U.S. patent application number 14/256023 was filed with the patent office on 2014-10-30 for premixer assembly for gas turbine combustor.
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 | 20140318139 14/256023 |
Document ID | / |
Family ID | 51788070 |
Filed Date | 2014-10-30 |
United States Patent
Application |
20140318139 |
Kind Code |
A1 |
METTERNICH; JEREMY ; et
al. |
October 30, 2014 |
PREMIXER ASSEMBLY FOR GAS TURBINE COMBUSTOR
Abstract
A novel and improved combustion liner for use in a gas turbine
engine is provided in which the premixer assembly is removably
fastened to the combustion liner. Apparatus and method for
removably securing the premixer assembly to the combustion liner is
provided. A combustor dome plate, swirler assembly and inlet ring
basket are coupled together by a plurality of removable fasteners
in order to increase accessibility to portions of the combustion
liner for inspection and repair processes.
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.: |
14/256023 |
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: |
60/755 ;
29/890.01 |
Current CPC
Class: |
F23R 3/60 20130101; F23R
2900/00017 20130101; F23R 2900/00005 20130101; F23R 3/286 20130101;
Y10T 29/49346 20150115; F23R 3/002 20130101 |
Class at
Publication: |
60/755 ;
29/890.01 |
International
Class: |
F23R 3/28 20060101
F23R003/28 |
Claims
1. A premixer assembly for a gas turbine combustor comprising: an
inlet ring basket having a plurality of lugs, with each of the lugs
having an opening extending therethrough; a plurality of swirler
assemblies each for receiving a fuel injector, the swirler
assemblies each 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 generally
perpendicular to the plurality of first holes; a dome plate spaced
an axial distance from the second mounting block of each of the
swirler assemblies, and oriented generally parallel to the second
mounting block, the dome plate having a plurality of cooling holes;
and, a plurality of fasteners; wherein the plurality of lugs are
positioned axially between the second mounting blocks of the
swirler assemblies and the dome plate and the plurality of
fasteners pass through the dome plate, the openings in the lugs and
the one or more second holes of the second mounting blocks.
2. The premixer assembly of claim 1, wherein the plurality of lugs
are integrally formed with the inlet ring basket.
3. The premixer assembly of claim 1, wherein each of the one or
more second holes corresponds to one of the plurality of lugs and
openings.
4. The premixer assembly of claim 1, wherein each of the swirler
assemblies is secured to the inlet basket by a plurality of
fasteners.
5. The premixer assembly of claim 4, wherein the plurality of
fasteners securing the swirler assemblies to the inlet ring basket
are oriented both parallel to and perpendicular to the longitudinal
axis of the premix tube of the swirler assemblies.
6. The premixer assembly of claim 1, wherein the holes in the dome
plate are oriented parallel to the longitudinal axis of the premix
tube.
7. The premixer assembly of claim 1, wherein the holes in the dome
plate are oriented at an angle relative to the longitudinal axis of
the premix tube.
8. The premixer assembly of claim 1, further comprising a plurality
of stand-offs positioned along the premix tube adjacent the outlet
end.
9. A method of assembling a premixer for a gas turbine combustor
comprising: providing a dome plate having a plurality of fastener
openings, an inlet ring basket having a plurality of lugs, each lug
having an opening extending therethrough, and a plurality of
swirler assemblies, the swirler assemblies each having a first and
second mounting block, with the first mounting block having a
plurality of first holes and the second mounting block having one
or more second holes; inserting the plurality of swirler assemblies
into the inlet ring basket; placing the dome plate in contact with
the plurality of lugs of the inlet ring basket; inserting the
swirler assemblies into corresponding cup openings in the dome
plate. aligning a fastener opening of the dome plate with the
opening of a lug and a second hole of the second mounting block;
placing a removable fastener through the fastener opening of the
dome plate, the opening of the lug and the second hole of the
second mounting block so as to secure the dome plate, lug and
second mounting block together.
10. The method of claim 9, wherein the plurality of dome mounting
holes are located in an annular array about a perimeter of the dome
plate.
11. The method of claim 10, wherein the dome plate further
comprises a plurality of cooling holes.
