U.S. patent application number 14/256022 was filed with the patent office on 2014-10-30 for removable swirler assembly for a combustion liner.
This patent application is currently assigned to KHALID OUMEJJOUD. The applicant listed for this patent is JEREMY METTERNICH, KHALID OUMEJJOUD. Invention is credited to JEREMY METTERNICH, KHALID OUMEJJOUD.
Application Number | 20140318150 14/256022 |
Document ID | / |
Family ID | 51788070 |
Filed Date | 2014-10-30 |
United States Patent
Application |
20140318150 |
Kind Code |
A1 |
METTERNICH; JEREMY ; et
al. |
October 30, 2014 |
REMOVABLE SWIRLER ASSEMBLY FOR A COMBUSTION LINER
Abstract
A novel and improved swirler assembly for use in a combustion
liner of a gas turbine engine is disclosed. The swirler assembly is
removable and sized to provide an improved assembly, repairability,
and fit-up in the combustion liner. The swirler assembly includes a
premix tube, premix swirler and a plurality of axially spaced
mounting blocks for receiving removable fasteners for securing the
swirler assembly to the combustor.
Inventors: |
METTERNICH; JEREMY;
(WELLINGTON, FL) ; OUMEJJOUD; KHALID; (PALM BEACH
GARDENS, FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
METTERNICH; JEREMY
OUMEJJOUD; KHALID |
WELLINGTON
PALM BEACH GARDENS |
FL
FL |
US
US |
|
|
Assignee: |
OUMEJJOUD; KHALID
PALM BEACH GARDENS
FL
METTERNICH; JEREMY
WELLINGTON
FL
|
Family ID: |
51788070 |
Appl. No.: |
14/256022 |
Filed: |
April 18, 2014 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
61815835 |
Apr 25, 2013 |
|
|
|
Current U.S.
Class: |
60/798 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 2900/00005 20130101; F23R 3/286 20130101; F23R 3/60 20130101;
F23R 2900/00017 20130101; Y10T 29/49346 20150115 |
Class at
Publication: |
60/798 |
International
Class: |
F23R 3/28 20060101
F23R003/28 |
Claims
1. A swirler assembly for a gas turbine combustor comprising: a
premix tube having an inlet end, an opposing outlet end and a
longitudinal axis extending therethrough; a premix swirler
positioned within the premix tube, the swirler having a plurality
of turning vanes for imparting a swirl to a passing flow; a first
mounting block positioned along an outer wall of the premix tube
proximate the inlet end and having a plurality of first holes
oriented generally perpendicular to the longitudinal axis; and, a
second mounting block positioned along the outer wall of the premix
tube a distance from the first mounting block, the second mounting
block has one or more second holes extending through the second
mounting block in a direction perpendicular to the plurality of
first holes.
2. The swirler assembly of claim 1, wherein the premix tube is
generally conical.
3. The swirler assembly of claim 1, wherein each of the first
mounting block and second mounting block are secured to the premix
tube.
4. The swirler assembly of claim 3, wherein the first and second
mounting blocks are secured to the premix tube by a weld or braze
joint.
5. The swirler assembly of claim 1, wherein the plurality of holes
in the first mounting block comprise at least two holes.
6. The swirler assembly of claim 1, wherein the one or more second
holes is threaded.
7. The swirler assembly of claim 1, wherein the second mounting
block has a second forward face and opposing second aft face, where
the second aft face is finish machined to a predetermined axial
dimension.
8. A multi-point, multi-directional fastening assembly for use in a
gas turbine combustor comprising: a first mounting block secured to
a body, the first mounting block having a first forward face, an
opposing first aft face, a pair of side faces, an outer face, and a
plurality of holes located in the outer face; and, a second
mounting block secured to the body, the second mounting block
having one or more holes located therein; wherein the second
mounting block is spaced an axial distance from the first mounting
block.
9. The fastening assembly of claim 8, wherein the outer face is
arc-shaped at least at regions surrounding the plurality of
holes.
10. The fastening assembly of claim 8, wherein the first mounting
block is secured to the body by a weld or braze joint.
11. The fastening assembly of claim 8, wherein the second mounting
block is secured to the body by a weld or braze joint.
