U.S. patent application number 12/952922 was filed with the patent office on 2012-05-24 for turbomachine nozzle segment having an integrated diaphragm.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to Glen Arthur MacMillan, Charles Andrew Malinowski, Frederic Woodrow Roberts, JR., Anshuman Singh.
Application Number | 20120128472 12/952922 |
Document ID | / |
Family ID | 46026211 |
Filed Date | 2012-05-24 |
United States Patent
Application |
20120128472 |
Kind Code |
A1 |
Singh; Anshuman ; et
al. |
May 24, 2012 |
TURBOMACHINE NOZZLE SEGMENT HAVING AN INTEGRATED DIAPHRAGM
Abstract
A turbomachine nozzle segment includes a vane having a first end
extending to a second end through an airfoil portion. An outer
member is positioned at the first end of the vane. The outer member
includes a mounting element configured and disposed to secure the
turbomachine nozzle segment to a turbomachine. An inner member is
positioned at the second end of the vane. The inner member includes
an upstream section and a downstream section. An upstream diaphragm
member extends substantially radially outwardly from the inner
member at the upstream section, and a downstream diaphragm member
extends substantially radially outwardly from the inner member at
the downstream section. Each of the upstream diaphragm member and
down stream member includes an outer surface and an inner surface.
One of the outer surface and inner surface of each of the upstream
diaphragm member and downstream diaphragm member includes a
cartridge mounting member.
Inventors: |
Singh; Anshuman;
(Simpsonville, SC) ; MacMillan; Glen Arthur;
(Simpsonville, SC) ; Malinowski; Charles Andrew;
(Mauldin, SC) ; Roberts, JR.; Frederic Woodrow;
(Simpsonville, SC) |
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
46026211 |
Appl. No.: |
12/952922 |
Filed: |
November 23, 2010 |
Current U.S.
Class: |
415/178 ;
415/202 |
Current CPC
Class: |
F01D 9/041 20130101;
F01D 25/246 20130101 |
Class at
Publication: |
415/178 ;
415/202 |
International
Class: |
F01D 1/02 20060101
F01D001/02; F01D 25/12 20060101 F01D025/12 |
Claims
1. A turbomachine nozzle segment comprising: a vane including a
first end extending to a second end through an airfoil portion; an
outer member positioned at the first end of the vane, the outer
member including a mounting element configured and disposed to
secure the turbomachine nozzle segment to a turbomachine; and an
inner member positioned at the second end of the vane, the inner
member including an upstream section and a downstream section, an
upstream diaphragm member extends substantially radially outwardly
from the inner member at the upstream section, and a downstream
diaphragm member extends substantially radially outwardly from the
inner member at the downstream section, each of the upstream
diaphragm member and down stream member including an outer surface
and an inner surface, one of the outer surface and inner surface of
each of the upstream diaphragm member and downstream diaphragm
member including a cartridge mounting member.
2. The turbomachine nozzle according to claim 1, wherein the
cartridge mounting member is formed on the inner surface of each of
the upstream and downstream diaphragm members.
3. The turbomachine nozzle according to claim 1, further
comprising: a nozzle cartridge positioned between the upstream and
downstream diaphragm members and coupled to the cartridge mounting
member, the nozzle cartridge including a main body extending
between an upstream end and a downstream end, the nozzle cartridge
forming a region defined by the inner member, and the upstream and
downstream diaphragm members.
4. The turbomachine nozzle according to claim 3, wherein the nozzle
cartridge includes at least one side portion having a dogleg
section.
5. The turbomachine nozzle according to claim 4, wherein the inner
surface of the nozzle cartridge includes a cartridge mounting
element, the cartridge mounting element being configured and
disposed to engage with the cartridge mounting member on
corresponding ones of the upstream and downstream diaphragm
members.
6. The turbomachine nozzle according to claim 3, wherein the main
body of the nozzle cartridge includes a substantially linear
cross-section extending between the upstream end and the downstream
end.
7. The turbomachine nozzle according to claim 3, wherein the main
body of the nozzle cartridge includes a generally curvilinear
circumferential profile.
