U.S. patent application number 15/129579 was filed with the patent office on 2017-05-25 for stator vane support system within a gas turbine engine.
This patent application is currently assigned to Siemens Aktiengesellschaft. The applicant listed for this patent is SIEMENS AKTIENGESELLSCHAFT. Invention is credited to Elliot Griffin.
Application Number | 20170146026 15/129579 |
Document ID | / |
Family ID | 50588931 |
Filed Date | 2017-05-25 |
United States Patent
Application |
20170146026 |
Kind Code |
A1 |
Griffin; Elliot |
May 25, 2017 |
STATOR VANE SUPPORT SYSTEM WITHIN A GAS TURBINE ENGINE
Abstract
A stator vane segment (10) including a connection system (12)
that enables stator vane (14) alignment while enabling an
individual stator vane (14) to be replaced is disclosed. The stator
vane connection system (12) may include a radially extending inner
support (26) extending from a stator vane (14), whereby the inner
support (26) is secured to forward and aft inner rings via a
removable, inner axial bolt (22). The stator vane connection system
(12) may include one or more first inner pins (24) that aligns the
stator vane (14) and is positioned within the portion of the inner
support (26) of the stator vane (14) to which one or more inner
axial bolts (22) are attached. The stator vane connection system
(12) may include one or more first outer alignment pins (28) that
aligns the stator vane (14) and is positioned within a portion of
the outer diameter platform (48) of the stator vane (14), whereby
the first outer alignment pin (28) aligns the stator vane (14).
Inventors: |
Griffin; Elliot; (Winter
Springs, FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
SIEMENS AKTIENGESELLSCHAFT |
MUNCHEN |
|
DE |
|
|
Assignee: |
Siemens Aktiengesellschaft
Munchen
DE
|
Family ID: |
50588931 |
Appl. No.: |
15/129579 |
Filed: |
March 27, 2014 |
PCT Filed: |
March 27, 2014 |
PCT NO: |
PCT/US2014/031934 |
371 Date: |
September 27, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F04D 29/542 20130101;
F01D 11/005 20130101; F05D 2230/61 20130101; F05D 2230/80 20130101;
F04D 29/644 20130101; F05D 2230/64 20130101; F01D 9/042 20130101;
F04D 29/164 20130101 |
International
Class: |
F04D 29/54 20060101
F04D029/54; F04D 29/16 20060101 F04D029/16; F04D 29/64 20060101
F04D029/64 |
Claims
1. A stator vane segment (10), characterized in that: a stator vane
(14) formed from an airfoil (32) formed from an outer wall (34),
and having a leading edge (36), a trailing edge (38), a pressure
side (40), a suction side (42), an inner diameter platform (44) at
a first end (46) of the airfoil (32) and an outer diameter platform
(48) at a second end (50) of the airfoil (32); a stator vane
connection system (12) comprising: at least one inner axial bolt
(22) extending through a first inner ring (18), through at least a
portion of an inner support (26) of the stator vane (14) positioned
inward of the airfoil (32), and into a second inner ring (20) to
secure the stator vane (14); at least one first inner pin (24)
positioned within the portion of the inner support (26) of the
stator vane (14) to which the at least one inner axial bolt (22) is
attached, wherein the at least one first inner pin (24) aligns the
stator vane (14); and at least one first outer alignment pin (28)
positioned within the portion of the outer diameter platform (48)
of the stator vane (14), wherein the at least one first outer pin
(28) aligns the stator vane (14).
2. The stator vane segment (10) of claim 1, further characterized
in that an outer tie bar (56) coupled to the outer diameter
platform (48), wherein the outer tie bar (56) is secured to the
outer diameter platform (48) via a dovetail connection (58) and at
least one radially extending bolt between the outer tie bar (56)
and the outer diameter platform (48).
3. The stator vane segment (10) of claim 1, characterized in that
the first inner ring (18) is a forward inner ring (18).
4. The stator vane segment (10) of claim 3, further characterized
in that a seal (76) extending radially inward from a radially inner
surface of the forward inner ring.
5. The stator vane segment (10) of claim 4, characterized in that
the seal (76) extending radially inward from a radially inner
surface of the forward inner ring is a honeycomb seal (76).
