U.S. patent application number 12/827278 was filed with the patent office on 2012-01-05 for rotor assembly for use in gas turbine engines and method for assembling the same.
Invention is credited to Eugenio Yegro Segovia.
Application Number | 20120003091 12/827278 |
Document ID | / |
Family ID | 45346947 |
Filed Date | 2012-01-05 |
United States Patent
Application |
20120003091 |
Kind Code |
A1 |
Segovia; Eugenio Yegro |
January 5, 2012 |
ROTOR ASSEMBLY FOR USE IN GAS TURBINE ENGINES AND METHOD FOR
ASSEMBLING THE SAME
Abstract
A method of assembling a rotor assembly for use with a turbine
engine. The method includes providing a rotor shaft and coupling at
least one rotor disk to the rotor shaft such that a cooling path is
defined between the rotor shaft and the rotor disk. The rotor disk
includes a substantially cylindrical body that has upstream and
downstream surfaces extending between a radially inner edge and a
radially outer edge. A first cooling plate is coupled to the
downstream surface of the rotor disk to define a cooling duct
between the first cooling plate and the downstream surface. The
cooling duct is configured to channel a cooling fluid from the
cooling path to the towards the outer edge.
Inventors: |
Segovia; Eugenio Yegro;
(Madrid, ES) |
Family ID: |
45346947 |
Appl. No.: |
12/827278 |
Filed: |
June 30, 2010 |
Current U.S.
Class: |
416/95 ;
29/889.21 |
Current CPC
Class: |
F01D 5/187 20130101;
F05D 2240/81 20130101; F05D 2260/201 20130101; F05D 2260/202
20130101; F01D 25/12 20130101; F05D 2250/15 20130101; Y10T 29/49321
20150115; Y02T 50/60 20130101; Y02T 50/676 20130101; F01D 5/082
20130101 |
Class at
Publication: |
416/95 ;
29/889.21 |
International
Class: |
F01D 5/08 20060101
F01D005/08; B21K 25/00 20060101 B21K025/00 |
Claims
1. A method of assembling a rotor assembly for use with a turbine
engine, said method comprising: providing a rotor shaft; coupling
at least one rotor disk to the rotor shaft such that a cooling path
is defined between the rotor shaft and the at least one rotor disk,
the at least one rotor disk including a substantially cylindrical
body having upstream and downstream surfaces extending between a
radially inner edge and a radially outer edge; and coupling a first
cooling plate to the downstream surface of the at least one rotor
disk to define a cooling duct between the first cooling plate and
the downstream surface, the cooling duct configured to channel a
cooling fluid from the cooling path to the towards the outer
edge.
2. A method in accordance with claim 1, further comprising coupling
a plurality of vanes between the downstream surface and the first
cooling plate, each vane extends outwardly from the inner edge
towards the outer edge, adjacent vanes are spaced a circumferential
distance apart such that a cooling channel is defined between each
pair of circumferentially-spaced vanes.
3. A method in accordance with claim 1, wherein coupling a
plurality of vanes further comprises: providing each vane having an
arcuate outer surface shaped to channel fluid through each cooling
channel; and coupling each vane between the downstream surface and
the first cooling plate.
4. A method in accordance with claim 1, further comprises coupling
an inner flange to the first cooling plate, the inner flange
extending inwardly from the first cooling plate towards the rotor
shaft.
5. A method in accordance with claim 1, further comprising coupling
a second cooling plate to the upstream surface of the at least one
rotor disk such that a return air duct is defined between the
second cooling plate and the upstream surface.
6. A method in accordance with claim 5, further comprising coupling
a first rotor disk to an adjacent second rotor disk such that the
first rotor disk cooling duct is in flow communication with the
second rotor disk return air duct.
7. A rotor assembly for use with a turbine, said rotor assembly
comprising: a rotor shaft; at least one rotor disk coupled to said
rotor shaft such that a cooling path is defined between said rotor
shaft and said at least one rotor disk, said at least one rotor
disk comprises a substantially cylindrical body extending between a
radially inner edge and a radially outer edge, said body extending
generally axially between an upstream surface and a downstream
surface; and a cooling assembly coupled to said at least one rotor
disk, said cooling assembly comprising a first cooling plate
coupled to said downstream surface such that a cooling duct is
defined between said first cooling plate and said downstream
surface, said cooling duct configured to channel cooling fluid from
the cooling path towards said outer edge.