12. The fastening assembly of claim 8, wherein the first and second
mounting blocks are integral to the body.
13. The fastening assembly of claim 8, wherein the plurality of
holes in the first mounting block are generally perpendicular to
the one or more mounting holes in the second mounting block.
14. A removable swirler assembly in a combustor comprising: a
generally cylindrical body; a center core positioned within the
cylindrical body proximate an inlet of the generally cylindrical
body; a plurality of vanes extending between the center core and
the generally cylindrical body; a first mounting block secured to
the generally cylindrical body, the first mounting block having a
first forward face, an opposing aft face, a pair of side faces, and
an outer face having a plurality of holes located therein; and, a
second mounting block secured to the generally cylindrical body,
the second mounting block having one or more holes located therein;
wherein the removable swirler is fastened to the combustor at both
the first mounting block and second mounting block through a
plurality of removable fasteners.
15. The removable swirler of claim 14, wherein the plurality of
vanes are oriented so as to impart swirl to a passing flow of air
and fuel.
16. The removable swirler of claim 14, wherein the first mounting
block extends in a circumferential distance greater than the second
mounting block.
17. The removable swirler of claim 14, wherein the plurality of
holes in the first mounting block are generally perpendicular to
the single hole in the second mounting block.
18. The removable swirler of claim 14 further comprising a
plurality of fasteners placed into the plurality of openings of the
first mounting block for securing the swirler to the combustor.
19. The removable swirler of claim 14, wherein the outer face of
the first mounting block is arc-shaped at least at regions
proximate the plurality of holes.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application claims priority to U.S. Provisional Patent
Application Ser. No. 61/815,835, filed on Apr. 25, 2013. This
application is related by subject matter to commonly-assigned U.S.
Non-Provisional patent applications entitled PREMIXER ASSEMBLY FOR
GAS TURBINE COMBUSTOR (Attorney Docket No. PSM-317/PSSF.199281) and
SWIRLER ASSEMBLY AND STIFFENING MECHANISM FOR PREMIXER ASSEMBLY OF
A GAS TURBINE COMBUSTOR (Attorney Docket No. PSM-318/PSSF.199282)
and assigned to the same assignee as the present application.
TECHNICAL FIELD
[0002] The present invention generally relates to a gas turbine
combustor. More specifically, the present invention is directed
towards a removable swirler portion of combustion liner having
features designed to enhance combustor performance and increase
component life through improved assembly and disassembly techniques
and improved cooling configurations.
BACKGROUND OF THE INVENTION
[0003] In a typical gas turbine engine, a compressor having
alternating stages of rotating and stationary airfoils is coupled
to a turbine through an axial shaft, with the turbine also having
alternating stages of rotating and stationary airfoils. The
compressor stages decrease in size in order to compress the air
passing therethrough. The compressed air is then supplied to one or
more combustors, which mixes the air with fuel. An ignition source
proximate the one or more combustors ignite the mixture, forming
hot combustion gases. The expansion of the hot combustion gases
drives the stages of a turbine, which is coupled to the compressor
through an axial shaft. The exhaust gases can then be used as a
source of propulsion, to generate steam through a heat recovery
steam generator, or in powerplant operations to turn a shaft
coupled to a generator for producing electricity.
[0004] The combustion system of a gas turbine engine can take on a
variety of configurations. A combustion system for a gas turbine
engine can comprise a single combustion chamber, a plurality of
individual combustion chambers spaced about the axis of the engine,
a plenum-type combustion system, or a variety of other combustion
systems. Depending on the engine geometry, performance
requirements, and physical operating location, the exact combustor
arrangement will vary.
[0005] One such combustion system comprises a casing secured to the
frame of the engine, a combustion liner secured within at least a
part of the casing, and one or more fuel nozzles positioned within
or adjacent to the combustion liner for injecting a fuel (gas,
liquid, or both) into the combustion chamber. The combustion system
is in fluid communication with the engine. More specifically, the
casing and liner arrangement provides a way for air from the
compressor to enter the combustion system, where it mixes with fuel
from the one or more fuel nozzles. The fuel-air mixture is ignited
by an ignition source, such as a spark igniter. Hot combustion
gases travel through the combustion liner and often through one or
more transition pieces and into the turbine. The transition piece
is essentially a duct having a geometry that changes from the shape
of the combustor to the inlet of the turbine.