6. The stator vane segment (10) of claim 3, characterized in that
the forward inner ring is sized to fit radially inward of a forward
extending portion of the inner diameter platform (44) and within a
recess in the inner diameter platform (44).
7. The stator vane segment (10) of claim 1, characterized in that
the second inner ring (20) is an aft inner ring (20).
8. The stator vane segment (10) of claim 7, further characterized
in that a seal (88) extending radially inward from a radially inner
surface (90) of the aft inner ring (20).
9. The stator vane segment (10) of claim 8, characterized in that
the seal (88) extending radially inward from a radially inner
surface (90) of the aft inner ring (20) is a honeycomb seal
(88).
10. The stator vane segment (10) of claim 7, characterized in that
an outer surface (92) of the aft inner ring (20) is flush with a
radially outer surface (94) of the inner diameter platform (44) of
the airfoil (32).
11. The stator vane segment (10) of claim 7, characterized in that
the aft inner ring (20) includes a portion that is sized to extend
axially forward into an aft recess (98) in the inner diameter
platform (44).
12. The stator vane segment (10) of claim 7, characterized in that
the aft inner ring (20) includes two aft extending arms (100, 102)
and separated from each other via an aft recess (104).
13. The stator vane segment (10) of claim 1, characterized in that
a radially inner surface (106) of the inner support (26) of the
stator vane (14) is flush with a radially inner surface (108) of
the first inner ring (18) and a radially inner surface (110) of the
second inner ring (20).
14. The stator vane segment (10) of claim 1, characterized in that
the at least one first inner pin (24) positioned within the portion
of the inner support (26) of the stator vane (14) extends in a
circumferential direction and at least one second inner pin (112)
positioned within the portion of the second inner ring (20) and
extending in a circumferential direction.
15. The stator vane segment (10) of claim 1, characterized in that
the at least one inner axial bolt (22) includes threads (116) that
engage threads (118) within the second inner ring (20).
16. The stator vane segment (10) of claim 1, characterized in that
the at least one inner axial bolt (22) includes a head (120) that
is larger than a shaft (122) of the axial bolt (22) and wherein the
first inner ring (18) includes a head receiving cavity (124) in
which the head 912) of the inner axial bolt (22) resides.
Description
FIELD OF THE INVENTION
[0001] This invention is directed generally to stator vane airfoils
within gas turbine engines, and more particularly to support
systems for stator vane airfoils.
BACKGROUND
[0002] Turbine engines typically include a plurality of rows of
stationary compressor stator vanes extending radially inward from a
shell and include plurality of rows of rotatable compressor blades
attached to a rotor assembly for turning the rotor. Conventional
turbine engines often include a segment with multiple stationary
airfoils collectively referred to as a stator. Stator segments
deflect in the upstream direction under steady gas pressure
loading, and the deflection varies around the circumference
dependent upon how the segment is constrained to the casing. The
unconstrained ends of the segment deflect more and have less axial
clearance to the upstream rotor disk. Thus, a need exists to
control deflection and alignment of the stator vane airfoils
forming the stator.
SUMMARY OF THE INVENTION
[0003] A compressor stator vane segment including a connection
system that enables stator vane alignment while enabling an
individual stator vane to be replaced is disclosed. The stator vane
connection system may include a radially extending inner support
extending from a stator vane, whereby the inner support is secured
to forward and aft inner rings via a removable, inner axial bolt.
The stator vane connection system may include one or more first
inner pins that aligns the stator vane and is positioned within the
portion of the inner support of the stator vane to which one or
more inner axial bolts are attached. The stator vane connection
system may include one or more first outer alignment pins that
aligns the stator vane and is positioned within the portion of the
outer diameter platform of the stator vane, whereby the first outer
alignment pin aligns the stator vane.
