U.S. patent application number 17/125661 was filed with the patent office on 2022-06-23 for seal assembly between a transition duct and a first stage vane structure.
The applicant listed for this patent is Siemens Energy Global GmbH & Co. KG. Invention is credited to Robert H. Bartley, Dustin C. Boudin, Wojciech Dyszkiewicz, Johan Hsu, Jordan Metz, Muzaffer Sutcu.
Application Number | 20220195943 17/125661 |
Document ID | / |
Family ID | |
Filed Date | 2022-06-23 |
United States Patent
Application |
20220195943 |
Kind Code |
A1 |
Boudin; Dustin C. ; et
al. |
June 23, 2022 |
SEAL ASSEMBLY BETWEEN A TRANSITION DUCT AND A FIRST STAGE VANE
STRUCTURE
Abstract
A sealing assembly positioned between a first component having a
first interface and a second component having a second interface is
provided. The sealing assembly includes a flat bracket fixedly
attached to the first interface to define an extension and a
floating seal including a body portion, a first U-shaped channel
arranged to engage the extension, and a second U-shaped channel
inhibiting movement of the floating seal in an axial direction
while allowing movement in a radial direction, and the second
U-shaped channel allowing movement in the axial direction and
inhibiting movement in the radial direction.
Inventors: |
Boudin; Dustin C.; (Belmont,
NC) ; Metz; Jordan; (Charlotte, NC) ; Hsu;
Johan; (Orlando, FL) ; Sutcu; Muzaffer;
(Oviedo, FL) ; Bartley; Robert H.; (Oviedo,
FL) ; Dyszkiewicz; Wojciech; (Winter Springs,
FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Siemens Energy Global GmbH & Co. KG |
Munchen |
|
DE |
|
|
Appl. No.: |
17/125661 |
Filed: |
December 17, 2020 |
International
Class: |
F02C 7/28 20060101
F02C007/28; F02C 7/12 20060101 F02C007/12 |
Claims
1. (canceled)
2. The sealing assembly of claim 10, wherein the flat bracket
includes a first planar face that abuts the first interface, a
second planar face, and a plurality of radially extending cooling
channels formed in the first planar face.
3. The sealing assembly of claim 10, wherein the flat bracket
includes a plurality of contact tabs for contacting the floating
seal.
4. The sealing assembly of claim 10, further comprising an
anti-rotation pin and a slot formed in the flat bracket, the
anti-rotation pin positioned at least partially within the slot to
inhibit the floating seal from circumferential movement.
5. The sealing assembly of claim 10, wherein the first component is
a transition component of a gas turbine engine and the second
component is a first stage turbine vane of the gas turbine engine,
and wherein the second U-shaped channel engages an upstream lip of
the first stage turbine vane.
6. The sealing assembly of claim 5, wherein the second U-shaped
channel defines a groove in the body portion and wherein the groove
includes a contact face including a wear strip attached to the
contact face.
7. The sealing assembly of claim 6, wherein the wear strip
comprises a cobalt-chromium alloy.
8. (canceled)
9. (canceled)
10. A sealing assembly positioned between a first component having
a first interface and a second component having a second interface,
the seal assembly comprising: a flat bracket fixedly attached to
the first interface to define an extension; and a floating seal
including a body portion, a first U-shaped channel arranged to
engage the extension, and a second U-shaped channel normal to the
first U-shaped channel arranged to engage the second interface, the
first U-shaped channel inhibiting movement of the floating seal in
an axial direction while allowing movement in a radial direction,
and the second U-shaped channel allowing movement in the axial
direction and inhibiting movement in the radial direction, wherein
the body portion defines a cylindrical surface and a frustoconical
surface, and wherein a first row of cooling passages include first
outlet holes formed in the frustoconical surface and a second row
of cooling passages include second outlet holes formed in the
cylindrical surface, wherein the second row of cooling passages
extend normal to the cylindrical surface and wherein the first row
of cooling passages extend on an oblique angle with respect to the
cylindrical surface, and wherein the first row of cooling passages
is staggered circumferentially with respect to the second row of
cooling passages so that none of the first outlet holes are axially
aligned with the second outlet holes.
11. The sealing assembly of claim 10, further comprising a
plurality of access bores formed in the body portion, and a
plurality of bolts arranged to attach the flat bracket to the first
interface, each access bore aligned with one of the plurality of
bolts to allow installation of the plurality of bolts through the
floating seal.
12. The sealing assembly of claim 10, wherein the thickness of the
flat bracket is in a range of 6 mm to 25 mm.