8. The turbomachine nozzle according to claim 3, wherein the
upstream diaphragm member includes a seal groove element, the
downstream diaphragm member includes a seal groove member, and the
nozzle cartridge includes seal groove portion, the seal groove
portion linking with the seal groove member and seal groove
element.
9. The turbomachine nozzle according to claim 1, further
comprising: a discourager seal provided on the outer surface of
each of the upstream and downstream diaphragm members.
10. The turbomachine nozzle according to claim 1, wherein the inner
member includes a curvilinear circumferential profile, the
curvilinear circumferential profile comprising about 22.5.degree.
of an overall circumferential circumference of a turbomachine
nozzle assembly.
11. The turbomachine nozzle according to claim 1, wherein the inner
member includes a dogleg section.
12. A turbomachine nozzle cartridge comprising: a main body having
an outer surface and an inner surface that extend between an
upstream end and a downstream end, the nozzle cartridge being
configured and disposed to be mounted between an upstream diaphragm
member and a downstream diaphragm member of a turbomachine
nozzle.
13. The turbomachine nozzle cartridge according to claim 12,
wherein the inner surface of the nozzle cartridge includes a
cartridge mounting element, the cartridge mounting element being
configured and disposed to engage with a cartridge mounting member
on corresponding ones of upstream and downstream diaphragm members
of a turbomachine nozzle.
14. The turbomachine nozzle cartridge according to claim 12,
wherein the nozzle cartridge includes at least one side portion
having a dogleg section.
15. The turbomachine nozzle cartridge according to claim 14,
further comprising: a seal grove portion formed in the at least one
side portion.
16. The turbomachine nozzle cartridge according to claim 12,
further comprising: a first mounting flange arranged at the
upstream end and a second mounting flange arranged at the
downstream end, each of the first and second mounting flanges
extending substantially radially outwardly from the main body.
17. The turbomachine nozzle cartridge according to claim 12,
wherein the main body of the nozzle cartridge includes a
substantially linear cross-section extending between the upstream
end and the downstream end.
18. The turbomachine nozzle cartridge according to claim 12,
wherein the main body of the nozzle cartridge includes a generally
curvilinear circumferential profile.
19. The turbomachine nozzle cartridge according to claim 17,
wherein the generally curvilinear circumferential profile
comprising about 22.5.degree. of an overall circumferential
circumference of a turbomachine nozzle assembly.
20. A turbomachine comprising: a compressor section; a turbine
section operatively connected to the compressor section; and a
turbine nozzle positioned within the turbine section, the turbine
nozzle including: a vane including a first end extending to a
second end through an airfoil portion; an outer member positioned
at the first end of the vane, the outer member including a mounting
element configured and disposed to secure the turbomachine nozzle
to a turbomachine; an inner member positioned at the second end of
the vane, the inner member including an upstream section and a
downstream section, an upstream diaphragm member extends
substantially radially outwardly from the inner member at the
upstream section, and a downstream diaphragm member extends
substantially radially outwardly from the inner member at the
downstream section, each of the upstream diaphragm member and down
stream member including an outer surface and an inner surface, one
of the outer surface and inner surface of each of the upstream
diaphragm member and downstream diaphragm member including a
cartridge mounting member; a cooling passage extending from the
outer member through the airfoil portion to the inner member; and a
nozzle cartridge including a main body having an outer surface and
an inner surface that extend between an upstream end and a
downstream end, the nozzle cartridge is mounted between the
upstream diaphragm member and the downstream diaphragm member of a
turbomachine nozzle.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to the art of
turbomachines and, more particularly, to a turbomachine nozzle
segment having an integrated diaphragm.
[0002] In general, gas turbomachines combust a fuel/air mixture
that releases heat energy to form a high temperature gas stream.
The high temperature gas stream is channeled to a turbine section
via a hot gas path. In the turbine, the high temperature gas stream
passes through a plurality of stages. Each stage includes a
plurality of nozzles arranged upstream from a plurality of turbine
blades. The high temperature gas stream passes over the nozzles,
then acts upon or rotates the turbine blades. The plurality of
nozzles are mounted to a housing of the turbine section and a
diaphragm is mounted to each of the plurality of nozzles. A
discourager seal is provided at an interface between each of the
plurality of nozzles and the associated diaphragm. The discourager
seals on each of the plurality of nozzles interact one with the
other to reduce loss of the high temperature gases or working fluid
from the corresponding one of the plurality of stages of the
turbine section. The turbine blades convert thermal energy from the
high temperature gas stream to mechanical energy that rotates a
turbine shaft. The turbine may be used in a variety of applications
such as providing power to a pump or an electrical generator.
