U.S. patent application number 13/909124 was filed with the patent office on 2014-12-04 for apparatus for moving turbine shell.
The applicant listed for this patent is General Electric Company. Invention is credited to Gerald Robert Graham, Andrew Thomas Hynous, Larry Alan Poston.
Application Number | 20140356152 13/909124 |
Document ID | / |
Family ID | 50884748 |
Filed Date | 2014-12-04 |
United States Patent
Application |
20140356152 |
Kind Code |
A1 |
Hynous; Andrew Thomas ; et
al. |
December 4, 2014 |
APPARATUS FOR MOVING TURBINE SHELL
Abstract
An apparatus for moving a turbine shell of a turbomachine is
provided. In one embodiment, the apparatus includes a shell support
having a first member and a second member coupled to a side of an
upper portion of a turbine shell. The apparatus also includes an
actuator coupled to the shell support. The actuator may rotate the
upper portion of the turbine shell to expose internal components of
a turbine system. The apparatus may also include a platform
positioned adjacent the shell support and a pivot assembly coupled
to the shell support and actuator. The pivot assembly of the
apparatus may be positioned on a first surface of the platform.
Additionally, the apparatus may include a securing structure
positioned on a second surface of the platform for preventing
movement of the shell support during the rotating of the upper
portion of the turbine shell.
Inventors: |
Hynous; Andrew Thomas;
(Greenville, SC) ; Graham; Gerald Robert;
(Greenville, SC) ; Poston; Larry Alan;
(Greenville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
50884748 |
Appl. No.: |
13/909124 |
Filed: |
June 4, 2013 |
Current U.S.
Class: |
415/201 |
Current CPC
Class: |
F05D 2230/72 20130101;
F01D 25/285 20130101; F05D 2250/411 20130101; F01D 25/24 20130101;
F05D 2260/02 20130101 |
Class at
Publication: |
415/201 |
International
Class: |
F01D 25/24 20060101
F01D025/24 |
Claims
1. An apparatus comprising: a shell support having a first member
and a second member coupled to a side of an upper portion of a
turbine shell; and an actuator coupled to the shell support, the
actuator for rotating the upper portion of the turbine shell to
expose internal components of a turbine system.
2. The apparatus of claim 1, wherein the actuator rotates the upper
portion of the turbine shell to a range of approximately 80 degrees
and approximately 95 degrees from horizontal.
3. The apparatus of claim 1, wherein the actuator is selected from
the group consisting of a mechanical ball screw actuator, a
hydraulic actuator, a pneumatic actuator, and an electric
actuator.
4. The apparatus of claim 1, wherein the first member is coupled to
a plurality of apertures on a vertical flange of the upper portion
of the turbine shell, the plurality of apertures on the vertical
flange for coupling the upper portion of the turbine shell to a
compressor casing during operation of the turbine system.
5. The apparatus of claim 1, wherein the second member is coupled
to a plurality of openings on a horizontal flange of the upper
portion of the turbine shell, the plurality of openings on the
horizontal flange for coupling the upper portion of the turbine
shell to a lower portion of the turbine shell during operation of
the turbine system.
6. The apparatus of claim 5, wherein the first member and the
second member are coupled to the upper portion of the turbine shell
after the upper portion of the turbine shell is positioned above
and separated from the lower portion of the turbine shell.
7. The apparatus of claim 5 further comprising: a platform
positioned adjacent the shell support; a pivot assembly coupled to
the shell support and the actuator, the pivot assembly positioned
on a first surface of the platform; and a securing structure
positioned on a second surface of the platform, the securing
structure for substantially preventing movement of the shell
support during the rotating of the upper portion of the turbine
shell.
8. The apparatus of claim 7, wherein the securing structure is
coupled to a support for supporting the shell support during the
rotation the upper portion of the turbine shell.
9. The apparatus of claim 1, wherein the actuator is operably
connected to a control system configured to control the actuator
during the rotating of the upper portion of the turbine shell.
10. The apparatus of claim 1, wherein the actuator rotates the
upper portion of the turbine shell to engage a support structure
positioned adjacent the turbine shell.
11. A system comprising: a shell rotating apparatus coupled to
opposing sides of an upper portion of a turbine shell, the shell
rotating apparatus including: a shell support having a first member
and a second member coupled to the upper portion of the turbine
shell; and an actuator coupled to the shell support, the actuator
for rotating the upper portion of the turbine shell to expose
internal components of a turbine system; and a control system
operably connected to the actuator of the shell rotating apparatus,
the control system configured to control the actuator during the
rotating of the upper portion of the turbine shell.
12. The system of claim 11, further comprising a support structure
positioned adjacent the shell rotating apparatus, the support
structure for supporting the upper portion of the turbine shell
after the rotating of the upper portion of the turbine shell by the
actuator of the shell rotating apparatus.
13. The system of claim 11, wherein the actuator of the shell
rotating apparatus rotates the upper portion of the turbine shell
to a range of approximately 80 degrees and approximately 95 degrees
from horizontal.
14. The system of claim 11, wherein the actuator is selected from
the group consisting of a mechanical ball screw actuator, a
hydraulic actuator, a pneumatic actuator, and an electric
actuator.
15. The system of claim 11, wherein the first member is coupled to
a plurality of apertures on a vertical flange of the upper portion
of the turbine shell, the plurality of apertures on the vertical
flange for coupling the upper portion of the turbine shell to a
compressor casing during operation of the turbine system.
16. The system of claim 11, wherein the second member is coupled to
a plurality of openings on a horizontal flange of the upper portion
of the turbine shell, the plurality of openings on the horizontal
flange for coupling the upper portion of the turbine shell to a
lower portion of the turbine shell during operation of the turbine
shell.
17. The system of claim 16, wherein the first member and the second
member are coupled to the upper portion of the turbine shell after
the upper portion of the turbine shell is positioned above and
separated from the lower portion of the turbine shell.
18. The system of claim 16, wherein the shell rotating apparatus
further includes: a platform positioned adjacent the shell support;
a pivot assembly coupled to the shell support and the actuator, the
pivot assembly positioned on a first surface of the platform; and a
securing structure positioned on a second surface of the platform,
the securing structure for substantially preventing movement of the
shell support during the rotating of the upper portion of the
turbine shell.
