interact, preventing axial movement of the at least one turbine
component with respect to the support structure in at least one
direction.
14. The turbine of claim 13, the mating surface of the one of the
at least one turbine component and the support structure associated
with the latch defining a cavity therein, and wherein the latch is
mounted in the cavity.
15. The turbine of claim 13, wherein the latch is pivotable about a
pivot point.
16. The turbine of claim 13, further comprising a spring, the
spring providing the outward bias.
17. The turbine of claim 13, further comprising a stop associated
with one of the at least one turbine component and the support
structure, the stop configured to interact with the other of the at
least one turbine component and the support structure such that
axial movement of the at least one turbine component with respect
to the support structure is prevented in two directions.
18. The turbine of claim 13, the other of the at least one turbine
component and the support structure defining an access hole, the
access hole providing access to the latch for releasing the latch
from the pocket, allowing axial movement of the at least one
turbine component with respect to the support structure in the at
least one direction.
19. The turbine of claim 13, wherein the latch is associated with
the mating surface of the support structure and the pocket is
defined in the mating surface of the at least one turbine
component.
20. The turbine of claim 13, wherein the at least one turbine
component is two turbine components.
Description
FIELD OF THE INVENTION
[0001] The subject matter disclosed herein relates generally to
turbine systems, and more particularly to axial retention devices
for retaining turbine components within turbine systems.
BACKGROUND OF THE INVENTION
[0002] Turbine systems are widely utilized in fields such as power
generation. For example, a conventional gas turbine system includes
a compressor, a combustor, and a turbine. During operation of the
gas turbine system, various components in the system are subjected
to high temperature flows, which can cause the components to fail.
Since higher temperature flows generally result in increased
performance, efficiency, and power output of the gas turbine
system, the components that are subjected to high temperature flows
must be cooled to allow the gas turbine system to operate at
increased temperatures. Thus, cooling medium may be flowed through
the gas turbine system to cool the various components.
[0003] Further, to obtain optimal performance and efficiency of a
turbine system, the high temperature flows and cooling medium flows
should be generally confined from one another. For example, in the
turbine of a turbine system, turbine components are generally
provided with cooling medium independent of the high temperature
flow to prevent ingestion of the high temperature flow therein
during operation. Additionally, sealing devices may be utilized to
shield the turbine components from leakage of the high temperature
flow, and further to prevent the escape of the cooling medium.
[0004] In many cases, the sealing devices and turbine components
are mounted in the turbine to annular support structures. The
sealing devices and turbine components may further be positioned
circumferentially and axially with respect to each other to prevent
leakage of the high temperature flow and escape of the cooling
medium. However, in many cases, the sealing devices and/or turbine
components may shift, slide, or become disengaged with respect to
the support structures, thus potentially allowing leakage therein
or escape therefrom. This leakage and/or escape can reduce the
performance and efficiency of the turbine system, and may further
be harmful to the system. Thus, in most cases, the sealing devices
and turbine components should not shift, slide, or become
disengaged with respect to the support structures.
[0005] Thus, an improved retention device for retaining sealing
devices and/or turbine components within support structures would
be desired in the art. For example, an axial retention device that
prevents axial movement of the sealing devices and/or turbine
components with respect to the support structures would be
advantageous.
BRIEF DESCRIPTION OF THE INVENTION
[0006] Aspects and advantages of the invention will be set forth in
part in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
[0007] In one embodiment, an axial retention device for a turbine
is disclosed. The axial retention device includes a latch
associated with a mating surface of one of a turbine component and
a support structure. The latch has an outward bias and includes an
axial load surface. The axial retention device further includes a
pocket defined in a mating surface of the other of the turbine
component and the support structure. The pocket is configured to
accept the latch therein and includes a mating axial load surface.
Engagement of the latch and the pocket allows the axial load
surface and the mating axial load surface to interact, preventing
axial movement of the turbine component with respect to the support
structure in at least one direction.
[0008] These and other features, aspects and advantages of the
present invention will become better understood with reference to
the following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and,
together with the description, serve to explain the principles of
the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] A full and enabling disclosure of the present invention,
including the best mode thereof, directed to one of ordinary skill
in the art, is set forth in the specification, which makes
reference to the appended figures, in which:
[0010] FIG. 1 is a schematic illustration of a turbine system;
[0011] FIG. 2 is a sectional side view of the turbine of a turbine
system according to one embodiment of the present disclosure;
[0012] FIG. 3 is a sectional side view of a portion of the turbine
of a turbine system according to one embodiment of the present
disclosure;
[0013] FIG. 4 is an exploded perspective view of a support
structure and two turbine components according to one embodiment of
the present disclosure;
[0014] FIG. 5 is a cross-sectional view of an axial retention
device according to one embodiment of the present disclosure;
and
[0015] FIG. 6 is a cross-sectional view of an axial retention
device according to another embodiment of the present
disclosure.