[0004] The compressor stator vane segment may be formed from a
stator vane including an airfoil formed from an outer wall, and
having a leading edge, a trailing edge, a pressure side, a suction
side, an inner diameter platform at a first end of the airfoil, and
an outer diameter platform at a second end of the airfoil. The
compressor stator vane segment may include a stator vane connection
system. The stator vane connection system may be formed from one or
more inner axial bolts extending through a first inner ring,
through at least a portion of an inner support of the stator vane
positioned inward of the airfoil, and into a second inner ring to
secure the stator vane. At least one first inner pin may be
positioned within the portion of the inner support of the stator
vane to which the inner axial bolt is attached. The first inner pin
may align the stator vane relative to an adjacent stator vane. One
or more first outer alignment pins may be positioned within the
portion of the outer diameter platform of the stator vane, whereby
the first outer pin aligns the stator vane relative to an adjacent
stator vane.
[0005] The stator vane connection system may also include an outer
tie bar coupled to the outer diameter platform. The outer tie bar
may be secured to the outer diameter platform via a removable
connection system, such as, but not limited to, a dovetail
connection and one or more radially extending bolts between the
outer tie bar and the outer diameter platform. In at least one
embodiment, the first inner ring may be a forward inner ring. One
or more seals may extend radially inward from a radially inner
surface of the forward inner ring. The seal extending radially
inward from a radially inner surface of the forward inner ring may
be a honeycomb seal. The forward inner ring may be sized to fit
radially inward of a forward extending portion of the inner
diameter platform and within a recess in the inner diameter
platform. In at least one embodiment, the second inner ring may be
an aft inner ring. One or more seals may extend radially inward
from a radially inner surface of the aft inner ring. The seal
extending radially inward from a radially inner surface of the aft
inner ring may be a honeycomb seal.
[0006] In at least one embodiment, an outer surface of the aft
inner ring may be flush with a radially outer surface of the inner
diameter platform of the airfoil. The aft inner ring may include a
portion that is sized to extend axially forward into an aft recess
in the inner diameter platform. The aft inner ring may also include
two aft extending arms separated from each other via an aft recess.
A radially inner surface of the inner support of the stator vane
may be flush with a radially inner surface of the first inner ring
and a radially inner surface of the second inner ring. In at least
one embodiment, the first inner pin may be positioned within the
portion of the inner support of the stator vane and may extend in a
circumferential direction, and one or more second inner pins may be
positioned within the portion of the second inner ring and may
extend in a circumferential direction. The inner axial bolt may
include threads that engage threads within the second inner ring.
The inner axial bolt may include a head that is larger than a shaft
of the axial bolt, and the first inner ring may include a head
receiving cavity in which the head of the inner axial bolt
resides.
[0007] The compressor stator vane segment may be assembled in a
number of ways. In at least one embodiment, the compressor stator
vane segment may be assembled by milling the airfoil, coating the
airfoil flow path surfaces, turning the outer ring from a rolled
ring, turning the forward inner ring from a custom forging, turning
the aft inner ring from a custom forging, drilling holes in the
outer ring, drilling holes in the inner forward ring, drilling
holes in the aft inner ring, brazing a forward honeycomb seal to
the forward inner ring, brazing an aft honeycomb seal to the aft
inner ring, turning the forward honeycomb inner diameter, turning
the aft honeycomb inner diameter, sawing the outer ring in half,
sawing the forward inner ring in half, sawing the aft inner ring in
half, and assembling the stator vanes and rings with bolts and pins
and stake the fasteners. Formation of the compressor vane segment
in this manner, reduces the number of manufacturing steps by seven
steps in comparison to conventional systems.
[0008] An advantage of the compressor stator vane segment is that
the compressor stator vane segment enables individual airfoil
replacement without cutting or welding during outages or other
times.
[0009] Another advantage of the compressor stator vane segment is
that fewer custom made parts, such as in one embodiment, three
fewer custom made parts, are needed than in conventional
systems.
[0010] Yet another advantage of the compressor stator vane segment
is that the compressor stator vane segment may be formed with fewer
manufacturing steps, such as in one embodiment, seven fewer steps,
are needed than in conventional systems.
[0011] Still another advantage of the compressor stator vane
segment is that welding and stress relieving are not required.
[0012] Another advantage of the compressor stator vane segment is
that machining of the entire assembly is not required, which
reduces lifting time and equipment costs.
