U.S. patent application number 12/986211 was filed with the patent office on 2012-07-12 for axial retention device for turbine system.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to Ravi Kishore Appapantula, Ramesh Ramachandran, Pradeep Kumar Yarava.
Application Number | 20120177498 12/986211 |
Document ID | / |
Family ID | 46330806 |
Filed Date | 2012-07-12 |
United States Patent
Application |
20120177498 |
Kind Code |
A1 |
Yarava; Pradeep Kumar ; et
al. |
July 12, 2012 |
AXIAL RETENTION DEVICE FOR TURBINE SYSTEM
Abstract
An axial retention device for a turbine system is disclosed. The
axial retention device includes a pocket defined in a mating
surface of one of a turbine component and a support structure. The
pocket includes a first axial load surface. The axial retention
device further includes a latch comprising a base member and a
pivotal member. The base member is associated with a mating surface
of the other of the turbine component and the support structure.
The pivotal member is configured to engage the pocket and includes
a first mating axial load surface. Engagement of the pivotal member
and the pocket allows the first axial load surface and the first
mating axial load surface to interact, preventing axial movement of
the turbine component with respect to the support structure in the
at least one direction.
Inventors: |
Yarava; Pradeep Kumar;
(Chennai, IN) ; Appapantula; Ravi Kishore; (Andhra
Pradesh, IN) ; Ramachandran; Ramesh; (Bangalore,
IN) |
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
46330806 |
Appl. No.: |
12/986211 |
Filed: |
January 7, 2011 |
Current U.S.
Class: |
416/220R |
Current CPC
Class: |
F01D 5/323 20130101 |
Class at
Publication: |
416/220.R |
International
Class: |
F01D 5/30 20060101
F01D005/30 |
Claims
1. An axial retention device for a turbine system, the axial
retention device comprising: a pocket defined in a mating surface
of one of a turbine component and a support structure, the pocket
including a first axial load surface; and a latch comprising a base
member and a pivotal member, the base member associated with a
mating surface of the other of the turbine component and the
support structure, the pivotal member configured to engage the
pocket and including a first mating axial load surface, wherein
engagement of the pivotal member and the pocket allows the first
axial load surface and the first 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, wherein in a first
position, the pivotal member is disengaged from the pocket and
allows axial movement of the turbine component with respect to the
support structure in the at least one direction, and in a second
position, the pivotal member is engaged with the pocket and
prevents axial movement of the turbine component with respect to
the support structure in the at least one direction.
3. The axial retention device of claim 2, wherein the pivotal
member is biased towards the second position.
4. The axial retention device of claim 2, the pivotal member
further comprising a disassembly feature, the disassembly feature
configured to pivot the pivotal member from the second position to
the first position.
5. The axial retention device of claim 4, wherein the disassembly
feature is a groove defined in the pivotal member.
6. The axial retention device of claim 4, further comprising a
lever configured to engage the disassembly feature and pivot the
pivotal member from the second position to the first position.
7. The axial retention device of claim 1, the pocket further
including a second axial load surface, the pivotal member further
including a second mating axial load surface, and wherein
interaction of the second axial load surface and the second mating
axial load surface prevents axial movement of the turbine component
with respect to the support structure in a second opposite
direction.
8. The axial retention device of claim 1, wherein the pocket is
defined in a mating surface of the support structure.
9. The axial retention device of claim 1, the mating surface of the
other of the turbine component and the support structure defining a
second pocket, and wherein the base member is configured to engage
the second pocket.
10. The axial retention device of claim 1, wherein the turbine
component is a blade and the support structure is a rotor disk.
11. A turbine system, comprising: a support structure, the support
structure having a mating surface; a turbine component, the turbine
component having a mating surface; a pocket defined in a mating
surface of one of the turbine component and the support structure,
the pocket including a first axial load surface; and a latch
comprising a base member and a pivotal member, the base member
associated with a mating surface of the other of the turbine
component and the support structure, the pivotal member configured
to engage the pocket and including a first mating axial load
surface, wherein engagement of the pivotal member and the pocket
allows the first axial load surface and the first mating axial load
surface to interact, preventing axial movement of the turbine
component with respect to the support structure in at least one
direction.