12. The method of claim 9, wherein the plurality of lugs are
positioned between the dome plate and the second mounting blocks of
the swirler assemblies.
13. The method of claim 9, wherein the one or more second holes in
the second mounting block is threaded.
14. The method of claim 9, wherein the swirler assemblies are
inserted into the corresponding cup openings such that the second
mounting blocks are in contact with the lugs of the inlet ring
basket.
15. The method of claim 14, wherein the swirler assemblies are
inserted in the corresponding cup openings such that a plurality of
stand-offs positioned along an outer surface of the premix tube
contact the dome plate.
16. The method of claim 9, wherein a tightening of the removable
fastener draws the second mounting block and the dome plate toward
the lug of the inlet ring basket.
17. An interface joint for coupling components of a premixer
assembly comprising: an inlet ring basket having a lug where the
lug has an opening extending therethrough; a swirler assembly
having a premix tube, a premix swirler positioned within the premix
tube, and a mounting block positioned along an outer wall of the
premix tube and having one or more holes extending through the
mounting block in a direction parallel to the premix tube; a dome
plate having a plurality of cooling holes; and, one or more
fasteners for securing the lug, mounting block and dome plate
together.
18. The interface joint of claim 17, wherein the inlet ring basket
has a plurality of lugs located in an annular array about the inlet
ring basket.
19. The interface joint of claim 17, wherein the plurality of
fasteners are removable.
20. The interface joint of claim 17, wherein the fasteners draw the
mounting block and the dome plate towards the lug of the inlet ring
basket.
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 REMOVABLE SWIRLER
ASSEMBLY FOR A COMBUSTION LINER (Attorney Docket No.
PSM-316/PSSF.199280) 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 premixer assembly for a gas turbine combustor, where the
premixer assembly is secured together by a plurality of removable
fasteners. As a result, the premixer assembly enhances combustor
performance and increases 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 easily 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 availability, 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 combustion liner for use in a gas turbine
engine. The combustion liner is generally cylindrical in shape and
has an inlet end and a discharge end, opposite the inlet end. The
combustion liner of the present invention further comprises a
premixer assembly which is removably fastened to the combustion
liner.
[0009] In accordance with an embodiment of the present invention,
there is provided a premixer assembly for a gas turbine combustor
comprising an inlet ring basket, a plurality of swirler assemblies
each having a premix tube, premix swirler in the premix tube, and a
first and second mounting block positioned along the premix tube, a
dome plate and a plurality of fasteners, where lugs of the inlet
ring basket are positioned between a mounting block of the swirler
assembly and the dome plate such that the fasteners pass through
the dome plate, openings in the lugs and a hole of the mounting
block so as to assemble the premixer.
[0010] In accordance with another embodiment of the present
invention, a method of assembling a premixer for a gas turbine
combustor is disclosed. A dome plate is provided having a plurality
of dome mounting holes, an inlet ring basket having a plurality of
lugs, and a plurality of swirler assemblies, each having at least
one mounting block and hole therein. The swirler assemblies are
then inserted into the inlet ring basket and loosely retained in
the radial direction by the first mounting block. The dome plate is
then placed into contact with the plurality of lugs and the swirler
assemblies are then inserted into the dome plate. The mounting
holes of the dome plate are aligned with corresponding openings in
the lugs and holes in the mounting block. A removable fastener is
then placed through the fastener opening of the dome plate, the
opening in the lug, and the hole in the mounting block so as to
secure the dome plate, lug (inlet ring basket) and mounting block
(swirler assembly) together.
[0011] In accordance with yet another embodiment of the present
invention, an interface joint for coupling components of a premixer
assembly is disclosed. The interface joint comprises a lug of an
inlet ring basket, a swirler assembly having a mounting block
positioned along an outer wall of the premix tube of the swirler
assembly, and a dome plate. One or more fasteners secure the lug,
mounting block, and dome plate together.
