U.S. patent application number 14/709974 was filed with the patent office on 2015-12-03 for fuel nozzle assembly with removable components.
The applicant listed for this patent is SIEMENS AKTIENGESELLSCHAFT. Invention is credited to Jurgen Buchheim, Thomas Hauser, Stephen A. Ramier.
Application Number | 20150345793 14/709974 |
Document ID | / |
Family ID | 53442988 |
Filed Date | 2015-12-03 |
United States Patent
Application |
20150345793 |
Kind Code |
A1 |
Ramier; Stephen A. ; et
al. |
December 3, 2015 |
FUEL NOZZLE ASSEMBLY WITH REMOVABLE COMPONENTS
Abstract
A fuel nozzle assembly (10) for a gas turbine engine (12) is
provided. The fuel nozzle assembly (10) includes a rocket unit (14)
and a flow-guiding element, such as may include swirler elements,
non-swirler elements, or a combination of swirler elements and
non-swirler elements, with an aft end (18) in threaded engagement
with a forward end (20) of the rocket unit (14). The fuel nozzle
assembly (10) may include an oil tip (36) including a clocking
feature with a mechanical constraint to orient the oil tip (36) at
a predetermined angular orientation (42) relative to the swirler
(16). The fuel nozzle assembly (10) may include one or more gas
stage inlets (13, 15), one or more oil stage inlets (17, 19), and a
flexible hose (26) to direct the oil to a plurality of rocket units
(14).
Inventors: |
Ramier; Stephen A.;
(Fredericton, CA) ; Hauser; Thomas; (Honow,
DE) ; Buchheim; Jurgen; (Berlin, DE) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
SIEMENS AKTIENGESELLSCHAFT |
MUNCHEN |
|
DE |
|
|
Family ID: |
53442988 |
Appl. No.: |
14/709974 |
Filed: |
May 12, 2015 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
14294526 |
Jun 3, 2014 |
|
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14709974 |
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Current U.S.
Class: |
60/796 ; 60/740;
60/744 |
Current CPC
Class: |
F23R 3/38 20130101; F23R
2900/00019 20130101; F23R 3/60 20130101; F23R 3/283 20130101 |
International
Class: |
F23R 3/28 20060101
F23R003/28; F23R 3/38 20060101 F23R003/38 |
Claims
1. A fuel nozzle assembly of a gas turbine engine, comprising: a
flow-guiding element; and an oil tip including a clocking feature
with a mechanical constraint to orient the oil tip at a
predetermined angular orientation relative to the flow-guiding
element.
2. The fuel nozzle assembly of claim 1, further comprising a rocket
unit and an aft end of the flow-guiding element in threaded
engagement with a forward end of the rocket unit.
3. The fuel nozzle assembly of claim 2, further comprising an aft
end of an oil tube of the rocket unit threadably engaged to a
flexible hose to the rocket unit.
4. The fuel nozzle assembly of claim 1, wherein said clocking
feature includes: a plurality of lobes separated by an angular
interval around a circumference of a forward end of the
flow-guiding element; and a radial projection at an aft end of the
oil tip, said radial projection selectively received within one of
the lobes to orient the oil tip at the predetermined angular
orientation.
5. The fuel nozzle assembly of claim 1, further comprising a seal
positioned between an annular surface of a forward end of the
flow-guiding element and a surface of an aft end of the oil tip,
wherein the seal is compressed by a predetermined amount based on
contact between the surface and a step of the flow-guiding element
positioned outside and forward of the annular surface.
6. The fuel nozzle assembly of claim 5, further including a nut
with a central opening to secure the oil tip; wherein the nut
includes internal threads in threaded engagement with external
threads on the forward end of the flow-guiding element to initiate
the contact between the surface and the step.
7. The fuel nozzle assembly of claim 6, wherein a forward end of
the nut includes a plurality of fingers separated by axial slots
such that the fingers are radially adjustable to engage an annular
ramp at the aft end of the oil tip.
8. The fuel nozzle assembly of claim 1, wherein the flow-guiding
element comprises a non-swirler element.
9. The fuel nozzle assembly of claim 1, wherein the flow-guiding
element comprises a swirler element.
10. The fuel nozzle assembly of claim 1, wherein the flow-guiding
element comprises a combination of at least one non-swirler element
and at least one swirler element.
Description
[0001] This application claims benefit of the Jun. 3, 2014 filing
date of U.S. application Ser. No. 14/294,526 which is incorporated
by reference herein.