12. The turbine system of claim 11, wherein in a first position,
the pivotal member is disengaged from the pocket and allows axial
movement of the turbine component with respect to the support
structure in the at least one direction, and in a second position,
the pivotal member is engaged with the pocket and prevents axial
movement of the turbine component with respect to the support
structure in the at least one direction.
13. The turbine system of claim 12, wherein the pivotal member is
biased towards the second position.
14. The turbine system of claim 12, the pivotal member further
comprising a disassembly feature, the disassembly feature
configured to pivot the pivotal member from the second position to
the first position.
15. The turbine system of claim 14, wherein the disassembly feature
is a groove defined in the pivotal member.
16. The turbine system of claim 14, further comprising a lever
configured to engage the disassembly feature and pivot the pivotal
member from the second position to the first position.
17. The turbine system of claim 11, the pocket further including a
second axial load surface, the pivotal member further including a
second mating axial load surface, and wherein interaction of the
second axial load surface and the second mating axial load surface
prevents axial movement of the turbine component with respect to
the support structure in a second opposite direction.
18. The turbine system of claim 11, wherein the pocket is defined
in a mating surface of the support structure.
19. The turbine system of claim 11, the mating surface of the other
of the turbine component and the support structure defining a
second pocket, and wherein the base member is configured to engage
the second pocket.
20. The turbine system of claim 11, wherein the turbine component
is a blade and the support structure is a rotor disk.
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 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. Further, a conventional
gas turbine includes a rotor with various rotor blades mounted to
disks in the compressor and turbine sections thereof. Each blade
includes an airfoil over which pressurized air or fluid flows, and
a platform at the base of the airfoil that defines the radial inner
boundary for the air or fluid flow. To attach the blades to the
rotor disks, the blades may include a suitable appendage, such as a
root or dovetail, configured to engage a complementary attachment
cavity in the perimeter of the disk.
[0003] In many cases, the blades disposed in the rotor disks may
shift, slide, or become disengaged with respect to the rotor disks
during operation of the system, thus potentially allowing air or
fluid flow leakage or other damage to the system. Thus, devices for
retaining the blades with respect to the rotor disks may be
desired.
[0004] One prior art method for axially retaining blades in rotor
disks involves staking. Staking creates an interference fit between
two components, such as between a blade and rotor disk. The blade
and rotor disk are connected, and then the apparatus connecting the
blade and rotor disk together is deformed to create the
interference fit. However, the use of staking for retaining blades
in rotor disks has many disadvantages. For example, blades must be
replaced after certain periods of use due to, for example, wear or
damage. Each time a blade is replaced, the blade must be staked to
the rotor disk at a different location. Utilizing staking to retain
the replacement blade in the rotor disk is a time consuming
process. Further, the available locations on the rotor disk for
staking are generally limited. After a certain number of
replacements, locations may be unavailable. The unavailability of
staking locations thus necessitates replacement of the rotor disk.
Replacement of the rotor disk is both time consuming and, due to
the cost of the rotor disk and the loss of production of the
turbine system during replacement, expensive.
[0005] Thus, an improved retention device for retaining blades and
other suitable components within rotor disks and other suitable
support structures would be desired in the art. For example, an
axial retention device that prevents axial movement of the blades
and other components with respect to the rotor disks and other
support structures would be advantageous. Further, a retention
device that provides for efficient and cost-effective replacement
of the blades and other components, and that reduces or eliminates
the need to replace the rotor disks and other support structures,
would be desired.
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
system is disclosed. The axial retention device includes a pocket
defined in a mating surface of one of a turbine component and a
support structure. The pocket includes a first axial load surface.