13. (canceled)
14. (canceled)
15. (canceled)
16. (canceled)
17. (canceled)
Description
BACKGROUND
[0001] A combustion turbine engine, such as a gas turbine engine,
includes a compressor section, a combustor section, and a turbine
section. Intake air is compressed in the compressor section and
then mixed with fuel. The mixture is ignited in the combustor
section to produce a high-temperature and high-pressure flow of
combustion gases conveyed by a transition duct system to the
turbine section of the engine, where thermal energy is converted to
mechanical energy. Seals are interposed between respective outlets
of the transition ducts and corresponding first stage turbine vane
structures to limit compressed air, as may be fluidly coupled to a
transition shell, to leak and mix with the hot flow of
combustion.
BRIEF SUMMARY
[0002] In one construction, a sealing assembly positioned between a
first component having a first interface and a second component
having a second interface is provided. The sealing assembly
includes a flat bracket fixedly attached to the first interface to
define an extension and a floating seal including a body portion, a
first U-shaped channel arranged to engage the extension, and a
second U-shaped channel inhibiting movement of the floating seal in
an axial direction while allowing movement in a radial direction,
and the second U-shaped channel allowing movement in the axial
direction and inhibiting movement in the radial direction.
[0003] In another construction, a method of cooling a sealing
assembly is provided. The method includes attaching a flat bracket
to a first component to define an extension, the bracket including
a plurality of radial cooling channels, engaging a first U-shaped
channel of a floating seal with the extension, the first U-shaped
channel cooperating with the extension to inhibit relative axial
movement therebetween while allowing relative radial movement,
engaging a second U-shaped channel of the floating seal with a
second component, the second U-shaped channel cooperating the
second component to allow relative axial movement therebetween
while inhibiting relative radial movement, discharging a first
cooling flow from a first row of cooling passages formed in a
frustoconical surface of the floating seal, discharging a second
cooling flow from a second row of cooling passages formed in a
cylindrical seal surface of the floating seal. The first row of
cooling passages includes first outlet holes formed in the
frustoconical surface and the second row of cooling passages
include second outlet holes formed in the cylindrical surface.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS
[0004] To easily identify the discussion of any particular element
or act, the most significant digit or digits in a reference number
refer to the figure number in which that element is first
introduced.
[0005] FIG. 1 illustrates a perspective view of a sealing interface
between a transition component and a turbine component.
[0006] FIG. 2 illustrates a cross sectional view of a sealing
interface between a transition component and a turbine
component.
[0007] FIG. 3 illustrates a side view of a flat bracket.
[0008] FIG. 4 illustrates a cross sectional partial perspective
view of a sealing interface secured with an anti-rotation pin.
[0009] FIG. 5 illustrates a perspective view of the sealing
interface having an attached wear strip.
[0010] FIG. 6 illustrates a top view of the floating seal.
[0011] FIG. 7 illustrates a bottom view of the floating seal.
[0012] FIG. 8 illustrates a top zoomed in view of the floating seal
having two rows of cooling passages.
[0013] FIG. 9 illustrates a cross sectional view of the sealing
interface with cooling flows.
DETAILED DESCRIPTION
[0014] A versatile sealing interface that can be retrofittable to
existing transition ducts already in the field and fit within the
tight clearance existing between the transition duct and a first
stage turbine vane structure is desired.
[0015] FIG. 1 illustrates a perspective view of a sealing interface
between a gas turbine transition 102 and a first stage turbine vane
104. In FIG. 1, both the inner sealing interface 108 and the outer
sealing interface 106 are shown for illustrative purposes. The
outer sealing interface 106 is positioned radially outward from the
inner sealing interface 108 with respect to a longitudinal axis 110
of the gas turbine engine about which axis the gas turbine engine
rotates. The outer sealing interface 106 and the inner sealing
interface 108 are essentially a mirror image of one another and
thus henceforth will be referred to as the sealing interface. The
sealing interface is arranged to seal a gap between the transition
102 and the first stage turbine vane 104. The transition 102 may
include an outlet exit frame having an outlet exit surface 202
including at least one flange having a plurality of fastener holes.
The flow path of the combustion gases is designated by F so that
the flow of combustion gases flows from the combustor of the gas
turbine engine through the transition 102 and into the turbine
section of the engine represented in FIG. 1 by the first stage
turbine vane 104.
[0016] FIG. 2 illustrates a cross sectional view of the sealing
interface 200 between the transition 102 and the first stage
turbine vane 104. The transition 102 includes an outlet exit frame
having an outlet exit surface 202. The first stage turbine vane 104
includes an upstream lip 204. The sealing interface 200 may be
arranged to couple the outlet exit frame of the transition 102 to
the first stage turbine vane 104.