FIELD OF THE INVENTION
[0002] The invention relates to gas turbine engines, and more
particularly to a fuel nozzle assembly of a combustor of a gas
turbine engine.
BACKGROUND OF THE INVENTION
[0003] FIG. 1 illustrates a conventional fuel nozzle assembly 110
for a gas turbine engine. The fuel nozzle assembly 110 includes
various components that are welded or brazed together, such as oil
tips 136 that are welded to swirlers 116, where the oil tips 136
have a predetermined angular orientation, for optimal oil
atomization and combustion performance. Additionally, the swirlers
116 are welded to rocket units 114, where the swirlers 116 have a
predetermined angular orientation, for optimal aerodynamics.
However, in the event that repair or replacement of the oil tips
136 or the swirlers 136 is needed, one or more of these welded
connections must be dismantled, necessitating a complete
disassembly and reassembly of the entire fuel nozzle assembly 110,
and involving extensive cost and turnaround time.
BRIEF DESCRIPTION OF THE DRAWINGS
[0004] The invention is explained in the following description in
view of the drawings that show:
[0005] FIG. 1 is a cross-sectional side view of a conventional fuel
nozzle assembly used in a gas turbine engine;
[0006] FIG. 2 is a side perspective view of a fuel nozzle assembly
of a gas turbine engine;
[0007] FIGS. 3A-3B are cross-sectional side views of a rocket
unit-swirler interface of the fuel nozzle assembly of FIG. 2;
[0008] FIG. 3C is a cross-sectional end view of the rocket
unit-swirler interface of FIG. 3B along the line 3C-3C;
[0009] FIG. 4 is a cross-sectional side view of a fuel
nozzle-rocket unit interface of a fuel nozzle assembly used in a
gas turbine engine;
[0010] FIG. 5 is a cross-sectional side view of a swirler-oil tip
interface of the fuel nozzle assembly of FIGS. 3A-3B; and
[0011] FIG. 6 is an exploded view of the swirler-oil tip interface
of FIG. 5.
DETAILED DESCRIPTION OF THE INVENTION
[0012] Based on the above-discussed limitations of the conventional
fuel nozzle assembly 110, the inventors recognized that if the oil
tips and the swirlers were more easily removable from the fuel
nozzle assembly, the oil tips or the swirlers could be repaired or
replaced without the need to disassemble and reassemble the entire
fuel nozzle assembly. Thus, the inventors recognized that removable
oil tips and removable swirlers would significantly reduce the
repair or replacement cost and turnaround time. Based on these
recognitions, the inventors developed structural features for each
of the oil tips and swirlers, to removably secure the oil tips and
the swirlers within the fuel nozzle assembly. Additionally, in
order to maintain the oil tips and the swirlers at their respective
predetermined angular orientation, the inventors developed a
respective clocking feature, to ensure that the oil tips and the
swirlers are oriented at their respective predetermined angular
orientation, when removably secured within the fuel nozzle
assembly. It will be appreciated that aspects of disclosed
embodiments are not limited to flow-guiding elements comprising
swirler elements (swirlers) since non-swirler elements could also
be used, depending on the needs of a given application. For
example, certain embodiments may include flow-guiding elements
comprising non-swirler elements in combination with (or in lieu of)
swirlers. Accordingly, without limitation, aspects of the present
invention, such as the foregoing structural features, as may
include clocking features, may be used with flow-guiding elements
comprising swirler elements, non-swirler elements, or a combination
of one or more swirler elements and one or more non-swirler
elements.
[0013] FIG. 2 illustrates a fuel nozzle assembly 10 for a gas
turbine engine 12. The gas turbine engine 12 is capable of
operation on a gas or oil feed such that the fuel nozzle assembly
10 includes a pair of gas stage inlets 13, 15, for use when the
engine operates in a gas mode and a pair of oil stage inlets 17,
19, for use when the engine operates in an oil mode. However, the
embodiments of the present invention are not limited to dual-fuel
nozzles, and are applicable to single-fuel gas turbine engines,
such as gas or oil turbine engines, for example. Flexible hosing 26
is used to connect the oil stage inlets 17, 19 to a plurality of
staged rocket units 14 through a cover plate 21. In an exemplary
embodiment, the flexible hosing 26 may be made from stainless steel
316L material, for example. A plurality of flow-guiding elements,
such as swirlers 16 are removably connected to the rocket units 14,
in a manner discussed in greater detail below, to receive fuel from
the rocket units 14 and to deliver a swirled mixture of air and
fuel to a combustion chamber (not shown). As noted above, the
flow-guiding elements may be non-swirler elements in combination
with (or in lieu of) swirlers. In the specific embodiment of FIG.