DETAILED DESCRIPTION OF THE INVENTION
[0016] Reference now will be made in detail to embodiments of the
invention, one or more examples of which are illustrated in the
drawings. Each example is provided by way of explanation of the
invention, not limitation of the invention. In fact, it will be
apparent to those skilled in the art that various modifications and
variations can be made in the present invention without departing
from the scope or spirit of the invention. For instance, features
illustrated or described as part of one embodiment can be used with
another embodiment to yield a still further embodiment. Thus, it is
intended that the present invention covers such modifications and
variations as come within the scope of the appended claims and
their equivalents.
[0017] FIG. 1 is a schematic diagram of a turbine system 10. While
the turbine system 10 described herein may generally be a gas
turbine system, it should be understood that the turbine system 10
of the present disclosure is not limited to gas turbine systems,
and that any suitable turbine system, including but not limited to
a steam turbine system, is within the scope and spirit of the
present disclosure.
[0018] Thus, the system as shown may include a compressor 12, a
combustor 14, and a turbine 16. The compressor 12 and turbine 16
may be coupled by a shaft 18. The shaft 18 may be a single shaft or
a plurality of shaft segments coupled together to form shaft
18.
[0019] The turbine 16 may include a plurality of turbine stages.
For example, in one embodiment, the turbine 16 may have three
stages, as shown in FIG. 2. For example, a first stage of the
turbine 16 may include a plurality of circumferentially spaced
nozzles 21 and buckets 22. The nozzles 21 may be disposed and fixed
circumferentially about the shaft 18. The buckets 22 may be
disposed circumferentially about the shaft 18 and coupled to the
shaft 18. A second stage of the turbine 16 may include a plurality
of circumferentially spaced nozzles 23 and buckets 24. The nozzles
23 may be disposed and fixed circumferentially about the shaft 18.
The buckets 24 may be disposed circumferentially about the shaft 18
and coupled to the shaft 18. A third stage of the turbine 16 may
include a plurality of circumferentially spaced nozzles 25 and
buckets 26. The nozzles 25 may be disposed and fixed
circumferentially about the shaft 18. The buckets 26 may be
disposed circumferentially about the shaft 18 and coupled to the
shaft 18. The various stages of the turbine 16 may be disposed in
the turbine 16 in the path of hot gas flow 28. It should be
understood that the turbine 16 is not limited to three stages, but
may have any suitable number of stages.
[0020] As shown in FIGS. 3 and 4, a plurality of annularly disposed
sealing devices 30 may be provided between each plurality of
buckets, such as, for example, buckets 22 or 24, and the adjacent
plurality of buckets, such as, for example, buckets 24 or 26. The
sealing devices 30 may be provided to form an outer boundary for
the path of gas flow 28, thus preventing the gas flow 28 from
migrating through the outer boundary and further preventing cooling
flows (not shown) exterior to the path of gas flow 28 from
migrating through the outer boundary into the path. The sealing
devices 30 may further interact with the plurality of nozzles, such
as nozzles 21, 23, or 25, as shown in FIG. 3. It should be
understood that the sealing devices 30 need not be designed as
shown in FIGS. 3 and 4, but rather that any suitable sealing device
is within the scope and spirit of the present disclosure.
[0021] The buckets 22, 24, 26 and sealing devices 30 must be
retained in the turbine 16. Thus, various support structures 32 may
be provided in the turbine 16 for mating with and supporting
various turbine components 34, such as the sealing devices 30
and/or buckets 22, 24, 26. The support structures 32 may be, for
example, rotor disks 36 configured to mate with the buckets 22, 24,
26. Alternatively, the support structures 32 may be, for example,
spacer rim structures 38 configured to mate with the sealing
devices 32.
[0022] As shown, the turbine components 34 and support structures
32 may include mating appendages 40 and cavities 42 for mating the
turbine components 34 and support structures 32 together. For
example, in some embodiments, the appendages 40 may be dovetails,
and the cavities 42 may be shaped and sized to receive the
dovetails therein. In general, the turbine components 34 are mated
to the support structures 32 by sliding the appendages 40 into the
cavities 42 along a generally axial axis 44, as shown in FIG. 4.