The axial retention device further includes a latch comprising a
base member and a pivotal member. The base member is associated
with a mating surface of the other of the turbine component and the
support structure. The pivotal member is configured to engage the
pocket and includes a first mating axial load surface. Engagement
of the pivotal member and the pocket allows the first axial load
surface and the first mating axial load surface to interact,
preventing axial movement of the turbine component with respect to
the support structure in the 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 compressor of a
turbine system according to one embodiment of the present
disclosure;
[0012] FIG. 3 is an exploded perspective view of a support
structure and turbine component according to one embodiment of the
present disclosure;
[0013] FIG. 4 is an exploded cross-sectional view of an axial
retention device according to one embodiment of the present
disclosure;
[0014] FIG. 5 is a cross-sectional view of an axial retention
device in a first position during assembly according to one
embodiment of the present disclosure;
[0015] FIG. 6 is a cross-sectional view of an axial retention
device in a second position according to one embodiment of the
present disclosure; and
[0016] FIG. 7 is a cross-sectional view of an axial retention
device in a first position during disassembly according to one
embodiment of the present disclosure.
DETAILED DESCRIPTION OF THE INVENTION
[0017] 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.
[0018] 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.
[0019] Thus, the system 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.
[0020] Various components of the compressor 12 of a turbine system
10 are shown in FIG. 2. For example, a rotor 20 of the compressor
12 may include a plurality of rotor disks 22. A plurality of blades
24 may be disposed in an annular array about each rotor disk 22,
and may be attached to the rotor disk 22 as discussed below. As
discussed below, each of the blades 24 may be attached to a rotor
disk 22 by sliding the blade 24 in a generally axial direction such
that an appendage of the blade 24 engages a cavity of the rotor
disk 22. For the blade 24 to be securely attached to the rotor disk
22, and to prevent axial movement of the blade 24 with respect to
the rotor disk 22, an axial retention device may be provided to
prevent such axial movement.
[0021] It should be understood, however, that the present
disclosure is not limited to axial retention devices for blades 24
in rotor disks 22 in the compressor 12 of a turbine system 10.
Rather, the axial retention device according to the present
disclosure may be utilized in conjunction with any suitable support
structure 32 to retain any suitable turbine component 34 in any
section of the turbine system 10. The support structure 32 and
turbine component 34 may, in exemplary embodiments, be a rotor disk
22 and blade 24, respectively, in the compressor 12. Alternatively,
however, the support structure 32 and turbine component 34 may be a
rotor disk and blade in the turbine 16, or a sealing device and
spacer rim structure in the compressor 12 or turbine 16, or any
other suitable support structure 32 and turbine component 34 in the
turbine system 10.
[0022] As shown in FIG. 3, 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. 3. 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 direction 46 or direction 48.
[0023] Thus as shown in FIGS. 3 through 7, 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
pocket 52 and a latch 54. The latch 54 according to the present
disclosure includes a base member 56 and a pivotal member 58. In
general, the pocket 52 may be defined in one of the turbine
component 34 and the support structure 32, and the base member 56
may be associated with the other of the turbine component 34 and
the support structure 32. For example, in exemplary embodiments as
illustrated in FIGS. 3 through 7, the pocket 52 may be associated
with the support structure 32 and the base member 56 may be defined
in the turbine component 34. In alternative embodiments, the pocket
52 may be associated with the turbine component 34 and the base
member 56 may be defined in the support structure 32.
[0024] The turbine component 34 may define a mating surface 62, and
the support structure 32 may define a mating surface 64. The mating
surfaces 62, 64 may be defined on the appendage 40 and in the
cavity 42, respectively, as shown in FIGS. 3 through 7. For
example, in exemplary embodiments, the mating surface 62 of the
turbine component 34 may be the bottom surface of the appendage 40,
and the mating surface 64 of the support structure 32 may be the
surface within the cavity 42 configured to mate with the bottom
surface of the appendage 40. In alternative embodiments, the mating
surface 62 may be any side or other surface of the appendage 40,
and the mating surface 64 may be the surface within the cavity 42
configured to mate with that surface of the appendage 40. In
further alternative embodiments, the mating surfaces 62, 64 may be
defined adjacent the appendage 40 and cavity 42. For example, the
mating surface 64 may be the rim of the support structure 32, and
the mating surface 62 of the turbine component 34 may be the
surface configured to mate with that surface of the support
structure 32. The mating surfaces 62, 64, generally mate together
when the turbine component 34 and support structure 32 are mated
together. The pocket 52 may be defined in the mating surface 62 or
64 of the turbine component 34 or support structure 32, and the
base member 56 may be associated with the other of the mating
surface 62 or 64 of the turbine component 34 or support structure
32. For example, in exemplary embodiments as shown in FIGS. 3
through 7, the pocket 52 may be defined in the mating surface 64 of
the support structure 32 and the base member 56 may be associated
with the mating surface 62 of the turbine component 34.