19. The system of claim 18, wherein the securing structure is
coupled to a support for supporting the shell rotating apparatus
during the rotation the upper portion of the turbine shell.
Description
BACKGROUND OF THE INVENTION
[0001] 1. Technical Field
[0002] The disclosure is related generally to turbomachines. More
particularly, the disclosure is related to an apparatus for moving
a turbine shell of the turbomachine.
[0003] 2. Related Art
[0004] Conventional turbomachines, such as gas turbine systems, are
utilized to generate power for electric generators. In general,
conventional turbomachines generate power by passing a fluid (e.g.,
hot gas) through a compressor and a turbine of the turbomachine.
More specifically, fluid may flow through a fluid flow path for
rotating a plurality of rotating buckets of the turbine for
generating the power. The fluid may be directed through the turbine
via the plurality of rotating buckets and a plurality of stationary
nozzles positioned between the rotating buckets. These internal
components (e.g., buckets, nozzles) may be included within a
turbine shell of the turbine. The turbine shell may act as a
housing for the internal components and the fluid passing through
the turbine during operation of the turbomachine.
[0005] When inspection or maintenance must be performed on the
internal components of the turbomachine, the exterior coverings of
each portion of the turbomachine (e.g., compressor, turbine)
typically must be removed. More specifically, when inspection
and/or maintenance must be performed on the internal components
(e.g., buckets, nozzles) of the turbine, at least a portion of the
turbine shell must be removed to allow operators access to these
internal components. In conventional systems, a roof portion of a
housing surrounding the turbomachine must be removed in order for a
crane to access the turbine shell during a maintenance process. The
crane must be capable of lifting the heavy turbine shell from its
operational position within the turbomachine, and may remove the
turbine shell from the housing via a roof opening, or may place the
turbine shell on the floor of the housing, away from the remainder
of the turbomachine. A crane capable of moving the heavy turbine
shell is very expensive. Additionally, the process of removing a
roof portion of the housing surrounding the turbomachine and
removing the turbine shell typically takes multiple days. As a
result, inspection and/or maintenance of the turbomachine may take
multiple weeks to accomplish, where more than a third of the
inoperable time of the turbomachine is a result of the expensive
and labor intensive process of removing the turbine shell from the
turbomachine.
BRIEF DESCRIPTION OF THE INVENTION
[0006] An apparatus for moving a turbine shell of a turbomachine is
disclosed. In one embodiment, the apparatus includes: a shell
support having a first member and a second member coupled to an
upper portion of a turbine shell; and an actuator coupled to the
shell support, the actuator for rotating the upper portion of the
turbine shell to expose internal components of a turbine
system.
[0007] A first aspect of the invention includes an apparatus
having: a shell support having a first member and a second member
coupled to an upper portion of a turbine shell; and an actuator
coupled to the shell support, the actuator for rotating the upper
portion of the turbine shell to expose internal components of a
turbine system.
[0008] A second aspect of the invention includes a system having: a
shell rotating apparatus coupled to opposing sides of an upper
portion of a turbine shell, the shell rotating apparatus including:
a shell support having a first member and a second member coupled
to the upper portion of the turbine shell; and an actuator coupled
to the shell support, the actuator for rotating the upper portion
of the turbine shell to expose internal components of a turbine
system; and a control system operably connected to the actuator of
the shell rotating apparatus, the control system configured to
control the actuator during the rotating of the upper portion of
the turbine shell.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] These and other features of this invention will be more
readily understood from the following detailed description of the
various aspects of the invention taken in conjunction with the
accompanying drawings that depict various embodiments of the
invention, in which:
[0010] FIG. 1 shows a schematic depiction of a turbomachine,
according to various embodiments of the invention.
[0011] FIG. 2 show a perspective view of a portion of a
turbomachine including a shell rotating apparatus according to
various embodiments of the invention.
[0012] FIG. 3 shows an internal perspective view of a shell
rotating apparatus according to various embodiments of the
invention.
[0013] FIG. 4 shows an external perspective view of a shell
rotating apparatus according to various embodiments of the
invention.
[0014] FIG. 5 shows a perspective view of a portion of a
turbomachine including a shell rotating apparatus rotating a
turbine shell according to various embodiments of the
invention.
[0015] FIG. 6 shows a perspective view of a portion of a
turbomachine including a shell rotating apparatus and maintenance
components according to various embodiments of the invention.
[0016] It is noted that the drawings of the invention are not
necessarily to scale. The drawings are intended to depict only
typical aspects of the invention, and therefore should not be
considered as limiting the scope of the invention. In the drawings,
like numbering represents like elements between the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0017] As described herein, aspects of the invention relate to
turbomachines. Specifically, as described herein, aspects of the
invention relate to an apparatus for moving a turbine shell of the
turbomachine.
[0018] Turning to FIG. 1, a schematic depiction of a turbomachine
is shown according to embodiments of the invention. Turbomachine
10, as shown in FIG. 1 may be a conventional gas turbine system.
However, it is understood that turbomachine 10 may be configured as
any conventional turbine system (e.g., steam turbine system)
configured to generate power for an electric generator. As such, a
brief description of the turbomachine 10 is provided for clarity.
As shown in FIG. 1, turbomachine 10 may include a compressor 12,
combustor 14 fluidly coupled to compressor 12 and a gas turbine
component 16 fluidly coupled to combustor 14 for receiving a
combustion product from combustor 14. Gas turbine component 16 may
also be coupled to compressor 12 via shaft 18. Shaft 18 may also be
coupled to a generator 20 for creating electricity during operation
of turbomachine 10. In an embodiment, as shown in FIG. 1, a turbine
housing 21 may substantially surround turbomachine 10 and the
components (e.g., compressor 12, turbine component 16) of
turbomachine 10.
[0019] During operation of turbomachine 10, as shown in FIG. 1,
compressor 12 may take in air and compress the inlet air before
moving the compressed inlet air to the combustor 14. Once in the
combustor 14, the compressed air may be mixed with a combustion
product (e.g., fuel) and ignited. Once ignited, the compressed
air-combustion product mixture is converted to a hot pressurized
exhaust gas (hot gas) that flows through gas turbine component 16.