Mating of the appendages 40 in the cavities 42 prevents movement of
the turbine components 34 with respect to the support structures 32
in the generally radial and tangential directions, but may not
prevent movement of the turbine components 34 with respect to the
support structures 32 in a generally axial direction. For example,
when the appendages 40 are mated with the cavities 42, the
appendages are free to move along the axial axis 44 in a first
direction 46 or a second direction 48.
[0023] Thus as shown in FIGS. 4 through 6, an axial retention
device 50 is provided for axially retaining a turbine component 34
in a support structure 32. The axial retention device 50 includes a
latch 52 and a pocket 54. In general, the latch 52 may be
associated with one of the turbine component 34 and the support
structure 32, and the pocket 54 may be defined in the other of the
turbine component 34 and the support structure 32. For example, in
exemplary embodiments, the latch 52 may be associated with the
support structure 32 and the pocket 54 may be defined in the
turbine component 34. In alternative embodiments, the latch 52 may
be associated with the turbine component 34 and the pocket 54 may
be defined in the support structure 32.
[0024] Further, as discussed above, a plurality of turbine
components 34 may be disposed in an annular array about the support
structure 32. In some embodiments, each turbine component 34 may
include an independent latch 52 or define an independent pocket 54
configured to mate with an independent latch 52 or independent
pocket 54 included or defined in the support structure 32. In other
embodiments, however, as shown in FIG. 4, two adjacent turbine
components 34 may each include an independent latch 52 or define an
independent pocket 54, and both latches 52 or pockets 54 may be
configured to mate with one latch 52 or pocket 54 included or
defined in the support structure 32.
[0025] The turbine component 34 may define a mating surface 56, and
the support structure 32 may define a mating surface 58. The mating
surfaces 56, 58 may be defined on the appendage 40 and in the
cavity 42, or may be defined adjacent the appendage 40 and cavity
42, as shown in FIGS. 5 through 6. The mating surfaces 56, 58,
generally mate together when the turbine component 34 and support
structure 32 are mated together. The latch 52 may be associated
with the mating surface 56 or 58 of the turbine component 34 or
support structure 32, and the pocket 54 may be defined in the other
of the mating surface 56 or 58 of the turbine component 34 or
support structure 32.
[0026] The pocket 54 according to the present disclosure may be
configured to accept the latch 52 therein. For example, the pocket
54 may be sized and shaped to accommodate at least a portion of the
latch 52 therein, and may further have various features for
engaging and interacting with the latch 52, as discussed below.
[0027] The latch 52 according to the present disclosure may have a
generally outward bias. "Outward" refers to a direction generally
radially away from an associated base component or surface, such as
a turbine component 34 or support structure 32. For example, in
some exemplary embodiments, as shown in FIG. 5, the latch 52 may be
pivotal about a pivot point 60. Thus, the latch 52 may be outwardly
biased about the pivot point 60. In other exemplary embodiments, as
shown in FIG. 6, the latch 52 may simply have a generally radial
outward bias.
[0028] Further, in some exemplary embodiments, the axial retention
device 50 may include a spring 62, or a plurality of springs 62.
The springs 62 may provide the outward bias. In embodiments wherein
the latch 52 has a pivot point 60, the springs 62 may be located,
for example, at the pivot point 60 or spaced from the pivot point
60. It should be understood, however, that the outward bias need
not be provided by springs, and rather that the outward bias may be
provided by any suitable biasing, tensioning, or preloading
device.
[0029] In exemplary embodiments, as shown in FIGS. 5 through 6, the
mating surface 56 or 58 of the turbine component 34 or support
structure 32 that is associated with the latch 52 may define a
cavity 64 therein. The latch 52 may be mounted in the cavity 64.
Thus, in exemplary embodiments, when the latch 52 is biased
outward, a portion of the latch 52 may protrude from the mating
surface 56 or 58. Further, in exemplary embodiments, when the latch
52 is retracted, as discussed below, the uppermost portions of the
latch 52 may be at or below the mating surface 56 or 58. In
alternative embodiments, however, the uppermost portions of the
latch 52 may remain above the mating surface 56 or 58 when
retracted. The cavity 64 may further include side surfaces 66. The
side surfaces 66 may interact with contact points 68 on the latch
52 to prevent movement of the latch 52 along the axial axis 44.