2, eight staged rocket units 14 and eight staged swirlers 16 are
provided in two stages and thus four pieces of flexible hosing 26
connect each oil stage inlet 17, 19 to four rocket units 14 of each
stage. However, this specific staged arrangement is exemplary and
the embodiments of the present invention are not limited to any
specific number of rocket units or stages in a fuel nozzle
assembly.
[0014] FIGS. 3A-3C illustrate an interface between a forward end 20
of the rocket unit 14 and an aft end 18 of the swirler 16 of the
fuel nozzle assembly 10. As illustrated in FIG. 3B, the interface
between the rocket unit 14 and the swirler 16 includes a flat
portion 58 of the aft end 18 of the swirler 16 engaged with an
inner surface of a flat portion 59 of the forward end 20 of the
rocket unit 14. FIG. 3C illustrates a cross-sectional end view of
this interface, with the flat portion 58 of a circumference 56 of
the swirler 16 radially oriented with the flat portion 59 of a
circumference 57 of the rocket unit 14. Thus, the flat portions 58,
59 acts as a clocking feature with a mechanical constraint, to
orient the swirler 16 at a predetermined angular orientation 54
(FIG. 2) relative to the rocket unit 14. In an exemplary
embodiment, the flat portions 58, 59 orient the swirler 16 within
an angular tolerance of the predetermined angular orientation 54,
such as within +/-1 degree, for example. As illustrated in FIG. 3C,
the diameter of the flat portion 59 of the forward end 20 of the
rocket unit 14 exceeds the diameter of the flat portion 58 of the
aft end 18 of the swirler 16 by a radial clearance 61. In an
exemplary embodiment, the radial clearance 61 is less than a
threshold clearance, such that the flat portions 58, 59 act as the
mechanical constraint to maintain the radial orientation of the
swirler 16 at the predetermined angular orientation 54 (FIG. 2).
The flat portion 58 around the circumference 56 of the aft end 18
of the swirler 16 is radially aligned with a flat portion 63 (FIG.
2) around a circumference of an outer surface of the swirler 16. As
illustrated in FIG. 2, the predetermined angular orientation 54 of
the swirler 16 aligns the flat portion 63 on the outer surface of
the swirler 16 with a flat portion 60 on an outer surface of an
adjacent swirler 16, such that the plurality of swirlers 16 align
and fit within the radial plane of the fuel nozzle assembly 10.
Additionally, as illustrated in FIG. 2, the predetermined angular
orientation 54 of the swirler 16 orients the vanes 23 of the
swirler 16 at predetermined radial positions, for enhanced
aerodynamics. Although FIG. 3C depicts that the swirler 16 is
aligned in the predetermined angular orientation 54 by aligning the
flat portions 58, 59 of the swirler 16 and the rocket unit 14, the
embodiments of the present invention may utilize any type of
clocking feature with a mechanical constraint, to orient the
swirler 16 at the predetermined angular orientation 54.
[0015] After aligning the swirler 16 at the predetermined angular
orientation 54, the swirler 16 is removably secured to the rocket
unit 14. As illustrated in FIGS. 3A-3B, the aft end 18 of the
swirler 16 includes an outer radial lip 66 from which the flat
portion 58 extends a distance 71 aft to a tip 72. The forward end
20 of the rocket unit 14 includes an inner radial lip 70 from which
the flat portion 59 extends a distance 73 forward to a tip 68. As
illustrated in FIG. 3B, the distance 71 is greater than the
distance 73. A seal 64, such as a C-seal, for example, is
positioned between the tip 68 of the forward end 20 of the rocket
unit 14 and the outer radial lip 66 of the aft end 18 of the
swirler 16. The gas passage between the rocket unit 14 and the
swirler 16 is sealed with the C-seal 64. Additionally, vibrations
at the interface of the rocket unit 14 and the swirler 16 during
operation of the fuel nozzle assembly 10 are absorbed over the
distance 73, due to the small radial clearance 61, i.e. the swirler
16 does not vibrate independent of the rocket unit 14. The seal 64
is compressed by a predetermined amount, when the tip 72 of the aft
end 18 of the swirler 16 makes contact with the inner radial lip 70
of the forward end 20 of the rocket unit 14. In an exemplary
embodiment, during a casting or machining of the swirler 16 and the
rocket unit 14, the distances 71, 73 may be subject to a tight
control tolerance, such that the seal 64 is compressed by the
predetermined amount when the tip 72 makes contact with the inner
radial lip 70. In order to move the tip 72 of the aft end 18 of the
swirler 16 in an aft direction and into contact with the inner
radial lip 70, a nut 44 is provided in threaded engagement with the
forward end 20 of the rocket unit 14. As illustrated in FIG. 3B, an
inner radial lip 74 of the nut 44 contacts a forward side of the
outer radial lip 66, so that upon threaded engagement of the nut 44
with the forward end 20 of the rocket unit 14, the tip 72 of the
aft end 18 of the swirler 16 moves into contact with the inner
radial lip 70. As further illustrated in FIG. 3B, the nut 44
includes internal threads 46 that are in threaded engagement with
external threads 48 on the forward end 20 of the rocket unit 14.