[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 in
accordance with an embodiment of the present invention;
[0017] FIG. 4 is a cross section view of a combustion liner taken
through a pilot swirler in accordance with an embodiment of the
present invention;
[0018] FIG. 5 is an alternate view of the cross section of FIG. 4,
in accordance with an embodiment of the present invention;
[0019] FIG. 6 is a cross section view of a combustion liner taken
through the main swirler 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 main swirler 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 the
inlet portion of the combustion liner of FIG. 3 in accordance with
an embodiment of the present invention;
[0023] FIG. 10 is a partial cross section view of the main swirler
portion of the combustion liner in accordance with an embodiment of
the present invention;
[0024] FIG. 11 is a detailed section view of the interface joint
for the premixer assembly in accordance with an embodiment of the
present invention; and,
[0025] FIG. 12 is a flow diagram of the steps for assembling a
premixer for a gas turbine combustor.
DETAILED DESCRIPTION
[0026] 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.
[0027] 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).
[0028] 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.
[0029] The present invention is shown in detail in FIGS. 3-12 and
discloses a new and improved premixer assembly for a combustion
liner of a gas turbine engine. Referring initially to FIGS. 3-7, a
combustion liner 300 having a premixer assembly 330 is disclosed.
The combustion liner 300 comprises a generally cylindrical liner
body 302 having an inlet end 304, an outlet, or discharge end 306,
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
1400 degrees Fahrenheit. Alternate materials can be used such as
Hastelloy-X or Inconel.
[0030] 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.
[0031] Referring now to FIGS. 9 and 10, the inlet ring basket 308
also comprises a plurality of lugs 309 located in an annular array
about the inlet ring basket 308, with each of the lugs 309 having
an opening 309A extending through the lug 309. The lugs 309 extend
radially inward from the inlet ring basket 308 and are used in part
for 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.
The plurality of lugs 309 can be a fabricated component or a
casting and is preferably made from a stainless steel material.
[0032] More specific details of the present invention are shown in
FIGS. 6-8, 10 and 11. In addition to the inlet ring basket 308
discussed above, the premixer assembly 330 also comprises a
plurality of swirler assemblies 332, each swirler assembly 332 for
receiving a fuel injector. 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 slightly conical, however,
alternate shapes for the premix tube 342 are possible.
[0033] 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 includes a plurality of first
holes 348 located in an outer face 347 and oriented generally
perpendicular to the longitudinal axis C-C of the premix tube 342,
as shown in FIG. 8.
[0034] 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 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.
[0035] A plurality of fasteners 350 and 358 are used to secure the
swirler assemblies 332 to the inlet basket 308. Fasteners 350 are
used to secure the swirler assemblies 332 to the inlet basket 308
via the first mounting block 344 where the fasteners 350 are
oriented generally perpendicular to the longitudinal axis C-C of
the swirler assemblies 332. Fasteners 358 are used to secure the
swirler assemblies 332 to the inlet basket 308 via the second
mounting block 346 where the fasteners 358 are oriented generally
parallel to the longitudinal axis C-C of the swirler assemblies
332.
[0036] The premixer assembly 330 also comprises a dome plate 334
spaced an axial distance from the second mounting block 346 of each
of the swirler assemblies 332. As shown in FIGS. 9-11, the dome
plate 334 is oriented generally parallel to the second mounting
block 346 and the plurality of lugs 309. The dome plate 334 is
positioned against a face of the lugs 309. The dome plate 334,
which can be more clearly seen in FIGS. 10 and 11, is a generally
cylindrical plate fabricated from a stainless steel. The exact
thickness of the plate can vary, but is approximately 0.350 inches
thick. The dome plate 334 also comprises a large opening 370 for
each swirler assembly 332 to pass therethrough, a series of
fastener openings 372 for each axial fastener 358 to pass through,
and a plurality of cooling holes 374. The dome plate 334 includes
numerous cooling holes 374 for directing a flow of compressed air
into the combustion zone of the combustion liner 300. For the dome
plate 334 shown in FIGS. 10 and 11, the cooling holes 374 are
oriented generally perpendicular to the dome plate 334 (the cooling
holes 374 are generally parallel to the longitudinal axis C-C of
the swirler assemblies 332). Alternatively, the cooling holes 374
could be oriented at a surface angle relative to the dome plate 334
as well as a compound angle in order to impart a swirl to the air
passing through the dome plate 334 or to improve the cooling
effectiveness through the dome plate 334. The exact quantity, size,
and shape of the cooling holes 374 can vary depending on the amount
of compressed air to be directed through the dome plate 334 as well
as to maintain a desired pressure drop into the combustion
zone.