[0013] Yet another advantage of the compressor stator vane segment
is that coating of the entire assembly is not required, which
reduces lifting time, shipping and equipment costs.
[0014] Still another advantage of the compressor stator vane
segment is that inner rings may be formed from a lower cost
material, such as, but not limited to, low carbon steel, than
conventional systems.
[0015] Another advantage of the compressor stator vane segment is
that a cover half and a base half may be interchangeable between
engines, which reduces service inventory and handling costs.
[0016] Yet another advantage of the compressor stator vane segment
is that the segment could be formed in 90 degree segments to
further reduce service inventory and handling costs and for ease of
assembly and disassembly.
[0017] Still another advantage of the compressor stator vane
segment is that mechanical dampening may be achieved through use of
the bolted assembly.
[0018] These and other embodiments are described in more detail
below.
BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The accompanying drawings, which are incorporated in and
form a part of the specification, illustrate embodiments of the
presently disclosed invention and, together with the description,
disclose the principles of the invention.
[0020] FIG. 1 is a perspective view of compressor stator vane
segment within a gas turbine engine.
[0021] FIG. 2 is a cross-sectional view of a compressor stator vane
segment within a gas turbine engine taken at section line 2-2 in
FIG. 1.
[0022] FIG. 3 is a detail view of a portion of the compressor
stator vane segment within a gas turbine engine taken at detail
line 3-3 in FIG. 2.
[0023] FIG. 4 is an end view of two compressor stator vane segments
forming a single stage stator assembly.
[0024] FIG. 5 is an end view of another embodiment of compressor
stator vane segments forming a single stage stator assembly,
whereby four stator vane segments are used.
DETAILED DESCRIPTION OF THE INVENTION
[0025] As shown in FIGS. 1-5, a compressor stator vane segment 10
including a connection system 12 that enables stator vane alignment
while enabling an individual stator vane 14 to be replaced is
disclosed. The stator vane connection system 12 may include a
radially extending inner support 16 extending from a stator vane
14, whereby the inner support 16 is secured to forward and aft
inner rings 18, 20 via a removable, inner axial bolt 22. The stator
vane connection system 12 may include one or more first inner pins
24 that aligns the stator vane 14 and is positioned within the
portion of the inner support 16 of the stator vane 14 to which one
or more inner axial bolts 22 are attached. The stator vane
connection system 12 may include one or more first outer alignment
pins 28 that aligns the stator vane 14 and is positioned within the
portion of the outer diameter platform 30 of the stator vane 14,
whereby the first outer alignment pin 28 aligns the stator vane 14.
In at least one embodiment, the compressor stator vane segment 10
may include a stator vane 14 formed from an airfoil 32 formed from
an outer wall 34, and having a leading edge 36, a trailing edge 38,
a pressure side 40, a suction side 42, and an inner diameter
platform 44 at a first end 46 of the airfoil 32 and an outer
diameter platform 30 at a second end 50 of the airfoil 32. The
stator vane 14 may be secured with the turbine engine 54 via a
stator vane connection system 12. The stator vane connection system
12 may be formed from one or more inner axial bolts 22 extending
through a first inner ring 18, through at least a portion of an
inner support 16 of the stator vane 14 positioned inward of the
airfoil 32, and into a second inner ring 20 to secure the stator
vane 14. In at least one embodiment, the first inner ring 18 is a
forward inner ring 18, and the second inner ring 20 is an aft inner
ring 20. One or more first inner pins 24 may be positioned within
the portion of the inner support 16 of the stator vane 14 to which
the inner axial bolt 22 is attached. The first inner pin 24 may
align the stator vane 14 relative to an adjacent stator vane 14.
The stator vane connection system 12 may also include on or more
first outer alignment pins 28 positioned within the portion of the
outer diameter platform 30 of the stator vane 14. The first outer
pin 24 aligns the stator vane 14 relative to an adjacent stator
vane 14.