8. A rotor assembly in accordance with claim 7, wherein said
cooling assembly further comprises a plurality of vanes coupled
between said downstream surface and said first cooling plate, each
said vane extends outwardly from said inner edge towards said outer
edge, adjacent said vanes are spaced a circumferential distance
apart such that a cooling channel is defined between each said pair
of circumferentially-adjacent vanes.
9. A rotor assembly in accordance with claim 8, wherein each said
vane comprises an arcuate outer surface shaped to channel cooling
fluid through each said cooling channel.
10. A rotor assembly in accordance with claim 8, wherein each said
pair of circumferentially-spaced vanes are spaced such that said
cooling channel is defined with an inlet opening that is smaller
than an outlet opening.
11. A rotor assembly in accordance with claim 8, wherein said first
cooling plate comprises an inner flange that extends inwardly from
said first cooling plate to define an inlet opening that extends
into a cooling fluid path defined between said rotor disk inner
edge and said shaft.
12. A rotor assembly in accordance with claim 8, wherein said
cooling assembly further comprises a second cooling plate coupled
to said upstream surface such that a return air duct is defined
between said second cooling plate and said upstream surface.
13. A rotor assembly in accordance with claim 12, wherein said at
least one rotor disk comprises at least a first rotor disk coupled
to a second rotor disk, said first cooling plate is coupled to
adjacent second cooling plate such that said cooling duct is
coupled in flow communication with said return air duct.
14. A rotor assembly in accordance with claim 7, wherein said
cooling assembly further comprises at least one turbulator coupled
to said first cooling plate.
15. A turbine engine comprising: a compressor; a turbine coupled in
flow communication with said compressor to receive at least some of
the air discharged by said compressor; a rotor shaft rotatably
coupled to said turbine; at least one rotor disk coupled to said
rotor shaft such that a cooling path is defined between said rotor
shaft and said at least one rotor disk, said at least one rotor
disk comprises a substantially cylindrical body extending between a
radially inner edge and a radially outer edge, said body extending
generally axially between an upstream surface and a downstream
surface; and a cooling assembly coupled to said at least one rotor
disk, said cooling assembly comprising a first cooling plate
coupled to said downstream surface such that a cooling duct is
defined between said first cooling plate and said downstream
surface, said cooling duct configured to channel cooling fluid from
the cooling path towards said outer edge.
16. A turbine engine in accordance with claim 15, wherein said
cooling assembly further comprises a plurality of vanes coupled
between said downstream surface and said first cooling plate, each
said vane extends outwardly from said inner edge towards said outer
edge, adjacent said vanes are spaced a circumferential distance
apart such that a cooling channel is defined between each said pair
of circumferentially-adjacent vanes.
17. A turbine engine in accordance with claim 16, wherein each said
vane comprises an arcuate outer surface shaped to channel cooling
fluid through each said cooling channel.
18. A turbine engine in accordance with claim 15, wherein said
first cooling plate comprises an inner flange that extends inwardly
from said first cooling plate to define an inlet opening that
extends into a cooling fluid path defined between said rotor disk
inner edge and said shaft.
19. A turbine engine in accordance with claim 15, wherein said
cooling assembly further comprises a second cooling plate coupled
to said upstream surface such that a return air duct is defined
between said second cooling plate and said upstream surface.
20. A turbine engine in accordance with claim 19, wherein said at
least one rotor disk comprises a first rotor disk coupled to a
second rotor disk, said first cooling plate is coupled to adjacent
second cooling plate such that said cooling duct is coupled in flow
communication with said return air duct.
Description
BACKGROUND OF THE INVENTION
[0001] The embodiments described herein relate generally to gas
turbine engines, and more particularly, to a rotor assembly used
with gas turbine engines.
[0002] At least some known gas turbine engines include a combustor,
a compressor coupled downstream from the combustor, a turbine, and
a rotor assembly rotatably coupled between the compressor and the
turbine. At least some known rotor assemblies include a rotor
shaft, at least one rotor disk coupled to the rotor shaft, and a
plurality of circumferentially-spaced rotor blades or buckets
coupled to each rotor disk. Each rotor blade includes an airfoil
that extends radially outward from a rotor blade platform. At least
some known rotor blades also include a dovetail that extends
radially inward from a shank that extends between the platform and
the dovetail. The dovetail is used to mount the rotor blade within
a rotor disk. The root segments of at least some known buckets are
coupled to a rotor disk with the dovetail that is inserted within a
dovetail slot formed in the rotor disk.