The hot gas flows through gas turbine component 16, and
specifically, passes over a plurality of buckets 22 (e.g., stages
of buckets) coupled to shaft 18, and a plurality of stator nozzles
24 coupled to a turbine shell 26 of turbine component 16. The hot
gas flows over the plurality of buckets 22 which rotates buckets 22
and shaft 18 of turbomachine 10, respectively. The plurality of
stator nozzles 24 may aid in directing the hot gas through turbine
component 16, and more specifically, may direct the hot gas from an
upstream set of buckets 22 to a downstream set of buckets 22. As
shaft 18 of turbomachine 10 rotates, compressor 12 and gas turbine
component 16 are driven and generator 20 may create power (e.g.,
electric current).
[0020] As used herein, the terms "axial" and/or "axially" refer to
the relative position/direction of objects along axis A, which is
substantially parallel with the axis of rotation of turbomachine 10
(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.
[0021] Turning to FIG. 2, a perspective view of a portion of
turbomachine 10 including a shell rotating apparatus is shown
according to various embodiments of the invention. In an
embodiment, as shown in FIG. 2, turbine shell 26 of turbomachine 10
(FIG. 1) may include an upper portion 100 and a lower portion 102.
During operation of turbomachine 10 (FIG. 1), upper portion 100 may
be coupled to lower portion 102 in order to form turbine shell 26
of turbomachine 10 (FIG. 1). More specifically, horizontal flange
104 of upper portion 100 and horizontal flange 106 of lower portion
102 may be coupled to form turbine shell 26. In an embodiment, as
shown in FIG. 2, horizontal flange 104 of upper portion 100 may
include a plurality of openings 110, and horizontal flange 106 of
lower portion 102 may include a plurality of openings 112. The
plurality of openings 110 of upper portion 100 may be in alignment
with the plurality of openings 112 of lower portion 102 when
horizontal flange 104 of upper portion 100 and horizontal flange
106 of lower portion 102 contact one another. During operation,
each of the plurality of openings 110, 112 may be configured to
receive a fastening component (e.g., bolt, threaded fastener,
cotter pin, etc.), not shown, for coupling upper portion 100 to
lower portion 102. Upper portion 100 may be coupled to lower
portion 102 of turbine shell 26 by any conventional mechanical
coupling technique including, but not limited to, welding, brazing,
snap-fit, slot-fit, bolt, rivet, etc. During operation of
turbomachine 10 (FIG. 1), upper portion 100 may be coupled to lower
portion 102 to form turbine shell 26, which may provide internal
components (e.g., stator nozzles 24) to turbomachine 10 (FIG. 10),
and may provide a continuous housing for hot gas to flow through
gas turbine component 16 (FIG. 1).
[0022] Additionally, during operation of turbomachine 10 (FIG. 1)
turbine shell 26 may be coupled to compressor casing 114 of
compressor 12 (FIG. 1). More specifically, as shown in FIG. 2,
upper portion 100 of turbine shell 26 may include a vertical flange
116, which may be coupled to a vertical flange 118 of compressor
casing 114. In an embodiment, as shown in FIG. 2, vertical flange
116 may be positioned substantially adjacent to, and perpendicular
to horizontal flange 104 of turbine shell 26. As shown in FIG. 2,
vertical flange 116 of upper portion 100 may include a plurality of
apertures 120, and vertical flange 118 of compressor casing 114 may
also include a plurality of apertures 122. The plurality of
apertures 120 of upper portion 100 may be in alignment with the
plurality of apertures 122 of compressor casing 114 when vertical
flange 116 of upper portion 100 and vertical flange 118 of
compressor casing 114 are in substantial contact. During operation,
each of the plurality of apertures 120, 122 may be configured to
receive a fastening component (e.g., bolt, threaded fastener,
cotter pin, etc.), not shown, for coupling upper portion 100 to
compressor casing 114. Upper portion 100 of turbine shell 26 may be
coupled to compressor casing by any conventional mechanical
coupling technique now known, or later developed. During operation
of turbomachine 10 (FIG. 1) upper portion 100 of turbine shell 26
may be coupled to compressor casing 114 of compressor 12 to provide
internal components (e.g., stator nozzles 24) to turbomachine 10
(FIG. 1) and provide a continuous housing for hot gas to flow
through turbomachine 10.
[0023] When a maintenance process must be performed on turbomachine
10 (FIG. 1), turbomachine 10 must be powered down and, at least
partially disassembled for inspection and/or maintenance of the
internal component (e.g., buckets 22) of turbomachine 10. More
specifically, when a maintenance process must be performed on
turbine component 16 of turbomachine 10 (FIG. 1), upper portion 100
of turbine shell 26 must be removed from turbomachine 10. As
discussed herein, shell rotating apparatus 200, as shown in FIGS.
2-5, may remove upper portion 100 of turbine shell 26 from
turbomachine 10, without removing a roof portion 124 of turbine
housing 21 (FIG. 1).
[0024] Once turbomachine 10 (FIG. 1) is powered down, a maintenance
process may be performed on turbomachine, and specifically, turbine
component 16 (FIG. 1). Preliminarily, upper portion 100 of turbine
shell 26 may be uncoupled from turbomachine 10 (FIG. 1).
Specifically, upper portion 100 of turbine shell 26 may be
uncoupled from lower portion 102 of turbine shell 26 and compressor
casing 114 of compressor 12, respectively. The fastening
components, not shown, coupling the horizontal flanges 104, 106 of
upper portion 100 and lower portion 102, and the fastening
components, not shown, coupling the vertical flanges 116, 118 of
upper portion 100 and compressor casing 114 may be removed.