Additionally, as illustrated in FIG. 3A, the nut 44 includes flat
portions 45 along an outer surface, such that the nut 44 can be
tightened by a wrench or a similar tightening tool, for example.
The nut 44 engages the forward end 20 of the rocket unit 14, until
the tip 72 of the aft end 18 of the swirler 16 makes contact with
the inner radial lip 70 of the forward end 20 of the rocket unit
14, indicating that the seal 64 is compressed by the predetermined
amount. Additionally, to prevent disengagement of the nut 44 from
the rocket unit 14 during operation of the gas turbine engine 12, a
tack weld 47 may be applied between an aft tip of the nut 44 and
the rocket unit 14, as illustrated in FIG. 3B.
[0016] FIGS. 3A-3B illustrate an oil tube 32 and an oil tip 36 that
are used to pass oil through the fuel nozzle assembly 10 operating
in an oil fuel mode. However, when the fuel nozzle assembly 10 is
single-fuel and operates in a single gas mode, the oil tube 32 and
the oil tip 36 are not present, since oil is not passed through the
fuel nozzle assembly 10. When the fuel nozzle assembly 10 operates
in the single gas mode, and the swirler 16 of the fuel nozzle
assembly 10 requires repair or replacement, the swirler 16 is
removed from the fuel nozzle assembly 10 with the following steps.
The tack weld 47 is first removed. The nut 44 is then disengaged
from the forward end 20 of the rocket unit 14, by disengaging the
internal threads 46 of the nut 44 from the external threads 48 on
the forward end 20. The swirler 16 can then be removed from the
forward end 20 of the rocket unit 14 and either repaired or
replaced with a substitute swirler.
[0017] When the fuel nozzle assembly 10 operates in a single oil
mode or in the dual-fuel mode, the oil tube 32 and the oil tip 36
are present within the fuel nozzle assembly 10. Before the swirler
16 can be removed from the dual-fuel or the single oil mode fuel
nozzle assembly 10, disengagement of the oil tube 32 from the fuel
nozzle assembly 10 is initially performed and will now be
discussed. FIG. 4 depicts an aft end 22 of the oil tube 32 that is
welded to an oil tube extension 33. A seal 34 is positioned between
an aft end of the oil tube extension 33 and a forward surface of an
inner radial lip 29 of a compression fitting 28. An extension screw
30 engages an aft surface of the inner radial lip 29 of the
compression fitting 28 and engages internal threads within the oil
tube extension 33, to move the oil tube extension 33 aft and
compress the seal 34 between the aft end of the oil tube extension
33 and the inner radial lip 29 of the compression fitting 28, to
form a sealed interface. In an exemplary embodiment, the aft end of
the oil tube extension 33 may include a pocket to receive the seal
34. In an exemplary embodiment, the extension screw 30 may have a
hexalobular internal drive feature with a hole through the center,
to allow oil to pass through, for example. In another exemplary
embodiment, the seal 34 may be a flat washer, for example. After
the seal 34 is compressed between the oil tube extension 33 and the
compression fitting 28, a connection 27 of the flexible hose 26
(FIG. 2) is engaged with the compression fitting 28, to connect the
flexible hose 26 via. compression style fitting.
[0018] When the fuel nozzle assembly 10 is operating in the single
oil mode or the dual-fuel mode, the swirler 16 may need repair or
replacement. Initially, the oil tube 32 is disengaged from the fuel
nozzle assembly 10 by the following steps. The flexible hose
connection 27 is disengaged from the compression fitting 28, by
disengaging the internal threads 31 on the flexible hose connection
27 from the external threads 39 on the compression fitting 28. This
step provides access to the extension screw 30, which is then
disengaged from the oil tube extension 33. The oil tube 32 and the
oil tube extension 33 are now disengaged from the fuel nozzle
assembly 10 and may be removed along with the swirler 16 that
requires repair or replacement. Upon repairing or replacing the
swirler 16, the oil tube 32 and oil tube extension 33 may be
reconnected to the fuel nozzle assembly 10 by engaging the
extension screw 30 within the oil tube extension 33 until the seal
34 is compressed and subsequently engaging the flexible hose
connection 27 with the compression fitting 28.
