U.S. patent application number 13/216297 was filed with the patent office on 2013-02-28 for turbine nozzle vane retention system.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is Thomas J. Brunt, Robert W. Coign. Invention is credited to Thomas J. Brunt, Robert W. Coign.
Application Number | 20130052024 13/216297 |
Document ID | / |
Family ID | 46826241 |
Filed Date | 2013-02-28 |
United States Patent
Application |
20130052024 |
Kind Code |
A1 |
Brunt; Thomas J. ; et
al. |
February 28, 2013 |
Turbine Nozzle Vane Retention System
Abstract
The present application provides a turbine nozzle vane retention
system. The turbine nozzle vane retention system may include a
number of nozzles with a platform, a slot extending into the
platform, and a pin extending between the slot of a first nozzle
and the slot of a second nozzle,
Inventors: |
Brunt; Thomas J.;
(Greenville, SC) ; Coign; Robert W.; (Greenville,
SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Brunt; Thomas J.
Coign; Robert W. |
Greenville
Greenville |
SC
SC |
US
US |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
46826241 |
Appl. No.: |
13/216297 |
Filed: |
August 24, 2011 |
Current U.S.
Class: |
416/220R |
Current CPC
Class: |
F01D 9/041 20130101;
F05D 2260/30 20130101 |
Class at
Publication: |
416/220.R |
International
Class: |
F01D 5/30 20060101
F01D005/30 |
Claims
1. A turbine nozzle vane retention system, comprising: a plurality
of nozzles; each of the plurality of nozzles comprising a platform;
a slot extending into the platform; and a pin extending between the
slot of a first nozzle and the slot of a second nozzle.
2. The turbine nozzle vane retention system of claim 1, wherein the
slot comprises a plurality of slots.
3. The turbine nozzle vane retention system of claim 1, wherein the
slot comprises a circular or a multi-faceted shape.
4. The turbine nozzle vane retention system of claim 1, wherein the
pin comprises a circular or a multi-faceted shape.
5. The turbine nozzle vane retention system of claim 1, wherein the
platform comprises a forward leg and wherein the slot is positioned
within the forward leg.
6. The turbine nozzle vane retention system of claim 1, wherein the
platform comprises one or more seal slots with a compliant seal
therein.
7. The turbine nozzle vane retention system of claim 1, wherein the
pin extends from a pressure side of the slot of the first nozzle to
a suction side of the slot of the second nozzle.
8. The turbine nozzle vane retention system of claim 1, wherein the
platform comprises an inner platform.
9. The turbine nozzle vane retention system of claim 8, further
comprising an outer platform.
10. The turbine nozzle vane retention system of claim 1, wherein
the slot is machined or cast into the platform.
11. The turbine nozzle vane retention system of claim 1, wherein
each of the plurality of nozzles comprises an airfoil.
12. The turbine nozzle vane retention system of claim 1, wherein
each of the plurality of nozzles comprises a singlet design.
13. A turbine nozzle vane retention system, comprising: a first
nozzle and a second nozzle; the first nozzle and the second nozzle
both comprising an airfoil and an inner platform with a slot
extending therein; and a pin extending between the slot of the
first nozzle and the slot of the second nozzle.
14. The turbine nozzle vane retention system of claim 13, wherein
the slot comprises a plurality of slots.
15. The turbine nozzle vane retention system of claim 13, wherein
the slot comprises a circular or a multi-faceted shape.
16. The turbine nozzle vane retention system of claim 13, wherein
the pin comprises a circular or a multi-faceted shape.
17. The turbine nozzle vane retention system of claim 13, wherein
the inner platform comprises a forward leg and wherein the slot is
positioned within the forward leg.
18. The turbine nozzle vane retention system of claim 13, wherein
the pin extends from a pressure side of the slot of the first
nozzle to a suction side of the slot of the second nozzle.
19. The turbine nozzle vane retention system of claim 13, wherein
the slot is machined or cast into the platform.
20. A turbine nozzle vane retention system, comprising: a plurality
of nozzles; each of the plurality of nozzles comprising a single
airfoil and an inner platform; one or more slots extending through
the inner platform; and a pin extending between a first slot of a
first nozzle and a second slot of a second nozzle.