BRIEF DESCRIPTION OF THE INVENTION
[0003] According to one aspect of the invention, a turbomachine
nozzle segment includes a vane having a first end extending to a
second end through an airfoil portion. An outer member is
positioned at the first end of the vane. The outer member includes
a mounting element configured and disposed to secure the
turbomachine nozzle segment to a turbomachine. An inner member is
positioned at the second end of the vane. The inner member includes
an upstream section and a downstream section. An upstream diaphragm
member extends substantially radially outwardly from the inner
member at the upstream section, and a downstream diaphragm member
extends substantially radially outwardly from the inner member at
the downstream section. Each of the upstream diaphragm member and
down stream member includes an outer surface and an inner surface.
One of the outer surface and inner surface of each of the upstream
diaphragm member and downstream diaphragm member includes a
cartridge mounting member.
[0004] According to another aspect of the invention, a turbomachine
nozzle cartridge includes a main body having an outer surface and
an inner surface that extend between an upstream end and a
downstream end. The nozzle cartridge is configured and disposed to
be mounted between an upstream diaphragm member and a downstream
diaphragm member of a turbomachine nozzle.
[0005] According to yet another aspect of the invention, a
turbomachine includes a compressor section, a turbine section
operatively connected to the compressor section, and a turbine
nozzle positioned within the turbine section. The turbine nozzle
includes a vane having a first end extending to a second end
through an airfoil portion. An outer member is positioned at the
first end of the vane. The outer member includes a mounting element
configured and disposed to secure the turbomachine nozzle to a
turbomachine. An inner member is positioned at the second end of
the vane. The inner member includes an upstream section and a
downstream section. An upstream diaphragm member extends
substantially radially outwardly from the inner member at the
upstream section, and a downstream diaphragm member extends
substantially radially outwardly from the inner member at the
downstream section. Each of the upstream diaphragm member and down
stream member includes an outer surface and an inner surface. One
of the outer surface and inner surface of each of the upstream
diaphragm member and downstream diaphragm member includes a
cartridge mounting member. A cooling passage extends from the outer
member through the airfoil portion to the inner member. A nozzle
cartridge includes a main body having an outer surface and an inner
surface that extend between an upstream end and a downstream end.
The nozzle cartridge is mounted between the upstream diaphragm
member and the downstream diaphragm member of a turbomachine
nozzle.
[0006] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF THE DRAWING
[0007] The subject matter, which is regarded as the invention, is
particularly pointed out and distinctly claimed in the claims at
the conclusion of the specification. The foregoing and other
features, and advantages of the invention are apparent from the
following detailed description taken in conjunction with the
accompanying drawings in which:
[0008] FIG. 1 is a partial cross-sectional side view of a turbine
section of a turbomachine including a plurality of turbine nozzles
having an integrated diaphragm members in accordance with an
exemplary embodiment;
[0009] FIG. 2 is a perspective view of a nozzle segment including
integrated upstream and downstream diaphragm members of the turbine
section of FIG. 1;
[0010] FIG. 3 is a perspective view of an inner member of the
nozzle segment of FIG. 2;
[0011] FIG. 4 is a perspective view of the nozzle segment of FIG. 2
including a nozzle cartridge in accordance with an exemplary
embodiment; and
[0012] FIG. 5 is a perspective view of an inner member of a nozzle
segment joined to a nozzle cartridge in accordance with another
exemplary embodiment.