[0006] The combustion liner is at the center of combustor
operations. The combustion liner geometry is dictated by a variety
of factors including the operating parameters of the engine,
performance requirements, and available geometry. While combustion
liner geometries can vary, the combustion liner typically includes
at least a portion for receiving fuel nozzles, for mixing fuel and
air together and for containing the reaction when the fuel and air
mixture is ignited.
[0007] Combustion liners of the prior art have met certain
performance requirements, but have also exhibited various
shortcomings. For example, prior combustion liners have been
primarily or exclusively welded assemblies, thereby making it
difficult for operators or repair facilities to access all of the
features of the combustion liner to be repaired. Furthermore, prior
combustor designs of similar structure were capable of operating
approximately 8,000 hours prior to refurbishment or replacement. In
an effort to improve gas turbine engine efficiency, there is a
strong desire in the operator community to be able to extend the
timeframe between repairs, so as to reduce engine downtime and
repair/overhaul costs.
SUMMARY
[0008] In accordance with the present invention, there is provided
a novel and improved swirler assembly for use in a combustion liner
of a gas turbine engine. The swirler assembly is removable and
sized to provide an improved assembly, repairability, and fit-up in
the combustion liner. A plurality of main swirler assemblies are
located in a combustion liner about a central axis and sized to
receive a plurality of fuel nozzles.
[0009] In accordance with an embodiment of the present invention,
there is provided a swirler assembly for a gas turbine combustor
comprising a premix tube, a premix swirler positioned within the
premix tube, a first mounting block positioned along an outer wall
of the premix tube proximate an inlet end and having a plurality of
first holes, and a second mounting block also positioned along the
outer wall of the premix tube, the second mounting block spaced a
distance from the first mounting block and having one or more
second holes perpendicular to the plurality of first holes.
[0010] In accordance with another embodiment of the present
invention, there is provided a multi-point, multi-directional
fastening assembly for use in a gas turbine combustor comprising a
first mounting block secured to a body with the first mounting
block having a forward face, an opposing aft face, generally
parallel side faces, an arc-shaped outer face and a plurality of
holes located in the arc-shaped outer face. The fastening assembly
also comprises a second mounting block secured to the body and
having one or more holes, where the plurality of holes in the first
mounting block are oriented generally perpendicular to the one or
more holes in the second mounting block.
[0011] In accordance with yet another embodiment of the present
invention there is provided a removable swirler assembly in a
combustor comprising a generally cylindrical body, a center core
and a plurality of vanes extending between the center core and the
generally cylindrical body. The removable swirler assembly also
comprises a first mounting block secured to the generally
cylindrical body where the first mounting block having a forward
face, an opposing aft face, generally parallel side faces, an
arc-shaped outer face and a plurality of holes located in the
arc-shaped outer face. The removable swirler assembly also
comprises a second mounting block secured to the body and having
one or more holes, where the removable swirler is fastened to the
combustor at both the first and second mounting blocks through a
plurality of removable fasteners.
[0012] Additional advantages and features of the present invention
will be set forth in part in a description which follows, and in
part will become apparent to those skilled in the art upon
examination of the following, or may be learned from practice of
the invention. The instant invention will now be described with
particular reference to the accompanying drawings.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS
[0013] The present invention is described in detail below with
reference to the attached drawing figures, wherein:
[0014] FIG. 1 is a partial cross section view of a gas turbine
engine of the prior art in which a combustion system in accordance
with an embodiment of the present invention is capable of being
used;
[0015] FIG. 2 is a cross section view of a gas turbine combustor of
the prior art capable of operating within the gas turbine engine of
FIG. 1;
[0016] FIG. 3 is a perspective view of a combustion liner
incorporating an embodiment of the present invention;
[0017] FIG. 4 is a cross section view of a combustion liner
incorporating an embodiment in accordance with an embodiment of the
present invention;
[0018] FIG. 5 is an alternate view of the cross section of FIG. 4,
incorporating an embodiment of the present invention;
[0019] FIG. 6 is a cross section view of a combustion liner taken
through the swirler assembly in accordance with an embodiment of
the present invention;
[0020] FIG. 7 is an alternate view of the cross section of FIG. 6,
in accordance with an embodiment of the present invention;
[0021] FIG. 8 is a perspective view of a swirler assembly portion
of the combustion liner of FIG. 3 in accordance with an embodiment
of the present invention;
[0022] FIG. 9 is a detailed cross section view taken through an
inlet portion of the combustion liner of FIG. 3 including a cross
section of the swirler assembly in accordance with an embodiment of
the present invention; and,
[0023] FIG. 10 is a partial cross section view of the swirler
assembly of the combustion liner in accordance with an embodiment
of the present invention.