[0025] After removing the fastening components (not shown) coupling
upper portion 100 to lower portion 102 and compressor casing 114,
respectively, upper portion 100 of turbine shell 26 may be
positioned substantially above and separate from lower portion 102
of turbine shell 26. More specifically, as shown in FIG. 2, upper
portion 100 of turbine shell 26 may be lifted above lower portion
102 of turbine shell to a predetermined distance (D), such that the
plurality of openings 104 positioned on horizontal flange 110 of
upper portion 100 may remain in substantial alignment with the
plurality of openings 112 on horizontal flange 106 of lower portion
102. Predetermined distance (D) may be, at least in part, dependent
upon the height of compressor casing 114. More specifically, upper
portion 100 of turbine shell 26 may be positioned above and
separate from lower portion 100 a predetermined distance (D), which
may allow upper portion 100 to be rotated and positioned
substantially above compressor casing 114 and substantially below
roof portion 124, as discussed herein. Upper portion 100 may be
positioned above and separate from lower portion 102 of turbine
shell 26 by any conventional mechanical lift mechanism including,
but not limited to, a hydraulic lift, a stanchion-style support, a
pneumatic actuator, internal crane of turbomachine 100 (FIG. 1),
etc.
[0026] After upper portion 100 of turbine shell 26 is positioned
substantially above and separated from lower portion 102 of turbine
shell 26, a shell rotating apparatus 200 may be coupled to each
opposing side 126 of upper portion 100 of turbine shell 26. More
specifically, as shown in FIG. 2, shell rotating apparatus 200 may
be coupled to each opposing side 126 of upper portion 100 of
turbine shell 26, adjacent horizontal flange 104 and vertical
flange 116 of upper portion 100. As discussed herein, shell
rotating apparatus 200 may be utilized during a maintenance process
being performed on turbomachine 10 (FIG. 1) to rotate and position
upper portion 100 substantially above compressor casing 114.
[0027] As shown in FIG. 2, and with reference to FIGS. 3 and 4,
shell rotating apparatus 200 may include a base 202, and a shell
support 204 coupled to base 202. In an embodiment, as shown in
FIGS. 2 and 3, base 202 may include a securing structure 206 for
substantially preventing movement of shell rotating apparatus 200
during rotation of upper portion 100 of turbine shell 26, as
discussed herein. As shown in FIGS. 2 and 3, securing structure 206
may include a first component 208 positioned substantially vertical
with respect to axis (A) of rotation. That is, first component 208
may be substantially parallel with vertical flange 118 of
compressor casing 114. As shown in FIGS. 2 and 3, first component
208 may include a plurality of mounting holes 210 formed through
first component 208. As shown in FIG. 2, the plurality of mounting
holes 210 of first component 208 of securing structure 206 may be
substantially aligned with the plurality of apertures 122 formed on
compressor casing 114 of compressor 12. The plurality of mounting
holes 210 of first component 208 of securing structure 206 and the
plurality of apertures 122 of compressor casing 114 may be
configured to receive a fastening component (e.g., bolt, threaded
fastener, cotter pin, etc.), not shown, in order to couple first
component 208 of securing structure 206 to compressor casing 114 of
compressor 12. As discussed herein, by coupling first component 208
to compressor casing 114, shell rotating apparatus 200 may be made
substantially secure or stable (e.g., not move) during the rotation
of upper portion 100 of turbine shell 26. In an alternative
embodiment, not shown, first component 208 of securing structure
206 may be coupled to compressor casing 114 of compressor 12 by any
conventional mechanical coupling technique now known, or later
developed.
[0028] First component 208 of securing structure 206, as shown in
FIGS. 2 and 3, may also include a substantially curved surface 212
positioned adjacent the plurality of mounting holes 210.
Substantially curved surface 212 may include an arc profile
substantially similar to the arc profile of compressor casing 114
of compressor 12. More specifically, with reference to FIG. 2, the
arc profile of substantially curved surface 212 of first component
208 may be substantially similar and in substantial alignment with
the arc profile of a portion of vertical flange 118 of compressor
casing 114 coupled to first component 208. As discussed herein,
substantially curved surface 212 of first component 208 may prevent
obstruction and/or may minimize inaccessibility to certain portions
of turbomachine 10 (FIG. 1) when a maintenance process is being
performed on turbomachine 10. That is, first component 208 of
securing structure 206 may aid in securing shell rotating apparatus
200 to turbomachine 10 (FIG. 1) without substantially obstructing
portions of turbomachine 10 while a maintenance process is being
performed on turbomachine 10. However, it is understood that first
component 208 of securing structure 206 may not require
substantially curved surface 212. More specifically, first
component 208 may include a substantially polygonal (e.g.,
rectangular) configuration, wherein a portion of first component
structure 208 may extend beyond the portion of vertical flange 118
of compressor casing 114 coupled to first component 208.
[0029] Also shown in FIGS. 2 and 3, securing structure 206 may
include a second component 214 positioned substantially horizontal
with respect to axis (A) of rotation. As shown in FIGS. 2 and 3,
second component 214 of securing structure 206 may be substantially
parallel with horizontal flange 106 of lower portion 102 of turbine
shell 26, and may be positioned substantially perpendicular to
first component 208. In an embodiment, as shown in FIGS. 2 and 3,
second component 214 may include a plurality of mounting holes 216
formed through second component 214. As shown in FIG. 2, the
plurality of mounting holes 216 may be substantially aligned with
the plurality of openings 112 on lower portion 102 of turbine shell
26. The plurality of mounting holes 216 of second component 214 of
securing structure 206 and the plurality of openings 112 of lower
portion 102 may be configured to receive a fastening component
(e.g., bolt, threaded fastener, cotter pin, etc.), not shown, in
order to couple second component 214 of securing structure 206 to
lower portion 102 of turbine shell 26. In an alternative
embodiment, not shown, second component 214 of securing structure
206 may be coupled to lower portion 102 of turbine shell 26 by any
conventional mechanical coupling technique now known, or later
developed.
[0030] Second component 214 of securing structure 206, as shown in
FIGS. 2 and 3, may also include a substantially curved surface 218
positioned opposite platform 150 of shell rotating apparatus 200.