[0003] Known rotor blades are hollow and include an internal
cooling cavity defined at least partially by the airfoil, platform,
shank, and dovetail. The rotating turbine blades or buckets channel
high-temperature fluids, such as combustion gases, through the
turbine. Because turbine engines typically operate at relatively
high temperatures, the airfoil portion of the rotor blades or
buckets is generally exposed to higher temperatures than the root
portion of the same airfoil. As a result, it is comment for thermal
gradients to develop and over time, continued exposure to the high
temperatures may cause the blade tips to prematurely fail. Such
failures may require replacement of the damaged turbine bucket and
require shut down of the turbine to enable repair or replacement of
the damaged blade.
[0004] As such, a rotor assembly that provides enhanced cooling of
a rotor disk and a turbine bucket could reduce maintenance costs
and extend the operational life of the rotor assembly. By extending
the operational life of the rotor assembly the operating costs of
the gas turbine engine is facilitated to be reduced.
BRIEF DESCRIPTION OF THE INVENTION
[0005] In one aspect, a method of assembling a rotor assembly for
use with a turbine engine is provided. The method includes
providing a rotor shaft and coupling at least one rotor disk to the
rotor shaft such that a cooling path is defined between the rotor
shaft and the rotor disk. The rotor disk includes a substantially
cylindrical body that has upstream and downstream surfaces
extending between a radially inner edge and a radially outer edge.
A first cooling plate is coupled to the downstream surface of the
rotor disk to define a cooling duct between the first cooling plate
and the downstream surface. The cooling duct is configured to
channel a cooling fluid from the cooling path to the towards the
outer edge.
[0006] In another aspect, a rotor assembly for use with a turbine
is provided. The rotor assembly includes a rotor shaft and at least
one rotor disk that is coupled to the rotor shaft such that a
cooling path is defined between the rotor shaft and the rotor disk.
The rotor disk includes a substantially cylindrical body that
extends between a radially inner edge and a radially outer edge.
The body extends generally axially between an upstream surface and
a downstream surface. A cooling assembly is coupled to the rotor
disk. The cooling assembly includes a first cooling plate that is
coupled to the downstream surface such that a cooling duct is
defined between the first cooling plate and the downstream surface.
The cooling duct is configured to channel cooling fluid from the
cooling path towards the outer edge.
[0007] In a further aspect, a gas turbine engine is provided. The
gas turbine engine includes a compressor and a turbine that is
coupled in flow communication with the compressor to receive at
least some of the air discharged by the compressor. A rotor shaft
is rotatably coupled to the turbine. At least one rotor disk is
coupled to the rotor shaft such that a cooling path is defined
between the rotor shaft and the rotor disk. The rotor disk includes
a substantially cylindrical body that extends between a radially
inner edge and a radially outer edge. The body extends generally
axially between an upstream surface and a downstream surface. A
cooling assembly is coupled to the rotor disk. The cooling assembly
includes a first cooling plate that is coupled to the downstream
surface such that a cooling duct is defined between the first
cooling plate and the downstream surface. The cooling duct is
configured to channel cooling fluid from the cooling path towards
the outer edge.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a schematic view of an exemplary turbine
engine.
[0009] FIG. 2 is a partial sectional view of a portion of an
exemplary rotor assembly that may be used with the gas turbine
engine shown in FIG. 1.
[0010] FIG. 3 is an enlarged partial sectional view of a portion of
the rotor assembly shown in FIG. 2.
[0011] FIG. 4 is a partial cross-sectional view of the rotor
assembly shown in FIG. 3 and taken along line 4-4.
DETAILED DESCRIPTION OF THE INVENTION
[0012] The exemplary methods and systems described herein overcome
disadvantages of known rotor assemblies by providing a rotor disk
that facilitates enhanced cooling across a surface of a rotor disk
and of a row of turbine buckets. More specifically, the embodiments
described herein provide a rotor disk that includes a cooling
assembly that channels a cooling fluid from a cooling path defined
along a rotor shaft towards the turbine buckets. In the exemplary
embodiment, the cooling assembly includes a plurality of vanes that
impart a centrifugal force to the cooling fluid to facilitate
channeling the cooling fluid radially outwardly from the rotor
shaft. The cooling fluid facilitates reducing a temperature of the
rotor disk and the turbine buckets, thus increasing the useful life
of the rotor assembly.