DETAILED DESCRIPTION
[0024] The subject matter of the present invention is described
with specificity herein to meet statutory requirements. However,
the description itself is not intended to limit the scope of this
patent. Rather, the inventors have contemplated that the claimed
subject matter might also be embodied in other ways, to include
different components, combinations of components, steps, or
combinations of steps similar to the ones described in this
document, in conjunction with other present or future
technologies.
[0025] Referring initially to FIG. 1, a gas turbine engine 100 of
the prior art is depicted in partial cross section. The gas turbine
engine 100 generally comprises an outer casing 102, enveloping the
main portions of the engine. A shaft 104 extends axially along an
engine axis A-A and is coupled to a compressor 106 and a turbine
108. The compressor 106 receives air through inlet region 110 and
directs the air through alternating rows of rotating and stationary
airfoils of decreasing size in order to compress the air as it
passes therethrough, thereby increasing the temperature and
pressure of the air. The compressed air is then directed through
one or more combustion systems 112 where fuel and air are mixed
together and ignited to form hot combustion gases. The hot
combustion gases are then directed into the turbine 108 and through
alternating rows of rotating and stationary airfoils of increasing
size, so as to expand the fluid and convert the energy of the
combustion gases into mechanical work to drive the shaft 104. The
shaft 104 may also be coupled to a shaft of an electrical generator
for purposes of generating electricity (not shown).
[0026] FIG. 2 discloses a cross section of a combustor 200 of a gas
turbine engine of the prior art. As such, this typical gas turbine
combustor 200 comprises a casing 202, a cover 204, one or more fuel
injectors 206, and a combustion liner 208. A transition piece 210
connects the combustion liner 208 to an inlet of the turbine
212.
[0027] The present invention is shown in detail in FIGS. 3-10 and
discloses a new and improved removable swirler assembly for use in
a combustor of a gas turbine engine. Referring initially to FIGS.
3-7, a combustion liner 300 having a removable swirler assembly 332
is disclosed. The combustion liner 300 comprises a generally
cylindrical liner body 302 having an inlet end 304, an outlet end
306, or discharge end, and an axis B-B extending through the
combustor. The combustion liner 300 is generally cylindrical in
cross section, but it is understood that the combustion liner 300
can vary in shape, have tapered sections, or sections of varying
diameter. The combustion liner 300 is generally fabricated from
rolled sheet metal that is welded along an axial seam and can be
formed or expanded into a modified cylindrical structure depending
on the specific combustion geometry. The combustion liner 300 is
preferably manufactured from a high temperature alloy, such as
Haynes 230, capable of withstanding elevated combustor conditions
upwards of approximately 1500 deg Fahrenheit. Alternate materials
can be used such as Hastelloy-X or Inconel.
[0028] The combustion liner 300 further comprises an inlet ring
basket 308 secured to the generally cylindrical body 302. The inlet
ring basket 308, as depicted in FIG. 3-7, consists of a series of
generally axially-oriented spindles 310 coupled to a forward ring
312 and extends forward from the inlet end 304 of the combustion
liner 300. The forward ring 312 is positioned a distance from the
combustion liner 300 in order to establish a mating location for a
set of fuel nozzles (not shown) in order to position the fuel
nozzles in the proper axial position within the combustor. The
inlet ring basket 308 can be a fabricated component or a casting
and is preferably made from a stainless steel material. Referring
now to FIG. 10, the inlet ring basket 308 also includes a plurality
of lugs 309 extending radially inward from the inlet ring basket
308 for use in securing a premixer assembly 330, as discussed in
more detail below. The lugs 309 can be fabricated separately and
welded to the inlet ring basket 308 or cast as part of the inlet
ring basket 308.