[0030] As shown, the latch 52 may include an axial load surface 70,
and the pocket 54 may include a mating axial load surface 72. As
shown in FIGS. 5 and 6, for example, the axial load surfaces 70, 72
may be generally planer side surfaces of the latch 52 and pocket
54, which may be generally perpendicular to the axial axis 44. It
should be understood, however, that the axial load surfaces 70, 72
may have any suitable contours and/or orientations. In general,
engagement of the latch 52 and the pocket 54 may allow the axial
load surfaces 70, 72 to interact, preventing axial movement of the
turbine component 34 with respect to the support structure 32 in at
least one direction. For example, interaction of the axial load
surfaces 70, 72 may prevent axial movement of the turbine component
34 in the first direction 46, as shown in FIGS. 5 and 6, or in the
second direction 48.
[0031] In some embodiments, as shown in FIG. 5, the axial retention
device 50 may further include a stop 74 associated with one of the
turbine component 34 or the support structure 32. The stop 74 may
be configured to interact with the other of the turbine component
34 or the support structure 32, preventing axial movement of the
turbine component 34 with respect to the support structure in
another direction, such that axial movement is prevented in two
directions. For example, the stop 74 may have a generally planer
side surface, which may be generally perpendicular to the axial
axis 44. It should be understood, however, that the stop 74 may
have any suitable contour and/or orientation. In general,
engagement of the latch 52 and the pocket 54 may allow the stop to
interact with a side surface of the other of the turbine component
34 or the support structure 32, preventing axial movement of the
turbine component 34 with respect to the support structure 32 in at
least one direction. For example, interaction of the stop 74 with
the other of the turbine component 34 or the support structure 32
may prevent axial movement of the turbine component 34 in the
second direction 48, as shown in FIG. 5, or in the first direction
46.
[0032] In another embodiment, as shown in FIG. 6, the latch 52 may
include a plurality of axial load surfaces 70, and the pocket 54
may include a plurality of mating axial load surfaces 72. In
general, engagement of the latch 52 and the pocket 54 may allow the
axial load surfaces 70, 72 to interact, preventing axial movement
of the turbine component 34 with respect to the support structure
32 in two directions. For example, interaction of the axial load
surfaces 70, 72 may prevent axial movement of the turbine component
34 in both the first direction 46 and the second direction 48, as
shown in FIG. 6.
[0033] In some embodiments, as shown in FIGS. 4 through 6, the one
of the turbine component 34 and the support structure 32 not
including the latch 52 may define an access hole 76. The access
hole 76 may provide access to the latch 52 for releasing the latch
52 from the pocket 54, allowing axial movement of the turbine
component 34 with respect to the support structure 32 in the at
least one direction, such as in the first direction 46 or the
second direction 48. For example, the access hole 76 may provide
access for enabling retraction of the latch 52 from the pocket 54,
thus disengaging the axial load surfaces 70, 72. In one embodiment,
the access hole 76 may allow a tool, such as a rod, or, for
example, an appendage, to be placed through the access hole 76 to
interact with the latch 52, to cause retraction of the latch
52.
[0034] Further, in some embodiments as shown in FIGS. 5 and 6, the
latch 52 may include a sealing surface 78. The sealing surface 78
may be configured to seal the access hole 76 when the latch 52 and
pocket 54 are engaged. For example, the sealing surface 78 may be
generally parallel to the opening of the access hole 76 adjacent
the latch 52 and/or perpendicular to the central axis of the access
hole 76. It should be understood, however, that the sealing surface
78 may have any suitable contour and/or orientation sufficient to
seal the access hole 76 when the latch 52 and pocket 54 are
engaged. When the latch 52 and pocket 54 are engaged, the sealing
surface 78 may abut the opening of the access hole 76 that is
adjacent the latch 52, thus generally sealing the access hole 76.
The sealing surface 78 may beneficially prevent or reduce the
potential leakage of high temperature flow and/or escape of cooling
medium through the access hole 76 between the turbine component 34
and support structure 32.
[0035] Beneficially, the axial retention device 50 of the present
disclosure may prevent axial movement of turbine components 34 with
respect to support structures 32 in one or more directions. This
prevention of axial movement may advantageously prevent or reduce
the potential leakage of high temperature flow and/or escape of
cooling medium between the turbine component 34 and support
structure 32.
[0036] 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 include 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.
* * * * *