[0013] As used herein, the term "upstream" refers to a forward or
inlet end of a gas turbine engine, and the term "downstream" refers
to an aft or nozzle end of the gas turbine engine.
[0014] FIG. 1 is a schematic view of an exemplary turbine engine
system 10. In the exemplary embodiment, turbine engine system 10
includes an intake section 12, a compressor section 14 coupled
downstream from intake section 12, a combustor section 16 coupled
downstream from compressor section 14, a turbine section 18 coupled
downstream from combustor section 16, and an exhaust section 20.
Turbine section 18 is coupled to compressor section 14 via a rotor
shaft 22. In the exemplary embodiment, combustor section 16
includes a plurality of combustors 24. Combustor section 16 is
coupled to compressor section 14 such that each combustor 24 is
positioned in flow communication with the compressor section 14. A
fuel nozzle assembly 26 is coupled to each combustor 24. Turbine
section 18 is coupled to compressor section 14 and to a load 28
such as, but not limited to, an electrical generator and/or a
mechanical drive application. In the exemplary embodiment, each
compressor section 14 and turbine section 18 includes at least one
rotor disk assembly 30 that is coupled to rotor shaft 22 to form a
rotor assembly 32.
[0015] During operation, intake section 12 channels air towards
compressor section 14 wherein the air is compressed to a higher
pressure and temperature prior to being discharged towards
combustor section 16. The compressed air is mixed with fuel and
ignited to generate combustion gases that are channeled towards
turbine section 18. More specifically, in combustors 24, fuel, for
example, natural gas and/or fuel oil, is injected into the air
flow, and the fuel-air mixture is ignited to generate high
temperature combustion gases that are channeled towards turbine
section 18. Turbine section 18 converts the thermal energy from the
gas stream to mechanical rotational energy, as the combustion gases
impart rotational energy to turbine section 18 and to rotor
assembly 32.
[0016] FIG. 2 is a partial sectional view of a portion of an
exemplary rotor assembly 32 that may be used with turbine engine
system 10. FIG. 3 is an enlarged partial sectional view of rotor
assembly 32. Identical components shown in FIG. 3 are labeled with
the same reference numbers used in FIG. 2. In the exemplary
embodiment, turbine section 18 includes a plurality of stages 34
that each include a rotating rotor disk assembly 30 and a
stationary row of stator vanes 36. In the exemplary embodiment,
each rotor disk assembly 30 includes a plurality of turbine buckets
38 coupled to a rotor disk 40. Each rotor disk 40 is coupled to a
rotor shaft, such as rotor shaft 22. A turbine casing 42 extends
circumferentially about turbine buckets 38 and stator vanes 36,
such that stator vanes 36 are supported by casing 42.
[0017] In the exemplary embodiment, each rotor disk 40 is annular
and includes a central bore 44 that extends substantially axially
therethrough. More specifically, a disk body 46 extends radially
outwardly from central bore 44, and central bore 44 is sized to
receive rotor shaft 22 therethrough. Disk body 46 extends radially
between a radially inner edge 48 and a radially outer edge 50, and
axially from an upstream surface 52 to an opposite downstream
surface 54. Each upstream surface 52 and downstream surface 54
extends between inner edge 48 and outer edge 50. An axial support
arm 56 is coupled between adjacent rotor disks 40 to form rotor
assembly 32.
[0018] Each turbine bucket 38 is coupled to outer edge 50 of rotor
disk 40 and extends radially outwardly from disk body 46. Turbine
buckets 38 are spaced circumferentially about rotor disk 40.
Adjacent rotor disks 40 are oriented such that a gap 58 is defined
between each row 59 of circumferentially-spaced turbine buckets 38.
Gap 58 is sized to receive a row 60 of circumferentially-spaced
stator vanes 36 that each extend inwardly from turbine casing 42
towards rotor shaft 22. More specifically, stator vanes 36 are
spaced circumferentially about rotor shaft 22 and are oriented to
channel combustion gases downstream towards turbine buckets 38. A
hot gas path 61 is defined between turbine casing 42 and each rotor
disk 40. Each row 59 and 60 of turbine buckets 38 and stator vanes
36 extends at least partially through a portion of hot gas path
61.