[0026] The stator vane connection system 12 may also include an
outer tie bar 56 coupled to the outer diameter platform 30. The
outer tie bar 56 may be secured to the outer diameter platform 30
via a removable connection system 58, such as, but not limited to,
a dovetail connection 58. The outer tie bar 56 may be configured to
have a dovetail shape extending in a circumferential direction such
that it includes an linear outer surface 70 with inwardly sloped
sidewalls 72, 74. In addition, the outer diameter platform 30 may
have a dovetail shaped receiver 62 with a linear base surface 64
and inward sloped sidewalls 66 and 68. The outer tie bar 56 may
also be coupled to the stator vane 14 via one or more radially
extending bolts 60 between the outer tie bar 56 and the outer
diameter platform 30.
[0027] The stator vane connection system 12 may also include one or
more forward seals 76 extending radially inward from a radially
inner surface 78 of the forward inner ring 18. In at least one
embodiment, the forward seal 76 may be, but is not limited to
being, a honeycomb seal or a knife seal. The forward inner ring 18
may be is sized to fit radially inward of a forward extending
portion 80 of the inner diameter platform 44 and within a recess 82
in the inner diameter platform 44. The forward surface 84 of the
forward inner ring 18 may be flush with a forward surface 86 of the
inner diameter platform 44.
[0028] The stator vane connection system 12 may also include one or
more aft seals 88 extending radially inward from a radially inner
surface 90 of the aft inner ring 20.
[0029] In at least one embodiment, the aft seal 88 may be, but is
not limited to being, a honeycomb seal or a knife seal. In at least
one embodiment, an outer surface 92 of the aft inner ring 20 may be
flush with a radially outer surface 94 of the inner diameter
platform 44 of the airfoil 32. The aft inner ring 20 may include a
forward portion 96 that is sized to extend axially forward into an
aft recess 98 in the inner diameter platform 44. The aft inner ring
20 may also include two aft extending arms 100, 102 and separated
from each other via an aft recess 104. In at least one embodiment,
a radially inner surface 106 of the inner support 16 of the stator
vane 14 may be flush with a radially inner surface 108 of the first
inner ring 18 and a radially inner surface 110 of the second inner
ring 20.
[0030] On or more first inner pins 24 positioned within the portion
of the inner support 16 of the stator vane 14 extends in a
circumferential direction. One or more second inner pins 112 may be
positioned within the portion of the second inner ring 20 and may
extend in a circumferential direction. The first inner pin 24 or
the second inner pin 112 or both may be positioned generally
orthogonal to a longitudinal axis 114 of a turbine engine 54. The
first inner pin 24 and the second inner pin 112 may have any
appropriate shape and length. In at least one embodiment, the first
inner pin 24 or the second inner pin 112, or both may be generally
cylindrical. The first inner pin 24 and the second inner pin 112
may be formed from any appropriate material. The
[0031] The inner axial bolt 22 may include threads 116 that engage
threads 118 within the second inner ring 20. The inner axial bolt
22 may also include a head 120 that is larger than a shaft 122 of
the axial bolt 22. The first inner ring 18 may include a head
receiving cavity 124 in which the head 120 of the inner axial bolt
22 resides.
[0032] The compressor stator vane segment 10 may be assembled in a
number of ways. In at least one embodiment, the compressor stator
vane segment 10 may be assembled by milling the airfoil 32, coating
the airfoil flow path surfaces, turning the outer ring from a
rolled ring, turning the forward inner ring 18 from a custom
forging, turning the aft inner ring 20 from a custom forging,
drilling holes in the outer ring, drilling holes in the inner
forward ring 18, drilling holes in the aft inner ring 20, brazing a
forward honeycomb seal 76 to the forward inner ring 18, brazing an
aft honeycomb seal 88 to the aft inner ring 20, turning the forward
honeycomb inner diameter, turning the aft honeycomb inner diameter,
sawing the outer ring in half, sawing the forward inner ring 18 in
half, sawing the aft inner ring 20 in half, and assembling the
stator vanes 14 and rings 18, 20 with bolts 22, 60 and pins 24, 28,
112 and staking the fasteners.
[0033] The foregoing is provided for purposes of illustrating,
explaining, and describing embodiments of this invention.
Modifications and adaptations to these embodiments will be apparent
to those skilled in the art and may be made without departing from
the scope or spirit of this invention.
* * * * *