Description
TECHNICAL FIELD
[0001] The present application and the resultant patent relate
generally to gas turbine engines and more particularly relate to a
turbine nozzle vane retention system using a retention pin about a
nozzle inner platform to retain the inner platform and/or other
components in case of failure.
BACKGROUND OF THE INVENTION
[0002] In gas turbine engines, thermally induced stresses may lead
to cracking in the turbine nozzles. If for example, a crack
propagates through the entire length of a nozzle airfoil, the inner
platform of the nozzle will no longer be retained in place. Parts
of the platform and/or other components therefore may dislodge and
cause catastrophic damage to the downstream flow path
components.
[0003] In doublet or triplet nozzle designs (two or three airfoils
per nozzle segment), the increased number of airfoils provides a
certain amount of redundancy against catastrophic failure given the
multiple load paths. Should a single airfoil crack and/or oxidize
severely, the adjacent airfoils still may retain the inner platform
in place. In a singlet design (one airfoil per segment), however, a
large section of the nozzle, the airfoil, and/or the platform may
dislodge if not retained at the inner and outer diameters.
Moreover, the risk of damage by a singlet nozzle inner platform
increases as gas turbine engine temperatures increase.
Specifically, the nozzle base material generally may be unable to
withstand the operating gas temperatures for long durations if the
nozzle cooling delivery system is compromised.
[0004] There is thus a desire for an improved turbine nozzle vane
retention system. Such a nozzle vane retention system should retain
at least the inner platform of a singlet nozzle in the event of
overall nozzle failure.
SUMMARY OF THE INVENTION
[0005] The present application and the resultant patent thus
provide a turbine nozzle vane retention system. The turbine nozzle
vane retention system may include a number of nozzles with a
platform, a slot extending into the platform, and a pin extending
between the slot of a first nozzle and the slot of a second
nozzle.
[0006] The present application and the resultant patent further
provide a turbine nozzle vane retention system. The turbine nozzle
vane retention system may include a first nozzle and a second
nozzle. Both nozzles may include an airfoil and an inner platform
with a slot extending therein. A pin may extend between the slot of
the first nozzle and the slot of the second nozzle.
[0007] The present application and the resultant patent further
provide a turbine nozzle vane retention system. The turbine nozzle
vane retention system may include a number of nozzles with a single
airfoil and an inner platform. One or more slots may extend through
the inner platform. A pin may extend between a first slot of a
first nozzle and a second slot of a second nozzle.
[0008] These and other features and improvements of the present
application and the resultant patent will become apparent to one of
ordinary skill in the art upon review of the following detailed
description when taken in conjunction with the several drawings and
the appended claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] FIG. 1 is a schematic diagram of a gas turbine engine.
[0010] FIG. 2 is a partial side view of a turbine stage showing a
turbine nozzle vane retention system as may be described
herein.
[0011] FIG. 3 is a partial perspective view of the turbine nozzle
and the turbine nozzle vane retention system of FIG. 2.
[0012] FIG. 4 is a partial side view of the pin of the turbine
nozzle vane retention system extending between a pair of
nozzles.
DETAILED DESCRIPTION
[0013] Referring now to the drawings, in which like numerals refer
to like elements throughout the several views, FIG. 1 shows a
schematic view of gas turbine engine 10 as may be used herein. The
gas turbine engine 10 may include a compressor 15. The compressor
15 compresses an incoming flow of air 20. The compressor 15
delivers the compressed flow of air 20 to a combustor 25. The
combustor 25 mixes the compressed flow of air 20 with a compressed
flow of fuel 30 and ignites the mixture to create a flow of
combustion gases 35. Although only a single combustor 25 is shown,
the gas turbine engine 10 may include any number of combustors 25.
The flow of combustion gases 35 is in turn delivered to a turbine
40. The flow of combustion gases 35 drives the turbine 40 so as to
produce mechanical work. The mechanical work produced in the
turbine 40 drives the compressor 15 via a shaft 45 and an external
load 50 such as an electrical generator and the like.