Substantially curved surface 218 may include an arc profile
substantially similar to the arc profile of lower portion 102 of
turbine shell 26. More specifically, with reference to FIG. 2, the
arc profile of substantially curved surface 218 of second component
214 may be substantially similar and in substantial alignment with
the arc profile of a portion of horizontal flange 106 of lower
portion 102. As discussed herein, second component 214 of securing
structure 206 may aid in securing shell rotating apparatus 200 to
turbomachine 10 (FIG. 1) and a fixed mounting, and substantially
curved surface 218 of second component 214 may prevent obstruction
and/or may minimize inaccessibility to certain portions of
turbomachine 10 (FIG. 1) when a maintenance process is being
performed on turbomachine 10. Similar to first component 208, it is
understood that second component 214 of securing structure 206 may
not require substantially curved surface 218. More specifically,
second component 214 may include a substantially polygonal (e.g.,
rectangular) configuration, wherein a portion of second component
214 may extend beyond the portion of horizontal flange 106 of lower
portion 102 coupled to second component 214.
[0031] As shown in FIG. 2, securing structure 206 of base portion
202 of rotating apparatus 200 may also be coupled to support 219.
More specifically, turbomachine 10 (FIG. 1) may include support 219
coupled to a portion of the floor of turbine housing 21 (FIG. 1),
and support 219 may extend from the floor adjacent to rotating
apparatus 200 for supporting rotating apparatus 200 during the
rotation of upper portion 100 of turbine shell 26. Securing
structure 206 of base portion 202 may be coupled to support 219 by
any conventional coupling technique now know or later
developed.
[0032] In an alternative embodiment, not shown, first component 208
and/or second component 214 of securing structure 206 may be
coupled to a support base positioned outside of the components
(e.g., lower portion 102, compressor casing 114) of turbomachine 10
(FIG. 1). That is, securing structure 206 may be coupled to a
support base positioned adjacent turbomachine 10 (FIG. 1) for
substantially preventing movement of shell support 204 of shell
rotating apparatus 200 during the rotation of upper portion 100 of
turbine shell 26, as discussed herein. In the alternative
embodiment, the support base may be coupled to a portion a floor of
turbine housing 21 (FIG. 1). That is, securing structure 206 of
shell rotating apparatus 200 may not be coupled to turbomachine 10,
and as discussed herein, only the components of shell support 204
may be coupled to upper portion 100 of turbine shell 26. As a
result, shell rotating apparatus 200 may be positioned within
housing 21 (FIG. 1) during the operation of turbomachine 10, such
that during a maintenance process being performed on turbomachine
10, shell rotating apparatus 200 may be readily available to rotate
upper portion 100 of turbine shell 26 in a substantially short
period of time.
[0033] As shown in FIGS. 2-4, shell rotating apparatus 200 may also
include a platform 220, and a pivot assembly 222 positioned on
platform 220. As shown in FIGS. 3 and 4, pivot assembly 222 may be
positioned on a first surface 224 of platform 220, and securing
structure 206 may be positioned on a second surface 226 of platform
220. As shown in FIGS. 3 and 4, platform 220 may form a base for
shell support 204 of shell rotating apparatus 200 and pivot
assembly 222, respectively. That is, platform 220 may provide a
surface (e.g., first surface 224) for mounting pivot assembly 222,
and shell support 204 coupled to pivot assembly 222, to be used for
rotating upper portion 100 of turbine shell 26 (FIG. 2), as
discussed herein. As shown in FIGS. 3 and 4, pivot assembly 222 and
securing structure 206 may be positioned on platform 220 by any
conventional mechanical coupling technique now known or later
developed.
[0034] In an embodiment, as shown in FIGS. 2-4, pivot assembly 222
may be coupled to shell support 204. More specifically, as shown in
FIGS. 3 and 4, shell support 204 of shell rotating apparatus 200
may be coupled to pivot assembly 222 via a pivot structure 228
positioned through shell support 204 and coupled to pivot assembly
222. That is, pivot structure 228 may be positioned through shell
support 204 and may engage pivot assembly 222 to substantially
secure shell support 204 to pivot assembly 222. Pivot assembly 222,
and more specifically pivot structure 228, may be configured to
allow shell support 204, and upper portion 100 of turbine shell 26
coupled to shell support 204 (FIG. 2), to rotate, as discussed
herein.
[0035] As shown in FIGS. 2-4, shell support 204 of shell rotating
apparatus 200 may include a first member 230 and a second member
232. In an embodiment, as shown in FIGS. 2-4, shell support 204 may
include a substantially polygonal body structure having a first
portion 234 positioned substantially vertical with respect to axis
(A) of rotation. First member 230 of shell support 204 may be
coupled to first portion 234. More specifically, as shown in FIGS.
2-4, first member 230 may be coupled to first portion 234 of shell
support 204 by a plurality of threaded fasteners 236 positioned
through first portion 234 for engaging and substantially securing
first member 230 to shell support 204. In an alternative
embodiment, not shown, first member 230 may be coupled to first
portion 234 of shell support 204 by any conventional mechanical
coupling technique including, but not limited to, welding, brazing,
snap-fit, slot-fit, bolt, rivet, etc.
[0036] In an embodiment, as shown in FIGS. 2-4, shell support 204
may also include a second portion 238 positioned substantially
adjacent first portion 234. More specifically, as shown in FIGS.
2-4, second portion 238 may be positioned adjacent to first portion
234, and may be positioned substantially parallel with respect to
axis (A) of rotation. Second member 232 of shell support 204 may be
coupled to second portion 238. More specifically, as shown in FIGS.
2-4, and as similarly discussed with respect to first member 230,
second member 232 may be coupled to second portion 238 of shell
support 204 by the plurality of threaded fasteners 236 positioned
through second portion 238. The plurality of threaded fasteners 236
may substantially engage and secure second member 232 to second
portion 238 of shell support 204. In an alternative embodiment, not
shown, second member 232 may be coupled to second portion 238 of
shell support 204 by any conventional mechanical coupling technique
including, but not limited to, welding, brazing, snap-fit,
slot-fit, bolt, rivet, etc. Additionally, although first member 230
and second member 232 of shell support 204 are shown as separate
components of shell rotating apparatus 200, it is understood that
first member 230 and second member 232 and/or shell support 204 may
be configured as a single component. It is understood that the
shape of shell support 204 may vary from that illustrated in FIGS.
3 and 4.