[0013] The detailed description explains embodiments of the
invention, together with advantages and features, by way of example
with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0014] Referring to FIG. 1, a turbomachine, in accordance with an
exemplary embodiment, is indicated generally at 2. Turbomachine 2
includes a turbine section 3 having a housing 4 that defines, at
least in part, a hot gas path 10. Turbine section 3 includes a
first stage 12, having a plurality of first stage vanes or nozzles
14, and blades 16; a second stage 17 having a plurality of second
stage vanes or nozzles 18 and blades 20; and a third stage 21
having a plurality of third stage vanes or nozzles 22 and blades
24. Of course it should be understood that turbine section 3 could
also include additional stages (not shown). Hot combustion gases
flow axially along hot gas path 10 through nozzles 14, 18, and 22,
impact and rotate blades 16, 20, and 24. In addition, a cooling
airflow is guided into turbine section 3 in order to mitigate
thermal fluxes that develop between portions of nozzles 14, 18, and
22.
[0015] Reference will now be made to FIGS. 2-4 in describing a
nozzle segment 30 of second stage 17 in accordance with an
exemplary embodiment. Nozzle segment 30 includes a plurality of
second stage nozzles or airfoils 18, 18a, and 18b. As each airfoil
18, 18a, and 18b is similarly formed, a detailed description will
follow referencing airfoil 18 with an understanding that airfoil
18a and 18b include similar structure. Airfoil 18 includes a first
end 34 that extends to a second end 35 through an intermediate or
airfoil portion 36. Nozzle segment 30 includes an outer member 40
integrally formed with airfoils 18, 18a, and 18b at first end 34.
Outer member 40 supports nozzle segment 30 from a casing portion
(not separately labeled) of turbomachine 2 and includes a main body
42 having a first circumferential edge 46 and an opposing second
circumferential edge 47. First and second circumferential edges 46
and 47 establish a circumferential profile 50 for outer member 40.
In the exemplary embodiment shown, circumferential profile 50 is
about 22.5.degree. of an overall circumference of second stage 17.
Each circumferential edge 46 and 47 includes a corresponding angled
or dogleg section 48 and 49.
[0016] Nozzle segment 30 also includes an inner member 60
integrally formed at second end 35 of airfoils 18, 18a, and 18b.
Inner member 60 includes a main body 64 having an upstream section
67 and a downstream section 69. Main body 64 also includes a first
circumferential edge 72 and a second, opposing, circumferential
edge 73 that establish a circumferential profile 75 for inner
member 60. In a manner similar to that described above, in the
exemplary embodiment shown, circumferential profile 75 is about
22.5.degree. of an overall circumference of second stage 17. Each
circumferential edge 72 and 73 includes a corresponding angled or
dogleg section 79 and 80. Each circumferential edge 72 and 73 is
also provided with a seal slot or groove 81 and 82 respectively. At
this point it should be understood that the term "inner" refers to
a portion of nozzle segment 30 that is positioned near a centerline
of turbomachine 2. The term "outer" refers to a portion of nozzle
segment 30 that is positioned away from the centerline in a
direction of a casing of turbomachines 2.
[0017] In accordance with the exemplary embodiment, inner member 60
includes an upstream diaphragm member 84 and a downstream diaphragm
member 86. Upstream diaphragm member 84 is integrally formed with
inner member 60 and extends generally radially outwardly from
upstream section 67 between first and second circumferential edges
72 and 73. Similarly, downstream diaphragm member 86 is integrally
formed with inner member 60 and extends generally radially
outwardly from downstream section 69 between first and second
circumferential edges 72 and 73. Upstream diaphragm member 84
includes a first end 90 that extends from upstream section 67 to a
second end 91. Second end 91 includes a generally curvilinear
circumferential profile (not separately labeled). Upstream
diaphragm member 84 also includes an outer surface 93 and an inner
surface 94 (FIG. 3) that extend between first and second ends 90
and 91. A first seal groove element 95 is formed in upstream
diaphragm member 84 at circumferential edge 73. First seal groove
element joins with seal groove 82. A second seal groove element 96
is formed in upstream diaphragm member 84 at circumferential edge
72. Second seal groove element 96 is linked with seal groove 81.
Similarly, downstream diaphragm member 86 includes a first end 97
that extends from downstream section 69 to a second end 98. Second
end 98 includes a generally curvilinear circumferential profile
(not separately labeled). Downstream diaphragm member 86 also
includes an outer surface 100 and an inner surface 101 that extend
between first and second ends 97 and 98. A first seal groove member
102 is formed in downstream diaphragm member 86 at circumferential
edge 73. First seal groove member 102 joins with seal groove 82. A
second seal groove member 103 is formed in downstream diaphragm
member 86 at circumferential edge 72. Second seal groove member 103
is linked with seal groove 81.