[0014] The gas turbine engine 10 may use natural gas, various types
of syngas, and/or other types of fuels. The gas turbine engine 10
may be anyone of a number of different gas turbine engines offered
by General Electric Company of Schenectady, New York and the like.
The gas turbine engine 10 may have different configurations and may
use other types of components. Other types of gas turbine engines
also may be used herein. Multiple gas turbine engines, other types
of turbines, and other types of power generation equipment also may
be used herein together.
[0015] FIGS. 2 and 3 show an example of a turbine nozzle vane
retention system 100 as may be described herein. The turbine nozzle
vane retention system 100 will be described herein in the context
of a first stage 110 of the turbine 40. In this example, the
turbine 40 may be part of a heavy duty gas turbine engine. The
turbine nozzle vane retention system 100, however, may be
applicable to many different types of turbines and components
thereof.
[0016] Generally described, the first stage 110 includes a first
stage nozzle 120 and a first stage bucket 130. Any number of
nozzles 120 and buckets 130 may be arranged in annular arrays in
the hot gas path of the turbine 40. The first stage nozzle 120
includes an outer platform 140, an inner platform 150, and an
airfoil 160 therebetween. Although a singlet design 170 with only
one airfoil 160 is shown, multiple airfoils 160 also may be used.
The outer platform 140 may be secured to a shroud 180, an outer
casing, a retaining ring, and the like. The inner platform 150
bears against an inner support ring 190, an inner casing, and the
like. Other components and other configurations may be used
herein.
[0017] The outer platform 140 ma include one or more outer seal
slots 200. Likewise, the inner platform 150 may include any number
of inner seals slots 210. The seal slots 200, 210 may be formed in
the platforms 140, 150 via an EDM process (electric discharge
machining) or other types of manufacturing techniques. A compliant
seal 220 may be positioned within the seal slots 200, 210. The
compliant seal 220 links adjacent nozzles 120. In the example of
FIG. 4, a first nozzle 121 and a second nozzle 122 are shown. Any
number of nozzles 120 may be used. Other components and other
configurations may be used herein.
[0018] The turbine nozzle vane retention system 100 also includes a
slot 230 formed in the inner platform 150. The slot 230 may extend
the width of the inner platform 150. Alternatively, a first slot
231 may be formed on a pressure side 240 of the nozzle 120 and a
second slot 232 may be formed on a suction side 250 of the nozzle
120. The slot 230 is shown on a forward leg 260 of the inner
platform 150, but any convenient location on the inner platform 150
or elsewhere may be used. The slot 230 is shown as having a
circular 270 shape, but a triangular, rectangular, or any
multi-faceted slot 230 may be used herein. The slot 230 may have
any desired size. The slot 230 may be machined or cast into the
inner platform 150. EDM and other types of manufacturing process
also may be used herein.
[0019] The turbine nozzle vane retention system 100 also includes a
pin 280 for positioning within the slot 230. The pin 280 may be any
type of rigid element with sufficient material strength so as to
maintain the inner platforms 150 in position. The term "pin" thus
refers to any rigid linking feature that may be used herein. The
pin 280 also may have a circular shape 290 or any shape or size
corresponding to the shape of the slot 230.
[0020] In use, the pin 280 may be positioned within the slots 230
of circumferentially adjacent nozzles 120. In the event of the
failure of a nozzle 120, the pin 280 and the slots 230 of the
turbine nozzle vane retention system 100 will transmit the gas path
pressure loads to adjacent undamaged nozzles 120 so as to prevent a
damaged inner platform 150 from being released into the gas path.
The turbine nozzle vane retention system 100 thus maintains the
inner platform 150 in place until the gas turbine engine 10 is
brought down for maintenance and the damaged nozzle section may be
replaced. The turbine nozzle vane retention system 100 thus
prevents such damage and the associated downtime and replacement
costs.
[0021] It should be apparent that the foregoing relates only to
certain embodiments of the present application and the resultant
patent. Numerous changes and modifications may be made herein by
one of ordinary skill in the art without departing from the general
spirit and scope of the invention as defined by the following
claims and the equivalents thereof.
* * * * *