[0037] As shown in FIG. 2, first member 230 and second member 232
of shell support 204 may be coupled to an upper portion 100 of
turbine shell 26. More specifically, as shown in FIG. 2, first
member 230 and second member 232 of shell support 204 may be
coupled to upper portion 100 of turbine shell 26 after upper
portion 100 is positioned above and substantially separate from a
lower portion 102 of turbine shell 26. As shown in FIG. 2, first
member 230 of shell support 204 may be coupled the plurality of
apertures 120 positioned on a vertical flange 116 of upper portion
100 of turbine shell 26. More specifically, as shown in FIG. 2,
first member 230 of shell support 204 may be coupled to the
plurality of apertures 120 positioned on vertical flange 116
adjacent side 126 of upper portion 100 of turbine shell 26. As
shown in FIGS. 3 and 4, first member 230 may include a plurality of
mounting holes 240 formed through first member 230, and the
plurality of mounting holes 240 may be substantially aligned with
the plurality of apertures 120 positioned on vertical flange 116 of
upper portion 100 (FIG. 2). The plurality of mounting holes 240
(FIGS. 3 and 4) of first member 230 and the plurality of apertures
120 of upper portion 100 (FIG. 2) may be configured to receive a
fastening component (e.g., bolt, threaded fastener, cotter pin,
etc.), not shown, in order to couple upper portion 100 of turbine
shell 26 to first member 230 of shell support 204. In an
alternative embodiment, not shown, upper portion 100 of turbine
shell 26 may be coupled to first member 230 of shell support 204 by
any conventional mechanical coupling technique now known, or later
developed.
[0038] As shown in FIGS. 3 and 4, first member 230 of shell support
204 may also include a substantially curved surface 242 positioned
opposite first portion 234 of shell support 204. When coupled to
upper portion 100, substantially curved surface 242 of first member
230 may be positioned adjacent vertical flange 116 of upper portion
100 of turbine shell 26. Substantially curved surface 242 may
include an arc profile substantially similar to the arc profile of
vertical flange 116 of upper portion 100 of turbine shell 26. More
specifically, with reference to FIGS. 2-4, the arc profile of
substantially curved surface 242 of first member 230 (FIGS. 3 and
4) may be substantially similar and in substantial alignment with
the arc profile of a portion of vertical flange 116 of upper
portion 100 (FIG. 2) coupled to first member 230. As discussed
herein, substantially curved surface 242 of first member 230 may
prevent obstruction and/or may minimize inaccessibility to certain
portions of turbomachine 10 (FIG. 1) when a maintenance process is
being performed on turbomachine 10. However, it is understood that
first member 230 of shell support 204 may not require substantially
curved surface 242. More specifically, first member 230 may include
a substantially polygonal (e.g., rectangular) configuration,
wherein a portion of first member 230 may extend beyond the portion
of vertical flange 116 of upper portion 100 coupled to first member
230.
[0039] In an embodiment, as shown in FIG. 2, second member 232 of
shell support 204 may be coupled to a plurality of openings 110
positioned on a horizontal flange 104 of upper portion 100 of
turbine shell 26. More specifically, as shown in FIG. 2, second
member 232 of shell support 204 may be coupled to the plurality of
openings 110 positioned on horizontal flange 104 adjacent side 126
of upper portion 100 of turbine shell 26. That is, horizontal
flange 104, and specifically the plurality of openings 110 on
horizontal flange 104, may be positioned adjacent vertical flange
116 of upper portion 100, such that the respective members (e.g.,
first member 230, second member 232) of shell support 204 may be
coupled to the respective flanges (e.g., vertical flange 116,
horizontal flange 104) of upper portion 100 of turbine shell 26. As
shown in FIGS. 2-4, second member 232 may include a plurality of
mounting holes 244 (FIGS. 3 and 4) formed through second member
232, similar to the plurality of mounting holes 240 formed through
first member 230. The plurality of mounting holes 224 may be
substantially aligned with the plurality of openings 110 positioned
on horizontal flange 104 of upper portion 100 (FIG. 2). The
plurality of mounting holes 224 (FIGS. 3 and 4) of second member
232 and the plurality of openings 110 of upper portion 100 (FIG. 2)
may be configured to receive a fastening component (e.g., bolt,
threaded fastener, cotter pin, etc.), not shown, in order to couple
upper portion 100 of turbine shell 26 to second member 232 of shell
support 204. In an alternative embodiment, not shown, upper portion
100 of turbine shell 26 may be coupled to second member 232 of
shell support 204 by any conventional mechanical coupling technique
now known, or later developed.
[0040] Similar to first member 230, second member 232 of shell
support 204 may include a substantially curved surface 246
positioned opposite second portion 238 of shell support 204, as
shown in FIGS. 3 and 4. When coupled to upper portion 100,
substantially curved surface 246 of second member 232 may be
positioned adjacent horizontal flange 104 of upper portion 100 of
turbine shell 26. Substantially curved surface 246 of second member
232 may include an arc profile substantially similar to the arc
profile of horizontal flange 104 of upper portion 100 of turbine
shell 26. More specifically, with reference to FIGS. 2-4, the arc
profile of substantially curved surface 246 of second member 232
(FIGS. 3 and 4) may be substantially similar and in substantial
alignment with the arc profile of a portion of horizontal flange
104 of upper portion 100 (FIG. 2) coupled to second member 232. As
discussed herein, substantially curved surface 246 of second member
232 may prevent obstruction and/or may minimize inaccessibility to
certain portions of turbomachine 10 (FIG. 1) when a maintenance
process is being performed on turbomachine 10. Similar to first
member 230, it is understood that second member 232 of shell
support 204 may not require substantially curved surface 246. More
specifically, second member 232 may include a substantially
polygonal (e.g., rectangular) configuration, wherein a portion of
second member 232 may extend beyond the portion of horizontal
flange 104 of upper portion 100 coupled to second member 232.
[0041] Although shown as single components, it is understood that
first member 230 and second member 232 of shell support 204 may be
configured as multiple components. More specifically, in an
alternative embodiment, not shown, first member 230 and/or second
member 232 may be formed from a plurality of distinct components
coupled to shell support 204 of shell rotating apparatus 200. In
the alternative embodiment, the plurality of components making up
first member 230 and/or second member 232 may be positioned along
first portion 234 and/or second portion 238, respectively, and may
be substantially spaced apart from one another.