[0037] Referring to FIG. 11, the plurality of lugs 309 of the inlet
ring basket 308 are positioned axially between the mounting blocks
346 of the swirler assemblies 332 and the dome plate 334. A
plurality of fasteners 358 pass through each of the fastener
openings 372 in the dome plate 334, through the openings 309A in
the lugs 309 and through a second hole 356 in the second mounting
block 346.
[0038] The main swirler assemblies 332 are positioned so as to be
in fluid communication with adjacent tubes 352, or hoovers, which
pass the flow of fuel and air from the main swirler assembly 332 to
the mixing zone of the combustion liner 300. That is, the main
swirler assemblies 332 are positioned so as to be adjacent to or
slightly engaged in the tubes 352. In order to ensure that the main
swirler assemblies 332 are in the proper radial position in the
combustion liner and dome plate 334 and thereby maintain a desired
radial clearance with the tubes 352, a plurality of stand offs 354
are located about the outer surface of the premix tubes 342.
[0039] The present invention also provides an interface joint for
coupling components of a premixer assembly 330. Referring to FIG.
11, the interface joint 400 comprises a lug 309 of an inlet ring
basket 308, where the lug 309 has an opening 309A extending through
the thickness of the lug 309. The interface joint 400 also includes
a swirler assembly 332 having a premix tube 342, a premix swirler
336 and a mounting block 346 having one or more holes 356 extending
through the mounting block 346 in a direction parallel to the
premix tube 342. A dome plate 334 also forms part of the interface
joint 400. More specifically, the dome plate 334, has a plurality
of cooling holes 374, fastener openings 372, and larger opening 370
for receiving the swirler assemblies 332, as discussed above. The
interface joint 400 also includes one or more removable fasteners
358 for securing the lug 309, mounting block 346, and dome plate
334 together. The fastener 358 draws the mounting block 346 and
dome plate 334 towards the lug 309 of the inlet ring basket
308.
[0040] Referring now to FIG. 12, the present invention also
provides a method 1200 of assembling a premixer for the gas turbine
combustor. The method comprises the step 1202 of providing the
components of the premixer including a dome plate having a
plurality of fastener openings, an inlet ring basket having a
plurality of lugs where each lug has an opening extending
therethrough, and a plurality of swirler assemblies having mounting
blocks with holes contained therein.
[0041] In a step 1204, the swirler assemblies are inserted into the
inlet ring basket and loosely affixed to the first mounting block.
Then, in a step 1206, the dome plate is placed in contact with the
plurality of lugs of the inlet ring basket and in a step 1208, the
swirler assemblies are inserted into the cup openings, or large
openings, of the dome plate 334. Then, in a step 1210, the fastener
opening in the dome plate, the opening in the lug, and the opening
in the mounting block of the swirler assembly are all aligned
together. For the embodiment shown in FIGS. 10 and 11, the swirler
assembly has two mounting blocks, and for this embodiment, it is
the second, or aft-most mounting block that is used this assembly
process.
[0042] Once the holes of the three components to be secured
together are aligned, in a step 1212, a removable fastener is
placed through the fastener opening in the dome plate, through the
opening in the lug, and through the hole in the mounting block, as
shown in FIG. 11. The removable fastener engages a series of
threads in the hole of the mounting block so as to secure the dome
plate, lug, and mounting block of a swirler assembly together. This
process is repeated for each of the fastener openings in the dome
plate, corresponding lugs and swirler assemblies such that the dome
plate and swirler assemblies are then bolted to the inlet ring
basket.
[0043] 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, such as machining of shroud faces other than
the hardface surfaces and operation-induced wear of the hardfaces,
will become apparent to those of ordinary skill in the art to which
the present invention pertains without departing from its
scope.
[0044] 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.
* * * * *