[0029] Referring to FIGS. 4-7, the combustion liner 300 also
comprises a premixer assembly 330. One component of the premixer
330 is one or more removable swirlers 332. Referring now to FIGS.
8-10, a swirler assembly 332 is depicted in the premixer assembly
330. The swirler assembly 332 comprises a premix tube 342 having an
inlet end 342A and an opposing outlet end 342B, and a longitudinal
axis C-C extending therethrough. The swirler assembly 332 also
comprises a premix swirler 336 positioned within the premix tube
342 where the premix swirler 336 has a plurality of turning vanes
338 for imparting a swirl to a passing flow through the premix tube
342. For the embodiment depicted in FIGS. 8-10, the premix tube 342
is generally cylindrical. However, alternate shapes for the premix
tube 342 are possible.
[0030] The swirler assembly 332 also comprises two mounting blocks
for securing the swirler assembly in a gas turbine combustor. A
first mounting block 344 is positioned along an outer wall of the
premix tube 342 proximate the inlet end 342A of the premix tube
342. The first mounting block 344 has a first forward face 344A, an
opposing first aft face 344B, a pair of generally parallel side
faces 345, and an outer face 347. The outer face 347 can have an
arc-like shape to it, at least along a portion of the outer face,
in order for the mounting block 344 to conform to the shape of the
inlet ring basket 308. The outer face 347 is used to set the radial
position of the swirler assembly 332 and its contact with the inlet
ring basket 308 to allow tighter dimensional control of the swirler
assembly 332 relative to a fuel nozzle. The first mounting block
344 also includes a plurality of first holes 348 located in the
arc-shaped outer face 347 and oriented generally perpendicular to
the longitudinal axis C-C of the premix tube 342, as shown in FIG.
8.
[0031] The swirler assembly 332 also comprises a second mounting
block 346 positioned along the outer wall of the premix tube 342
and spaced an axial distance from the first mounting block 344. The
second mounting block 346 has a second forward face 346A and an
opposing second aft face 346B, where the second aft face 346B is
machined to a predetermined size in order to form a specific axial
dimension for mounting the swirler assembly 332 in the proper axial
location in the combustor. To position the swirler assembly 332 in
the proper axial location, the second mounting block 346 includes a
relief cut 360 machined into the second aft face 346B. The second
mounting block 346 also has one or more second holes 356 extending
through the second mounting block 346 in a direction generally
perpendicular to the plurality of first holes 348.
[0032] For the embodiment of the present invention depicted in
FIGS. 8-10, the second mounting block 346 is in direct axial
alignment with the first mounting block 344. However, depending on
the combustor geometry, the first and second mounting blocks 344
and 346 may not be in axial alignment, but clocked
circumferentially relative to one another.
[0033] Each of the first mounting block 344 and second mounting
block 346 are secured to the premix tube 342. Different methods of
attachment for the mounting blocks are possible. In one embodiment,
the first mounting block 344 and second mounting block 346 are
welded to the premix tube 342. A bead of compatible weld material
(compatible between the material of premix tube 342 and the
mounting blocks 344 and 346) is laid down at the intersection of
the mounting block and the premix tube 342.
[0034] An alternate method of securing the first and second
mounting blocks 344 and 346 to the premix tube 342 is through a
braze joint. A braze joint will help form a more complete joint as
the entire surface of the mounting block in contact with the premix
tube 342 is joined to the premix tube 342. In contrast, a weld
joint only secures the mounting block to the premix tube 342 at the
edges where the mounting block contacts the premix tube.
[0035] In yet another embodiment, it is possible for the mounting
blocks 344 and 346 to be integral with the premix tube 342. The
incorporation of the mounting blocks 344 and 346 into the premix
tube 342 can be accomplished by a casting or forging.