[0042] In an embodiment, as shown in FIGS. 2-4, shell rotating
apparatus 200 may also include an actuator 248 coupled to shell
support 204. As discussed herein, actuator 248 of shell rotating
apparatus 200 may be configured to rotate upper portion 100 of
turbine shell 26 to expose internal components (e.g., shaft 18,
buckets 22, stator nozzles 24) of turbomachine 10 (FIG. 1). As
shown in FIGS. 2-4, actuator 248 may be coupled to shell support
204 adjacent first portion 234 and first member 230, respectively.
More specifically, as shown in FIGS. 2-4, actuator 248 may be
coupled to a first end 250 of shell support 204 positioned
substantially above horizontal flange 104 of upper portion 100.
Actuator 248, as shown in FIGS. 2-4, may include a conventional
mechanical ball screw actuator. However, it is understood that
actuator 248 may be selected from a group of any conventional
actuators capable of rotating upper portion 100 of turbine shell 26
including, but not limited to, a hydraulic actuator, a pneumatic
actuator, mechanical actuator, or an electric actuator.
[0043] Additionally, as shown in FIGS. 3 and 4, pivot assembly 222
may be coupled to actuator 248. More specifically, as shown in FIG.
4, actuator 248 may include a piston 252 coupled to a pin 254 of
pivot assembly 222. In coupling piston 252 of actuator 248 to pin
254 of pivot assembly 222, actuator 248 may rotate shell support
102, and upper portion 100 of turbine shell 26 coupled to shell
support 102 (FIG. 2), during the actuation of actuator 248. More
specifically, as shown in FIG. 5, by constraining piston 252 of
actuator 248, during the actuation of actuator 248 where piston 252
retracts into actuator 248, first end 250 of shell support 102 may
move with actuator 248 such that first end 250 of shell support 102
is moved closer to lower portion 102 of turbine shell 26 (FIG. 2).
Simultaneously, as first end 250 of shell support 102 moves closer
to lower portion 102 of turbine shell 26 (FIG. 2), a second end 256
of shell support 102 moves away from lower portion 102 of turbine
shell 26. As a result, as shown in FIG. 5, shell support 204, and
upper portion 100 of turbine shell 26 may be substantially rotated,
and first member 230 of shell support 204 may be substantially
horizontal with respect to axis (A) of rotation, and second member
232 of shell support 204 may be substantially vertical with respect
axis (A) of rotation. That is, shell support 204 may substantially
rotate upper portion 100 of turbine shell 26, for positioning upper
portion above compressor 12, as discussed herein, and/or
positioning upper portion 100 of turbine shell 26 to be more easily
relocated while a maintenance process may be performed on turbine
component 16.
[0044] In an embodiment, as shown in FIG. 5, actuator 248 of shell
rotating apparatus 200 may rotate upper portion 100 of turbine
shell 26 to a range of approximately 80 degrees and approximately
95 degrees from horizontal or axis (A) of rotation. More
specifically, actuator 248 of shell rotating apparatus 200 may
rotate upper portion 100 of turbine shell 26 approximately 85
degrees from horizontal. As shown in FIG. 5, the rotating of upper
portion 100 of turbine shell 26 may include positioning upper
portion 100 of turbine shell 26 above compressor casing 114 of
compressor 12, within turbine housing 21 (FIG. 1). More
specifically, as shown in FIG. 5, upper portion 100 of turbine
shell 26 may be rotated and positioned above compressor casing 114
using shell rotating apparatus 200, without having to remove a roof
portion 124 of turbine housing 21, as discussed herein.
[0045] Shell rotating apparatus 200, and specifically actuator 248,
may rotate upper portion 100 of turbine shell 26 until upper
portion 100 substantially engages a support structure 258
positioned adjacent turbine shell 26. More specifically, as shown
in FIG. 5, upper portion 100 may be rotated to be positioned above
compressor casing 114 and may substantially engage support
structure 258 in order to be positioned in a desirable maintenance
position prior to performing a maintenance process on turbomachine
10 (FIG. 1). In an embodiment, as shown in FIG. 5, vertical flange
116, now positioned substantially horizontal with respect to axis
(A) of rotation, may substantially engage support structure 258. As
shown in FIG. 5, support structure 258 may be positioned
substantially adjacent shell rotating apparatus 200, turbine shell
26 and compressor casing 114, respectively. In an embodiment,
support structure 258 may be positioned on the floor of turbine
housing 21 for supporting upper portion 100 of turbine shell 26
after the rotating of upper portion 100 by actuator 248. That is,
support structure 258 may provide additional support to upper
portion 100 of turbine shell 26, and/or may relief some of the
mechanical stress placed on shell rotating apparatus 200 once upper
portion 100 of turbine shell 26 is positioned above compressor
casing 114. In an alternative embodiment, support structure 258 may
be coupled to a component (e.g., compressor casing 114, turbine
shell 26) of turbomachine 10 (FIG. 1) for supporting upper portion
100 after rotation.
[0046] As shown in FIGS. 2 and 5, actuator 248 may be operably
connected to a control system 260 configured to control actuator
248 during the rotating of upper portion 100 of turbine shell 26,
as discussed herein. Control system 260 may be configured as any
conventional user-interactive or automated computer system for
controlling actuator 248 during the rotating of upper portion 100
of turbine shell 26. That is, control system 260 may include any
conventional or standard control system, which may contain at least
a portion of computerized features, corresponding with actuator 248
of shell rotating apparatus 200.
[0047] In an embodiment, as shown in FIG. 6, after upper portion
100 of turbine shell 26 has be rotated by shell rotating apparatus
200, maintenance components 300 may be coupled to turbomachine 10
(FIG. 1). More specifically, as shown in FIG. 6, maintenance
components 300 may be coupled to upper portion 100 of turbine shell
26 and compressor casing 114 of compressor 12. As shown in FIG. 6,
maintenance components 300 may include a platform system 302
coupled to upper portion 100 of turbine shell 26, and a storage
rack 303 coupled to compressor casing 114 of compressor 12.
