[0001] The disclosure is related generally to turbomachines. More particularly, the disclosure
is related to an apparatus for moving a turbine shell of the turbomachine.
[0002] 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.
[0003] 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.
[0004] 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.
[0005] 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.
[0006] 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.
[0007] 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:
FIG. 1 shows a schematic depiction of a turbomachine, according to various embodiments
of the invention.
FIGS. 2 show a perspective view of a portion of a turbomachine including a shell rotating
apparatus according to various embodiments of the invention.
FIG. 3 shows an internal perspective view of a shell rotating apparatus according
to various embodiments of the invention.
FIG. 4 shows an external perspective view of a shell rotating apparatus according
to various embodiments of the invention.
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.
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.
[0008] 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.
[0009] 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.
[0010] 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.
[0011] 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).
[0012] 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.
[0013] 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).
[0014] 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.
[0015] 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).
[0016] 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.
[0017] 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.
[0018] 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.
[0019] 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.
[0020] 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.
[0021] 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.
[0022] 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.
[0023] 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.
[0024] 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.
[0025] 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.
[0026] 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.
[0027] 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.
[0028] 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.
[0029] 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.
[0030] 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.
[0031] 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 244 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 244 (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.
[0032] 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.
[0033] 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.
[0034] 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.
[0035] 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.
[0036] 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.
[0037] 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.
[0038] 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.
[0039] 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.
[0040] 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.
[0041] 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.
[0042] 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.
[0043] 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.
[0044] 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.
[0045] 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.
[0046] 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.
[0047] 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.
[0048] 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.
[0049] 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.
[0050] Various aspects and embodiments of the present invention are defined by the following
numbered clauses:
- 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 clause 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, 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.
1. An apparatus (200) comprising:
a shell support (204) having a first member (230) and a second member (232) coupled
to an upper portion (100) of a turbine shell (26); and
an actuator (248) coupled to the shell support (204), the actuator (248) for rotating
the upper portion (100) of the turbine shell (26) to expose internal components of
a turbine system.
2. The apparatus of claim 1, wherein the shell support (204) has a first member (230)
and a second member (232) coupled to a side of the upper portion (100) of the turbine
shell (26);
3. The apparatus of claim 1 or claim 2, wherein the actuator (248) rotates the upper
portion (100) of the turbine shell (26) to a range of approximately 80 degrees and
approximately 95 degrees from horizontal.
4. The apparatus of claim 1, 2 or 3, wherein the actuator (248) is selected from the
group consisting of a mechanical ball screw actuator, a hydraulic actuator, a pneumatic
actuator, and an electric actuator.
5. The apparatus of any preceding claim, wherein the first member (230) is coupled to
a plurality of apertures on a vertical flange of the upper portion (100) of the turbine
shell (26), the plurality of apertures on the vertical flange for coupling the upper
portion (100) of the turbine shell (26) to a compressor casing during operation of
the turbine system.
6. The apparatus of any preceding claim, wherein the second member (232) is coupled to
a plurality of openings on a horizontal flange of the upper portion (100) of the turbine
shell (26), the plurality of openings on the horizontal flange for coupling the upper
portion (100) of the turbine shell (26) to a lower portion (102) of the turbine shell
(26) during operation of the turbine system.
7. The apparatus of claim 6, wherein the first member (230) and the second member (232)
are coupled to the upper portion (100) of the turbine shell (26) after the upper portion
(100) of the turbine shell (26) is positioned above and separated from the lower portion
(102) of the turbine shell (26).
8. The apparatus of claim 6 or claim 7, further comprising:
a platform (220) positioned adjacent the shell support (204);
a pivot assembly (222) coupled to the shell support (204) and the actuator (248),
the pivot assembly (222) positioned on a first surface of the platform (220); and
a securing structure (206) positioned on a second surface of the platform (220) the
securing structure (206) for substantially preventing movement of the shell support
(204) during the rotating of the upper portion (100) of the turbine shell (26).
9. The apparatus of claim 8, wherein the securing structure (206) is coupled to a support
for supporting the shell support (204) during the rotation the upper portion (100)
of the turbine shell (26).
10. The apparatus of any preceding claim, wherein the actuator (248) is operably connected
to a control system (260) configured to control the actuator (248) during the rotating
of the upper portion (100) of the turbine shell (26).
11. The apparatus of any preceding claim, wherein the actuator (248) rotates the upper
portion (100) of the turbine shell (26) to engage a support structure (258) positioned
adjacent the turbine shell (26).
12. A system comprising:
a shell rotating apparatus (200) coupled to opposing sides of an upper portion (100)
of a turbine shell (26), the shell rotating apparatus (200) including the apparatus
of any preceding claim; and
a control system (260) operably connected to the actuator (248) of the shell rotating
apparatus (200), the control system (260) configured to control the actuator (248)
during the rotating of the upper portion of the turbine shell (26).
13. The system of claim 12, further comprising a support structure (258) positioned adjacent
the shell rotating apparatus (200), the support structure (258) for supporting the
upper portion (100) of the turbine shell (26) after the rotating of the upper portion
(100) of the turbine shell (26) by the actuator (248) of the shell rotating apparatus
(200).
14. The system of claim 12 or Claim 13, wherein the actuator (248) of the shell rotating
apparatus (200) rotates the upper portion (100) of the turbine shell (26) to a range
of approximately 80 degrees and approximately 95 degrees from horizontal.