[0017] As seen in FIG. 2, the sealing interface 200 includes a
floating seal 206 having an upstream portion 212, a downstream
portion 214, and a flat bracket 208 positioned between the
transition 102 and the floating seal 206. The upstream portion 212
of the floating seal 206 is generally U-shaped in cross section and
defines a first channel 210. The downstream portion 214 of the
floating seal 206 is also generally U-shaped and is situated normal
to the U-shaped upstream portion 212. The downstream portion 214
comprises a second channel 216 that engages the upstream lip 204 of
the first stage turbine vane 104.
[0018] FIG. 2 illustrates the flat bracket 208 having a thickness
and disposed between the upstream portion 212 of the floating seal
206 and the outlet exit surface 202. The flat bracket 208 may be
fixedly attached to the transition 102 by a fastener, for example.
The flat bracket 208 provides a barrier between the floating seal
206 and the transition 102 to eliminate any potential wear of the
outlet exit surface 202. The flat bracket 208 also extends beyond
the transition 102 to provide an extension. The first channel 210
is positioned to engage the flat bracket 208.
[0019] In an embodiment, the thickness of the flat bracket 208 may
be in a range of between 6 mm and 25 mm. However, some
considerations are taken into account when determining the
thickness of the flat bracket 208. For example, the thickness of
the flat bracket 208 is smaller than the width of the first channel
210 such that the floating seal 206 can move relative to the flat
bracket 208. In addition, the thickness may be in the range of one
to two times the wall thickness of the floating seal 206 measured
at the first channel 210. In an embodiment, the gap clearance,
i.e., the difference of the flat bracket thickness and the width of
the first channel 210, is in a range of 0.4 mm to 2 mm.
[0020] To accommodate axial and radial movement of the first stage
turbine vane 104 relative to the transition 102 during operation of
the gas turbine, the floating seal 206 was designed to float, such
that it can accommodate the movements of the first stage turbine
vane 104 without coming into contact with any surrounding
components or restraining any movement. For example, the first
channel 210, when engaged with the flat bracket 208, inhibits
movement of the floating seal 206 in the axial direction but allows
movement in the radial direction and the second channel 216, when
engaged with the first stage turbine vane 104, inhibits movement of
the floating seal 206 in the radial direction but allows movement
in the axial direction.
[0021] While designed to float, the floating seal 206 does still
come into contact with the first stage turbine vane 104 at times.
An outer contact face 220, with respect to the gas path, of the
second channel 216 typically experiences significant wear from
contact with the upstream lip 204 of the first stage turbine vane
104. A wear strip 218 is thus attached to the contact face 220 of
the second channel 216. The wear strip 218 may extend a length (1)
of the second channel 216, as shown. The width of the wear strip
218 is designed to accommodate vane twist that occurs from the
thermal growth of the first stage turbine vane 104.
[0022] FIG. 3 illustrates a side view of a face of an outer flat
bracket. The inner flat bracket is generally a mirror image of the
outer flat bracket. Thus, henceforth the inner flat bracket and the
outer flat bracket will be referred to as the flat bracket 208. The
flat bracket 208 includes a first planar face 310 and a second
planar face (not shown). The first planar face 310 includes a
plurality of cooling channels 302 extending radially. The plurality
of cooling channels 302 provides cooling air from a compressor
section to cool the outlet exit surface 202 of the transition 102.
Some of the cooling channels 302 may be routed around mounting
holes. Cooling channel outlets 312 may be equally spaced along the
first planar face 310 for uniform cooling of the outlet exit
surface 202.
[0023] In an embodiment, the flat bracket 208 includes a plurality
of contact tabs 304. The contact tabs 304 are provided on an end of
the flat bracket 208 that engages the floating seal 206 within the
first channel 210. The contact tabs 304 are provided on the flat
bracket 208 in order to reduce points of contact between the
floating seal 206 and the flat bracket 208 and thus reduce
potential binding of the floating seal 206. In an embodiment, a
slot 306 is formed in the flat bracket 208 through which an
anti-rotation pin may extend.
[0024] In an embodiment, the flat bracket 208 includes a plurality
of bolt holes 308. A plurality of bolts may be used to attach the
flat bracket 208 to the transition 102 through the plurality of
bolt holes 308. During the attaching, the first planar face 310 is
positioned to mate to the outlet exit surface 202 in order to cool
the outlet exit surface 202.
[0025] FIG. 4 illustrates a partial cross-sectional perspective
view of the sealing interface 200. The sealing interface 200
includes an anti-rotation pin 402 extending through the slot 306 in
the flat bracket 208. The slot 306 allows for radial movement of
the anti-rotation pin 402 along the slot 306. The anti-rotation pin
402 restricts the floating seal 206 from circumferential movement.