[0025] As discussed, the base member 56 may be associated with the
mating surface 62 or 64. In some embodiments, the base member 56
may be, for example, mounted to the mating surface 62 or 64. In
these embodiments, the base member 56 may be mounted utilizing, for
example, a suitable adhesive, mechanical fastener, or other
suitable mounting device or method. In other embodiments, the base
member 56, or a portion thereof, may be integral with the mating
surface 62 or 64. In other exemplary embodiments, as shown in FIGS.
3 though 7, the mating surface 62 or 64 that is associated with the
base member 56 may define a second pocket 72 therein. The base
member 56 may be configured to engage the second pocket 72. In
general, engagement of the base member 56 and the second pocket 72
prevents axial movement along the axial axis 44 of the base member
56 with respect to the second pocket 72 in at least one direction.
For example, as shown, the base member 56 may be disposed in the
second pocket 72. In some embodiments, the base member 56 may be
mounted in the second pocket 72 utilizing, for example, a suitable
adhesive, mechanical fastener, or other suitable mounting device or
method, and thus may engage the second pocket 72. In other
exemplary embodiments, the base member 56 may not be mounted or
otherwise attached to the second pocket 72, and may simply be
positioned in the second pocket 72. In these embodiments, the
second pocket 72 may include a first axial load surface 74 and,
optionally, a second axial load surface 76. Further, the base
member 56 may include a first mating axial load surface 82 and,
optionally, a second mating axial load surface 84. When the base
member 56 is positioned in the second pocket 72, the first axial
load surface 74 and the first mating axial load surface 82 may
interact, preventing axial movement of the base member 56 in one
direction, such as in direction 46. Further, in exemplary
embodiments, the second axial load surface 76 and the second mating
axial load surface 84 may interact, preventing axial movement of
the base member 56 in a second opposite direction, such as in
direction 48. Thus, the base member 56 in these embodiments may
engage the second pocket 72.
[0026] In exemplary embodiments, the base member 56 may be
removable from the second pocket 72. Alternatively, however, the
base member 56 may be permanently mounted in the second pocket
72.
[0027] As shown in FIGS. 3 though 7, the pivotal member 58 may be
configured to engage the pocket 52. In general, engagement of the
pivotal member 58 and the pocket 52 prevents axial movement along
the axial axis 44 of the pivotal member 58 with respect to the
pocket 52 in at least one direction. For example, to engage the
pocket 52 as shown in FIG. 6, the pivotal member 58 may be disposed
in the pocket 52. The pocket 52 may include a first axial load
surface 94 and, optionally, a second axial load surface 96.
Further, the pivotal member 58 may include a first mating axial
load surface 102 and, optionally, a second mating axial load
surface 104. When the pivotal member 58 is disposed in the pocket
52, the first axial load surface 94 and the first mating axial load
surface 102 may interact, preventing axial movement of the pivotal
member 58 in one direction, such as in direction 46, and thus
preventing axial movement of the turbine component 34 with respect
to the support structure 32 in that direction. Further, in
exemplary embodiments, the second axial load surface 96 and the
second mating axial load surface 104 may interact, preventing axial
movement of the pivotal member 58 in a second opposite direction,
such as in direction 48, and thus preventing axial movement of the
turbine component 34 with respect to the support structure 32 in
that direction. Thus, the pivotal member 58 in these embodiments
may engage the pocket 52.
[0028] As mentioned, the pivotal member 58 may be configured to
engage the pocket 52. For example, the pivotal member 58 may be
pivotal with respect to the base member 56. The pivotal member 58
may pivot about a pivot point 110. The pivot point 110 may be
located adjacent an end of the base member 56, as shown in FIGS. 3
through 7, or may be located adjacent the base member 56 at any
point along the base member 56. The pivot point 110 may generally
connect the pivotal member 58 to the base member 56.