[0018] Upstream diaphragm member 84 and downstream diaphragm member
86 are also shown to include discourager seals 104 and 105 provided
on outer surfaces 93 and 100 respectively. Discourager seals 104
and 105 can either be integrally formed on corresponding ones of
outer surfaces 93 and 100 or may be mounted in grooves or other
structure (not shown) provided on corresponding ones of outer
surfaces 93 and 100. In addition, upstream diaphragm member 84 and
downstream diaphragm member 86 are also shown to include cartridge
mounting members 110 and 112 provided on corresponding ones of
inner surfaces 94 and 101. As will be discussed more fully below,
cartridge mounting members 110 and 112 provide an interface for
additional sealing structure for nozzle segment 30. Nozzle segment
30 is also shown to include a plurality of passages 118-120 that
deliver cooling fluid flow, in the form of compressor discharge
air, through airfoils 18, 18a, and 18b respectively. Passages
118-120 lead though airfoils 18, 18a, and 18b into a region 121
that extends between upstream diaphragm member 84 and downstream
diaphragm member 86. Region 121 receives extraction air through a
plurality of cooling passages 118-120 that extend through airfoils
18, 18a, and 18b, and is pushed out through openings 122-124 that
are formed in upstream diaphragm member 84. At this point it should
be understood that various other cooling scheme, including the use
of cooling tubes or conduits that extend from upstream diaphragm
member 84, through airfoils 18, 18a, and 18b, and to a casing of
turbomachine 2 could also be employed
[0019] In further accordance with the exemplary embodiment, nozzle
segment 30 includes a nozzle cartridge 136 (FIG. 4) that is
detachably mounted to inner member 60. Nozzle cartridge 136
provides a seal that limits leakage flow from passing between
nozzle segment 30 and a wheel space (not separately labeled) of
turbine section 3. Nozzle cartridge 136 includes a main body 139
having a substantially linear cross-section and a substantially
curvilinear circumferential profile. In a manner similar to that
described above, in the exemplary embodiment shown, the
circumferential profile is about 22.5.degree. of an overall
circumference of second stage 17. Nozzle cartridge 136 is shown to
include a main body 139 having an upstream end 141 and a downstream
end 142. Main body 139 also includes an outer surface 144, an inner
surface 145, a first side portion 146 and a second side portion
(not shown). Side portion 146 includes an angled or dogleg portion
147 on side portion corresponds to dogleg sections 80 on inner
member 60. The second side portion (not shown) includes a similar
angled or dogleg portion (also not shown). Side portion 146 is also
shown to include a seal groove portion 148 that links with first
seal groove element 95 and first seal groove member 102 to form a
seal zone (not separately labeled) that prevents leakage flow from
passing between adjacent nozzle cartridges.
[0020] As best shown in FIG. 4, nozzle cartridge 136 defines a
region 148 in inner member 60. In a manner similar to that
described above, region 148 is an encapsulated region
defined/bounded by upstream diaphragm member 84, downstream
diaphragm member 86 and nozzle cartridge 136. Region 148 channels
extraction air passing through airfoils 18, 18a, and 18b to provide
cooling to the wheel space. Nozzle cartridge 136 includes a
plurality of projections, one of which is indicated at 150 that
define a labyrinth seal which limits leakage flow across stages 17,
and 21. Nozzle cartridge 136 is further shown to include first
cartridge mounting element 152 provided on upstream end 141 and a
second cartridge mounting element 154 provided on downstream end
142. First and second cartridge mounting elements 152 and 154
engage with first and second cartridge mounting members 110 and 112
on inner member 60 to secure nozzle cartridge 136 to nozzle segment
30
[0021] Reference will now be made to FIG. 5 in describing a nozzle
segment 180 in accordance with another aspect of the exemplary
embodiment. Nozzle segment 180 includes a plurality of airfoils,
one of which is indicated at 183 that extend between an outer
member (not shown) and an inner member 190. Inner member 190
includes a main body 193 having an upstream section 195 and a
downstream section 196. Main body 193 also includes a first
circumferential edge (not shown) that extends to a second
circumferential edge 198 to define a circumferential profile 200.