The floating seal 206 includes a cutout portion, or U-shaped
channel 210, to allow the relative radial movement of the
anti-rotation pin 402 of the floating seal 206 within the slot
306.
[0026] FIG. 4 also illustrates an embodiment where the floating
seal 206 includes a plurality of access bores 404 formed in the
body portion of the floating seal 206. The plurality of access
bores 404 are positioned to mate up with a plurality of
corresponding bolt holes 308 in the flat bracket 208. The plurality
of access bores 404 are aligned with a corresponding bolt in a
corresponding bolt hole 308 attaching the flat bracket 208 to the
outlet exit surface 202 to allow the bolts to be installed through
the access bores 404. The access bores 404 may be oval shaped and
are large enough that the bolt head does not come into contact with
the floating seal 206. Two rows of cooling passages, an upstream
row of cooling passages 406 and a downstream row of cooling
passages 408 may be positioned in the body portion of the floating
seal 206.
[0027] FIG. 5 illustrates a perspective view of the sealing
interface 200 having a wear strip 218 attached to a contact face
220 of the U-shaped downstream portion 214. In an embodiment, the
downstream portion 214 includes the contact face 220, the contact
face 220 including the wear strip 218 and extends circumferentially
along the downstream portion 214. The wear strip 218 is attached to
the contact face 220 by brazing, for example, however other methods
of attachment are also possible. In an embodiment, the wear strip
218 may comprise a cobalt-chromium alloy. In particular, the
cobalt-chromium alloy may be Stellite 6B.RTM..
[0028] FIG. 6 illustrates a top view of the floating seal 206 while
FIG. 7 illustrates a bottom view of the floating seal 206. The
floating seal 206 includes a first cylindrical surface 602, a
second cylindrical surface 606 and a frustoconical surface 604. The
floating seal 206 also includes two rows of cooling passages. Each
cooling passage of an upstream row of cooling passages 406 extends
on an oblique angle, with respect to the first cylindrical surface
602, and includes an outlet hole in the frustoconical surface 604.
A cross section of a cooling passage of the upstream row of cooling
passages 406 may be seen in FIG. 4. Each cooling passage of a
downstream row of cooling passages 408 extends normally to the
first cylindrical surface 602 and includes an outlet hole in a
second cylindrical surface 606. The upstream row of cooling
passages 406 and the downstream row of cooling passages 408 allow a
cooling air flow from the compressor section of the engine to cool
the sealing interface 200 throughout the floating seal 206 and on a
hot combustion gas side of the sealing interface 200.
[0029] In an embodiment, the upstream row of cooling passages 406
is staggered circumferentially with respect to the downstream row
of cooling passages 408 such that none of the cooling passages from
the upstream row of cooling passages 406 is axially aligned with
the cooling passages of the downstream row of cooling passages 408.
The staggered arrangement may be seen in FIG. 8. A distance
(d.sub.1) between the rows 406, 408 may be between 2-3 mm, for
example. A distance (d.sub.2) between the cooling passages 406, 408
in each row may be between 5-6 mm, for example.
[0030] FIG. 9 illustrates a cross sectional view of the sealing
interface 200 with the cooling flows shown through the floating
seal 206 and along the flat bracket 208/outlet exit surface 202
interface. A cooler fluid flow originating from the compressor
section of the engine may be used (flow shown by the arrows) to
cool the floating seal 206 and the outlet exit surface 202.
However, as the sealing interface 200 is used to limit the
compressed air, as may be fluidly coupled to the transition shell,
from mixing with the combustion gases, a limited amount of cooling
flow is permitted. Cooling through the cooling channels 302 is
represented by cooling flow B. Cooling through the upstream row of
cooling passages 406 may be seen by cooling flow C and cooling
through the downstream rows of cooling passages 408 may be seen by
cooling flow D. Cooling flows A and E represent leakage flows
through the sealing interface 200 into the combustion gas flow F
(shown in FIG. 1). The proposed design of the sealing interface 200
with the cooling passages 302, 606, and 608 meet thresholds for
leakage flow through the sealing interface 200.
[0031] The proposed sealing interface allows the newer design of
the transition duct to mate with existing first stage turbine vane
structures already in the field such that the sealing interface is
retrofittable. In addition, the proposed solution is cost effective
as it allows the transition duct the versatility of being mated to
more than one style of first stage turbine vane structures while
continuing to provide consistent sealing performance. The sealing
interface also introduces cooling features for cooling the
interface itself and the adjoining transition.
* * * * *