[0019] In the exemplary embodiment, each turbine bucket 38 extends
radially outwardly from rotor disk 40 and includes an airfoil 62, a
platform 64, a shank 66, and a dovetail 68. Platform 64 extends
between airfoil 62 and shank 66 such that each airfoil 62 extends
radially outwardly from platform 64 towards turbine casing 42.
Shank 66 extends radially inwardly from platform 64 to dovetail 68.
Dovetail 68 extends radially inwardly from shank 66 and enables
turbine buckets 38 to be securely coupled to rotor disk 40. A shank
sidewall 70 extends between a forward cover plate 72 and an aft
cover plate 74. Shank sidewall 70 is recessed with respect to
forward cover plate 72 and aft cover plate 74, such that when
turbine buckets 38 are coupled to rotor disk 40, a shank cavity 76
is defined between circumferentially-adjacent shank sidewalls 70.
In one embodiment, an annular passage 78 is defined through shank
66 and dovetail 68 and extends from rotor disk 40 to platform 64.
Passage 78 enables a flow of cooling fluid to be channeled from
rotor disk outer edge 50 towards platform 64. In the exemplary
embodiment, a forward angel wing 80 extends outwardly from forward
cover plate 72 to facilitate sealing a forward buffer cavity 82
defined between rotor disk upstream surface 52 and stator vane 36.
An aft angel wing 84 extends outwardly from aft cover plate 74 to
facilitate sealing an aft buffer cavity 86 defined between rotor
disk downstream surface 54 and stator vane 36. In the exemplary
embodiment, a forward lower angel wing 88 extends outwardly from
forward cover plate 72 to facilitate sealing between turbine bucket
38 and rotor disk 40. More specifically, forward lower angel wing
88 is positioned between dovetail 68 and forward angel wing 80.
[0020] Rotor disk inner edge 48 is spaced at a distance radially
outwardly from rotor shaft 22 such that a gap 90 is defined between
an outer surface 92 of rotor shaft 22 and inner edge 48. Rotor
disks 40 are coupled together such that a cooling flow path 94 is
defined between rotor shaft 22 and each rotor disk 40. Cooling flow
path 94 is configured to facilitate channeling a flow of cooling
fluid 96 from compressor section 14 through turbine section 18. A
cooling assembly 100 is coupled to at least one rotor disk 40 for
use in channeling cooling fluid from cooling flow path 94 towards
turbine buckets 38. More specifically, in the exemplary embodiment,
cooling assembly 100 channels cooling fluid 96 from rotor disk
inner edge 48 towards outer edge 50.
[0021] In the exemplary embodiment, cooling assembly 100 includes a
first cooling plate 102 and a second cooling plate 104. First
cooling plate 102 is coupled to rotor disk downstream surface 54,
and second cooling plate is coupled to rotor disk upstream surface
52. First cooling plate 102 includes a first cooling disk 106
extending between an inner portion 108 and a radially outer portion
110. First cooling disk 106 includes a bore 111 defined by inner
portion 108. Bore 111 is sized to receive rotor shaft 22. In the
exemplary embodiment, first cooling disk 106 extends from inner
edge 48 to outer edge 50 across downstream surface 54 and is spaced
a distance d.sub.1 from rotor disk 40 such that a cooling duct 112
is defined between an inner surface 114 of first cooling disk 106
and rotor disk downstream surface 54. An inlet opening 116 is
defined between rotor disk downstream surface 54 and inner portion
108, and an outlet opening 118 is defined between downstream
surface 54 and outer portion 110. In the exemplary embodiment,
cooling duct 112 extends between inlet openings 116 and 118 for use
in channeling cooling fluid 96 from inlet opening 116 through
outlet opening 118. Inlet opening 116 enables cooling fluid 96 to
be channeled into cooling duct 112 from cooling flow path 94. First
cooling disk 106 is oriented substantially parallel with rotor disk
downstream surface 54 such that cooling duct 112 has a
substantially uniform width w from inner portion 108 to outer
portion 110. In the exemplary embodiment, inner portion 108
substantially circumscribes rotor shaft outer surface 92 and is
spaced a distance d.sub.2 radially from outer surface 92 such that
at least a portion of cooling flow path 94 is defined between first
cooling plate 102 and rotor shaft 22. First cooling plate 102
channels at least a portion of cooling fluid 96 from cooling flow
path 94 through cooling duct 112 towards rotor disk outer edge 50
to facilitate cooling of rotor disk 40 and each turbine buckets 38.