In a manner similar to that described above, in the exemplary
embodiment shown, circumferential profile 200 is about 22.5.degree.
of an overall circumference of second stage 12. In a manner also
similar to that described above circumferential edge 198 includes
an angled or dogleg section 202.
[0022] An upstream diaphragm member 205 is integrally formed with
inner member 190 and extends generally radially outwardly from
upstream section 195. Similarly, a downstream diaphragm member 207
is also integrally formed with inner member 190 and extends
generally radially outwardly from downstream section. Upstream
diaphragm member 205 includes a first end 211 that extends from
upstream section 195 to a second end 212. Second end 212 includes a
generally curvilinear circumferential profile (not shown). Upstream
diaphragm member 205 also includes an outer surface 214 and an
inner surface 215 that extend between first and second ends 211 and
212. Similarly, downstream diaphragm member 207 includes a first
end 219 that extends from downstream section 196 to a second end
220. Second end 220 includes a generally curvilinear
circumferential profile (not shown). Downstream diaphragm member
207 also includes an outer surface 222 and an inner surface 223
that extend between first and second ends 219 and 220. A first
discourager seal 225 is provided on outer surface 214 of upstream
diaphragm member 205 and a second discourager seal 226 is provided
on outer surface 222 of downstream diaphragm member 207. Inner
member 190 is also shown to include a first cartridge mounting
member 228 that is provided on outer surface 214 of upstream
diaphragm member 205 and a second cartridge mounting member 230
provided on outer surface 222 of downstream diaphragm member
207.
[0023] In further accordance with the exemplary aspect depicted in
FIG. 5, a nozzle cartridge 240 is mounted to inner member 190.
Nozzle cartridge 240 includes a main body 243 having an upstream
end 245 and a downstream end 246 that are separated by an outer
surface 248 and an inner surface 249. Cartridge 240 also includes a
first side portion 250 and a second side portion (not shown). Each
of the first and second side portions includes an angled or dogleg
section, one of which is shown at 251 on side portion 250 that
corresponds to dogleg section 202 on inner member 190. A first
mounting flange 252 extends from upstream end 245 and a second
mounting flange 253 extends from downstream end 246. Each mounting
flange 252, 253 includes a corresponding cartridge mounting element
255 and 257. Cartridge mounting elements 255 and 257 cooperate with
cartridge mounting members 228 and 230 on inner member 190. With
this arrangement, mounting flanges 252 and 253 wrap around outer
surfaces 214 and 222 of upstream diaphragm member 205 and
downstream diaphragm member 207 respectively. Once in place, nozzle
cartridge 240 forms a cavity 260 in inner member 190.
[0024] At this point it should be appreciated that the exemplary
embodiments provide a nozzle segment having an integrated diaphragm
that reduces leakage points and simplifies construction by reducing
or even eliminating numerous welded joints. In addition the
particular construction of the nozzle segment eliminates load
sharing with adjacent nozzle segments. The integrated diaphragm
eliminates numerous diaphragm machining operations saving
time/labor/costs associated with forming and installing nozzles in
a turbomachine. The exemplary embodiments are further shown to
reduce both known and unknown leakages thereby enhancing
turbomachine efficiency. Finally, it should be understood that the
particular nozzle segment shown is exemplary, the number of vanes
as well as the materials used may vary.
[0025] While the invention has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the invention is not limited to such
disclosed embodiments. Rather, the invention can be modified to
incorporate any number of variations, alterations, substitutions or
equivalent arrangements not heretofore described, but which are
commensurate with the spirit and scope of the invention.
Additionally, while various embodiments of the invention have been
described, it is to be understood that aspects of the invention may
include only some of the described embodiments. Accordingly, the
invention is not to be seen as limited by the foregoing
description, but is only limited by the scope of the appended
claims.
* * * * *