Platform system 302 may include a base structure 304 coupled
directly to upper portion 100 of turbine shell 26. More
specifically, as shown in FIG. 6, base structure 304 may be coupled
to horizontal flange 104 of upper portion 100, and both an outer
surface 128 and inner surface 130 of upper portion 100 of turbine
shell 26. Base structure 304 of platform system 302 may be
positioned substantially above vertical flange 116 of upper portion
100, and may include additional supports 308 (shown in phantom)
coupled to vertical flange 116 of upper portion 100. Supports 308
may provide additional structural support to platform system 302,
however, it is understood that supports 308 may not be required to
couple platform system 302 to upper portion 100 of turbine shell
26. In an embodiment, as shown in FIG. 6, base structure 304 may
provide a framework for platform system 302, such that a turbine
operator performing maintenance on turbomachine 10 (FIG. 1) may
walk around rotated upper portion 100 of turbine shell using
platform system 302.
[0048] Platform system 302, as shown in FIG. 6, may also include a
deck surface 310 coupled to base structure 304. More specifically,
deck surface 310 may be positioned substantially over base
structure 304 to provide a turbine operator a platform for walking
around upper portion 100 of turbine shell 26, and/or providing
overhead access to the internal components (e.g., buckets 22) of
turbine component 16 (FIG. 1). Deck surface 310 may include any
conventional material for providing the turbine operator a flat
walkway or platform to walk on including, but not limited to,
plywood, sheet metal, rubber matting, etc.
[0049] In an embodiment, as shown in FIG. 6, platform system 302
may also include boundary rails 312 coupled to base structure 304.
More specifically, boundary rails 312 may be coupled to base
structure 304 opposite upper portion 100 of turbine shell 26 for
providing a substantially enclosed work area for platform system
302. Boundary rails 312 may be coupled to base structure 304 by any
conventional mechanical coupling technique now known or later
developed. Boundary rails 312 may include any conventional
substantially vertical framework structure configured to provide a
boundary for platform system 302 and/or prevent a user walking on
platform system 302 from undesirably leaving deck surface 310.
[0050] As shown in FIG. 6, storage rack 303 of maintenance
components 300 may be coupled to compressor casing 114 of
compressor 12. More specifically, storage rack 303 may be coupled
to compressor casing 114 adjacent upper portion 100 of turbine
shell 26 and platform system 302, respectively. Storage rack 303
may include a support frame 314 coupled to an outer surface 132 of
compressor casing 114. In an embodiment, as shown in FIG. 6,
storage rack 303 may also include a plurality of rack protrusions
316. Each of the plurality of rack protrusions 316 may be
positioned substantially perpendicular to support frame 314, and
may extend toward platform system 302. The plurality of rack
protrusions 316 of storage rack 303 may provide a user on platform
system 302, who may be performing a maintenance process on
turbomachine 10 (FIG. 1), the ability to temporarily store
components of turbomachine 10 (FIG. 1). That is, storage rack 303
may provide a user performing maintenance on turbomachine 10 (FIG.
1) an onsite, temporary storage component for holding internal
components (e.g., buckets 22) that may need to be serviced and/or
removed from turbine component 16 (FIG. 1) so maintenance may be
performed on other components of turbine component 16.
[0051] By utilizing shell rotating apparatus 200 during a
maintenance process of turbomachine 10 (FIG. 1), a roof portion 124
of turbine housing 21 (FIG. 1) may not be required to be removed in
order to move upper portion 100 of turbine shell 26. That is, shell
rotating apparatus 200 may remove upper portion 100 of turbine
shell 26 from turbomachine 10, without the need of a conventional
overheard crane (not shown). These conventional overheard cranes
may require that a roof portion 124 of housing 21 be removed to
gain access to upper portion 100 of turbine shell 26, which can be
expensive and time consuming. As a result, by utilizing shell
rotating apparatus 200, maintenance process may be performed on
turbomachine 10 (FIG. 1) with a reduced cost and reduced
operational downtime of turbomachine 10, by comparison to
conventional processes.
[0052] The material used for shell rotating apparatus 200 may be
any combination of material capable of withstanding the weight of
upper portion 100 during the rotation process. More specifically,
shell rotating apparatus 200, and the respective components (e.g.,
base portion 202, shell support 204), may be made from any
conventional material capable of withstanding the force placed on
shell rotating apparatus 200 during the rotating of upper portion
100 including, but not limited to, steel alloys, aluminum alloys,
iron alloys, titanium, etc.
[0053] As discussed herein, actuator 248 may include a simple pivot
hinge assembly (e.g., piston 252, pin 254) for rotating upper
portion 100 of turbine shell 26. However, it is understood that a
plurality of conventional pivot assemblies and/or rotating
mechanisms may be used with shell rotating apparatus 200. For
example, a floating hinge assembly or lift hinge assembly may be
utilized by shell rotating apparatus 200 to provide an amount of
translational movement when removing upper portion 100 from turbine
shell 26.
[0054] Although discussed herein as turbine shell 26 being
configured as two portions (e.g., upper portion 100, lower portion
102), it is understood that turbine shell 26 may include a
plurality of portions. For example, in an alternative embodiment,
turbine shell 26 may be configured in four separate portions. In
the alternative embodiment, a single shell rotating apparatus 200
may be coupled to each of the two quarters that form the upper
portion 100 of turbine shell 26. As a result, each of the shell
rotating apparatus 200 may rotate the individual portions forming
upper portion 100 of turbine shell 26 distinct of one another.
[0055] Additionally, it is understood that a single shell rotating
apparatus 200 may be utilized for rotating upper portion 100 of
turbine shell 26. More specifically, a single shell rotating
apparatus 200 may be coupled to a single side 126 of upper portion
100 of turbine shell 26 for rotating upper portion 100 during a
maintenance process of turbomachine 10 (FIG. 1). In an embodiment
using only one shell rotating apparatus 200, a plurality of support
structures 258 may be used with turbomachine 10 to help alleviate
the stress placed on the single shell rotating apparatus 200 during
the rotating of upper portion 100 of turbine shell 26. That is, the
plurality of support structures 258 may substantially support upper
portion 100 of turbine shell 26 after upper portion 100 is rotated,
which may result in less stress placed on the singe shell rotating
apparatus 200 while a maintenance process is being performed on
turbomachine 10.
[0056] 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.
[0057] 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.
* * * * *