[0036] The exact size, spacing and quantity of holes in the first
mounting block 344 and the second mounting block 346 can vary and
depends on a variety of factors such as combustor geometry, size of
the swirler assemblies 332, and mechanical and thermal loading on
the swirler assemblies 332. For an embodiment of the present
invention depicted in FIGS. 8-10, the first mounting block 344
comprises two first holes 348 with the first holes 348 oriented
generally perpendicular to the longitudinal axis C-C. The second
mounting block 346 comprises one or more second holes 356, and the
embodiment shown in FIGS. 8-10 utilizes a single second hole 356.
However, it is possible that more than one second hole 356 is
needed in order to secure the swirler assembly 342 to a combustor.
For the embodiment shown in FIGS. 8-10, the second hole 356 is
generally parallel to axis C-C.
[0037] As discussed above, the swirler assembly 332 is designed to
be easily removable from a combustor to better facilitate
maintenance and repair. Therefore, a plurality of removable
fasteners 350 and 358 are utilized to secure the swirler assembly
332 in the combustor. In one embodiment, the removable fasteners,
such as bolts, engage a corresponding thread pattern in the
plurality of first holes 348 and one or more second holes 356. A
thread pattern is but one way of securing the removable fasteners.
Alternatively, the one or more second holes 356 could be through
holes (i.e. not threaded) and utilize a nut adjacent to surface
346A. Furthermore, a bolt/stud could be welded/installed in lieu of
hole 356 with a nut then placed on the surface of the dome plate
334.
[0038] The swirler assemblies 332 are positioned so as to be in
fluid communication with adjacent tubes 352, also referred to as
hoovers, which pass the flow of fuel and air from the swirler
assembly 332 to the mixing zone of the combustion liner 300. That
is, the swirler assemblies 332 are positioned so as to be adjacent
to or slightly engaged in the tubes 352. In order to ensure that
the swirler assemblies 332 are in the proper radial position in the
combustion liner and form a radial clearance with the tubes 352, a
plurality of stand offs 354 are located about the outer surface of
each of the premix tubes 342, adjacent the outlet end 342B.
[0039] As discussed above, the swirler assemblies 332 are removably
secured to the combustor through a plurality of fasteners 350 and
358, such as bolts or other means. For example, and as shown in
FIGS. 6-10, the main swirler assemblies 332 are secured to the dome
plate 334 by way of fasteners 350 and 358 passing through first
holes 348 and second hole 356. Through the use of both radially and
axially oriented fasteners 350 and 358, better positioning and
tolerance control of the swirler assemblies 332 relative to the
premixer assembly 330 and combustion liner 300 is achieved.
Furthermore, through removably securing the swirler assemblies 332
to the premixer assembly 330, access for overhaul and repairs to
the premixer assembly 330 is vastly improved compared to prior art
combustors which had swirler assemblies welded to the premixer
assembly. As one skilled in the art will appreciate, in addition to
accessibility issues, welding of the swirler assemblies also causes
deformation of the swirler assemblies, which can thereby affect
flow control.
[0040] The swirler assemblies 332 are preferably manufactured from
a material comparable to the premixer assembly 330, such as a type
of stainless steel. The swirler assemblies 332 can also be a
fabricated assembly of various machined parts or a casting.
[0041] Referring now to FIGS. 9 and 10, a swirler assembly 332 is
shown installed within the premixer assembly 330. As discussed
above, the swirler assembly 332 is secured in position by fasteners
350 and 358, which are oriented in both a radial and axial
direction. The swirler assembly 332 is slid into position such that
the standoffs 354 provide a radial clearance with respect to the
tubes 352 and the second mounting block 346 contacts the lug 309 of
the inlet ring basket 308 at the proper axial location due to the
relief cut 360.
[0042] The present invention has been described in relation to
particular embodiments, which are intended in all respects to be
illustrative rather than restrictive. Alternative embodiments and
required operations will become apparent to those of ordinary skill
in the art to which the present invention pertains without
departing from its scope.
[0043] From the foregoing, it will be seen that this invention is
one well adapted to attain all the ends and objects set forth
above, together with other advantages which are obvious and
inherent to the system and method. It will be understood that
certain features and sub-combinations are of utility and may be
employed without reference to other features and sub-combinations.
This is contemplated by and within the scope of the claims.
* * * * *