In one embodiment, a flange 120 extends radially inwardly from
inner portion 108 towards rotor shaft 22.
[0022] In the exemplary embodiment, a plurality of vanes 122 are
coupled between rotor disk 40 and first cooling disk 106. Vanes 122
are circumferentially-spaced and each extends between disk inner
portion 108 and outer portion 110. Vanes 122 impart a centrifugal
force upon cooling fluid 96 entering inlet opening 116 of cooling
duct 112. Cooling duct 112 channels cooling fluid 96 from inlet
opening 116 to outlet opening 118. Inlet opening 116 is defined
between a pair of circumferentially-adjacent vanes 122. More
specifically, in the exemplary embodiment, inlet openings 116 are
adjacent to inner portion 108. Outlet openings 118 are defined
between adjacent vanes 122 such that each outlet opening 118 is
adjacent to outer portion 110.
[0023] Cooling plate 104 is coupled to rotor disk 40 and is spaced
at a distance d.sub.3 from upstream surface 52 such that a return
air duct 124 is defined between cooling plate 104 and upstream
surface 52. In the exemplary embodiment, cooling plate 104 includes
a second cooling disk 126. Second cooling disk 126 includes an
inner portion 128 and a radially outer portion 130. A bore 131 is
defined by inner portion 128 that is sized to receive rotor shaft
22. Outer portion 130 is positioned adjacent to rotor disk outer
edge 50. Inner portion 128 circumscribes rotor shaft 22. Rotor disk
inner edge 48 is positioned closer to outer surface 92 than inner
portion 128. Return air duct 124 extends between a return air inlet
opening 132 and a return air outlet opening 134. Return air inlet
opening 132 is defined between outer portion 130 and upstream
surface 52. Return air outlet opening 134 is defined between inner
portion 128 and upstream surface 52. Return air duct 124 enables
cooling fluid 96 to be channeled from rotor disk outer edge 50 to
cooling flow path 94.
[0024] In the exemplary embodiment, cooling assembly 100 includes
an upper cooling flange 136 that extends between cooling plates 102
and 104 such that cooling duct 112 is coupled in flow communication
with return air duct 124. A channel 138 is defined between cooling
plate outer portion 110 and cooling plate outer portion 130.
Channel 138 forms a portion of a cooling circuit 140 for use in
channeling cooling fluid 96 from cooling duct 112 to return air
duct 124.
[0025] During operation, compressor section 14 (shown in FIG. 1)
compresses air and discharges compressed air into combustor section
16 (shown in FIG. 1) and towards turbine section 18. The majority
of air discharged from compressor section 14 is channeled towards
combustor section 16, and a smaller portion of air discharged from
compressor section 14 is channeled downstream towards turbine
section 18 for use in cooling rotor assembly 32. More specifically,
a first flow leg 142 of pressurized compressed air is channeled to
combustors 24 (shown in FIG. 1) wherein the air is mixed with fuel
and ignited to generate high temperature combustion gases 142. The
combustion gases 142 are channeled towards hot gas path 61, wherein
the gases 142 impinge upon turbine buckets 38 and stator vanes 36
to facilitate imparting a rotational force on rotor assembly 32.
Compressed air also enters a second flow leg 144 for use as cooling
fluid 96. Air discharged from flow leg 144 is channeled into
cooling flow path 94 between rotor shaft 22 and rotor disks 40. As
rotor assembly 32 rotates, cooling assembly 100 directs at least a
portion of air discharged from flow leg 144 outwardly from cooling
flow path 94 through each cooling duct 112 towards rotor disk outer
edge 50.
[0026] FIG. 4 is a partial cross-sectional view of rotor assembly
32 along sectional line 4-4. Identical components shown in FIG. 4
are labeled with the same reference numbers used in FIG. 2 and FIG.