[0029] In exemplary embodiments, the pivotal member 58 may pivot
between a first position, as shown in FIGS. 5 and 7, and a second
position, as shown in FIGS. 4 and 6. In the first position, the
pivotal member 58 may be disengaged from the pocket 52. When
disengaged, the first axial load surface 94 and the first mating
axial load surface 102 may not interact. Thus, the pivotal member
58 may be allowed to move axially with respect to the pocket 52 in
at least one direction, such as in direction 46. Further, the
turbine component 34 may be allowed to move axially with respect to
the support structure 32 in at least one direction, such as in
direction 46. In the second position, the pivotal member 58 may be
engaged with the pocket 52. When engaged, the first axial load
surface 94 and the first mating axial load surface 102 may
interact. Thus, the pivotal member 58 may be prevented from moving
axially with respect to the pocket 52 in at least one direction,
such as in direction 46. Further, the turbine component 34 may be
prevented from moving axially with respect to the support structure
32 in at least one direction, such as in direction 46.
[0030] In some embodiments, the pivotal member 58 may be biased
towards the second position. For example, the latch 54 may include
a spring member (not shown) or other suitable biasing device
therein. The spring member or other biasing device may exert a
force on the pivotal member 58, such as a tensile or compressive
force, to bias the pivotal member 58 towards the second position.
In alternative embodiments, however, the pivotal member 58 may be
biased towards the first position, may have no bias, or may have
any other suitable bias.
[0031] In some embodiments, the pivotal member 58 may include a
disassembly feature 120. The disassembly feature 120 may be
configured to pivot the pivotal member 58 from the second position
to the first position. For example, in some embodiments, the
disassembly feature 120 may be a tab, handle or other protrusion.
The disassembly feature 120 in these embodiments may be engaged by
a pivoting device, such as a lever, or by a person, to pivot the
pivotal member 58 from the second position to the first position.
In other embodiments, the disassembly feature 120 may be a groove
122 (see FIG. 3) defined in the pivotal member 58. The groove 122
may be engaged by a pivoting device to pivot the pivotal member 58
from the second position to the first position.
[0032] In some embodiments, as shown in FIG. 7, the axial retention
device 50 may further include a pivoting device, such as a lever
124. The lever 124 may be configured to engage the disassembly
feature 120, such as the groove 122 in exemplary embodiments, and
pivot the pivotal member 58 from the second position to the first
position.
[0033] The disassembly feature 120 and the pivoting device, such as
the lever 124, may pivot the pivotal member 58 from the second
position to the first position. As discussed above, the turbine
component 34 in the first position may be allowed to move axially
with respect to the support structure 32 in at least one direction.
Thus, pivoting of the pivotal member 58 from the second position to
the first position may allow for the turbine component 34 to be
disassembled from the support structure 32.
[0034] Thus, the axial retention device 50 of the present
disclosure may allow for efficient, cost-effective, and repeatable
assembly, retention, and disassembly of turbine components 34 in
support structures 32. For example, as shown in FIG. 5 and
discussed above, the pivotal member 58 of the axial retention
device 50 may, in the first position, allow a turbine component 34
to be assembled in a support structure 32. After the turbine
component 34 is moved axially with respect to the support structure
32 to a desired position in the support structure 32, the pivotal
member 58 may pivot to a second position, as shown in FIG. 6. In
the second position, the axial retention device 50 may retain the
turbine component 34 within the support structure 32, thus
preventing axial movement of the turbine component 34 with respect
to the support structure 32 in at least one direction. To
disassemble the turbine component 34 from the support structure 32,
as shown in FIG. 7, the pivotal member 58 may be pivoted from the
second position to the first position. In the first position, the
axial retention device 50 may again allow axial movement of the
turbine component 34 within the support structure 32 in at least
one direction.
[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. Further, the use of an axial retention device 50 as
discussed herein may provide for efficient and cost-effective
assembly and disassembly of turbine components 34 in support
structures 32. Further, the axial retention device 50 may provide
for repeated assembly and disassembly of turbine components 34 in
support structures 32 without requiring frequent replacement of the
support structures 32. Additionally, existing turbine components 34
and support structures 32 may be retrofitted to accommodate axial
retention devices 50, thus reducing the time and cost previously
associated with assembly and disassembly of these turbine
components 34 and support structures 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.
* * * * *