3. In the exemplary embodiment, vanes 122 extend between inner
portion 108 and outer portion 110 of first cooling plate 102. An
inlet edge 150 of each vane 122 is spaced circumferentially about
bore 111 defined by inner portion 108. Bore 111 is sized to receive
rotor shaft 22 therein such that cooling flow path 94 is defined
circumferentially between rotor shaft 22 and first cooling plate
102. Each vane 122 includes a pressure side 152 and an opposing
suction side 154. Each pressure side 152 and suction side 154
extends between inlet edge 150 and an outlet edge 156. Each pair of
circumferentially-spaced adjacent vanes 122 are spaced such that a
cooling channel 158 is defined between inlet opening 116 and outlet
opening 118. Each cooling channel 158 is further defined between
first cooling disk 106 and downstream surface 54 (shown in FIG. 2).
Each inlet opening 116 extends between a pressure side 152 and an
adjacent suction side 154 of vane 122 at inlet edge 150. Each
outlet opening 118 extends between pressure side 152 and an
adjacent suction side 154 at outlet edge 156. Inlet opening 116 has
a first width 160 that is smaller than a second width 162 of outlet
opening 118. Each vane 122 is formed with an arcuate shape and is
oriented such that cooling channel 158 is defined with a spiral
shape that diverges outwardly from inner portion 108 towards outer
portion 110. In one embodiment, a plurality of turbulators 164,
such as fins and/or ribs, are coupled to downstream surface 54
and/or to first cooling disk 106 within cooling channel 158, to
facilitate a heat transfer from rotor disk 40 to cooling fluid
96.
[0027] During operation, cooling fluid 96 is channeled into cooling
channels 158 through each inlet opening 116. As cooling fluid 96
enters inlet openings 116, a rotation of rotor assembly 32 causes
vanes 122 impart a centrifugal force to cooling fluid 96, such that
a pressure of cooling fluid 96 within each cooling channel 158 is
increased. As the centrifugal force acts upon cooling fluid 96, a
differential pressure within cooling fluid 96 is created between
inlet opening 116 and outlet opening 118. Cooling channels 158
discharge cooling fluid 96 outwardly from inlet opening 116 to
outlet opening 118. Cooling fluid 96 facilitates convectively
cooling rotor disk 40 as the fluid 96 is channeled across
downstream surface 54. Cooling fluid 96 impinges against support
arm 56 to facilitate cooling of rotor disk outer edge 50 and
support arm 56. In one embodiment, at least a portion of cooling
fluid 96 is channeled into each bucket passage 78 to facilitate
cooling shanks 66 and platforms 64.
[0028] The above-described rotor assembly facilitates reducing an
operating temperature of a gas turbine. More specifically, by
providing a rotor assembly having a cooling assembly coupled to an
outer surface of a rotor disk, a cooling fluid is channeled
radially outwardly from a rotor shaft towards a turbine bucket to
facilitate cooling the rotor assembly. In addition, by assembling a
cooling assembly that includes a plurality of cooling channels, a
centrifugal force generated by a rotation of the rotor assembly
facilitates channeling cooling fluid through the cooling channels
to reduce an operating temperature of the rotor assembly. Moreover,
by providing a rotor assembly having a cooling assembly, the
cooling of a rotor disk is increased over known rotor assemblies
that do not channel cooling fluid from the rotor shaft towards the
turbine buckets. As such, the cost of maintaining the gas turbine
engine system is facilitated to be reduced.
[0029] Exemplary embodiments of a rotor assembly for use in a gas
turbine engine and method for assembling the same are described
above in detail. The methods and apparatus are not limited to the
specific embodiments described herein, but rather, components of
systems and/or steps of the method may be utilized independently
and separately from other components and/or steps described herein.
For example, the methods and apparatus may also be used in
combination with other combustion systems and methods, and are not
limited to practice with only the gas turbine engine assembly as
described herein. Rather, the exemplary embodiment can be
implemented and utilized in connection with many other combustion
system applications.
[0030] Although specific features of various embodiments of the
invention may be shown in some drawings and not in others, this is
for convenience only. Moreover, references to "one embodiment" in
the above description are not intended to be interpreted as
excluding the existence of additional embodiments that also
incorporate the recited features. In accordance with the principles
of the invention, any feature of a drawing may be referenced and/or
claimed in combination with any feature of any other drawing.
[0031] 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.
* * * * *