[0019] FIG. 5 illustrates the oil tip 36 removably secured to the
swirler 16 in the fuel nozzle assembly 10. In addition to the
swirler 16, the oil tip 36 is removable from the fuel nozzle
assembly 10, in the event that repair or replacement of the oil tip
36 is required. The oil tip 36 may be removed for repair or
replacement, irrespective of whether the swirler 16 requires repair
or replacement. The oil tip 36 is removably secured to the swirler
16 using the following steps. As illustrated in FIG. 6, the oil tip
36 is initially passed through a central opening 89 in a nut 88,
until a plurality of fingers 94 at a forward end 93 of the nut 88
engage an annular ramp 96 at an aft end 83 of the oil tip 36. The
fingers 94 are separated by axial slots 95, such that the fingers
94 are radially adjustable to expand over and engage the annular
ramp 96. After the oil tip 36 is secured within the nut 88, the oil
tip 36 is radially oriented using a clocking feature with a
mechanical constraint to orient the oil tip 36 at a predetermined
angular orientation 42 relative to the swirler 16. The oil tip 36
is radially aligned such that a radial projection 82 of the oil tip
36 is received within one of a plurality of lobes 78 spaced by an
angular interval 79 on a forward end 81 of the swirler 16,
resulting in the predetermined angular orientation 42 of the oil
tip 36. In the exemplary embodiment of FIGS. 5-6, twelve lobes 78
are separated by an angular interval 79 of 30 degrees, such that
the oil tip 36 can be oriented in 30 degree increments, for
example. However, the embodiments of the present invention are not
limited to any specific number of lobes or angular interval. In
another exemplary embodiment, the lobes 78 are spaced within an
angular tolerance of each angular interval 79, such as within +/-1
degree, for example. As illustrated in FIG. 5, the oil tip 36
defines an opening 43 with radial holes 41 to direct the oil for
atomization during operation of the fuel nozzle assembly 10. As
appreciated by one skilled in the art, the radial holes 41 may be
asymmetrically arranged within the opening 43, such that ideal
atomization of the oil occurs at a predetermined angular
orientation. After the radial projection 82 is received within the
appropriate lobe 78 on the forward end 81 of the swirler 16, the
oil tip 36 is angularly fixed at the predetermined angular
orientation 42. The nut 88 is then engaged with the forward end 81
of the swirler 16, such that internal threads 90 of the nut 88
engage with external threads 92 on the forward end 81 of the
swirler 16. As the nut 88 is engaged with the forward end 81 of the
swirler 16, a surface 86 (FIG. 6) of the oil tip 36 moves and makes
contact with a seal 84 positioned between an annular surface 85 of
the forward end 81 and the oil tip 36. As the surface 86 continues
to move, the seal 84 is axially compressed along the annular
surface 85. The seal 84 is compressed by a predetermined amount
when the surface 86 makes contact with a step 87 of the forward end
81 that is positioned outside and forward of the annular surface
85. A height of the step 87 above the annular surface 85 controls
the predetermined amount at which the seal 84 is compressed. When
the seal 84 is compressed by the predetermined amount, a forward
tip of the oil tube 32 (FIG. 5) is aligned with an inlet of the
opening 43 of the oil tip 36. The forward tip of the oil tube 32 is
sealed to an inner surface of the swirler 16, in a similar manner
as appreciated by one skilled in the art. An aft end 97 of the nut
88 may be crimped within a groove 99 along the swirler 16 outer
surface to secure the nut 88 and the oil tip 36 to the forward end
81 of the swirler 16. The crimping of the aft end 97 may be
performed with a crimping tool that is known to one skilled in the
art.
[0020] In the event that the oil tip 36 requires re-alignment,
repair or replacement, the following steps may be employed. The aft
end 97 of the nut 88 is initially de-crimped from the groove 99
along the swirler 16. The nut 88 is then disengaged from the
forward end 81 of the swirler 16, which causes the surface 86 of
the oil tip 36 to move forward from the annular surface 85 and
decompression of the seal 84. The radial projection 82 moves out of
the selective lobe 78 during the threaded disengagement of the nut
88. If the oil tip 36 needs to be realigned, then upon threaded
disengagement of the nut 88 from the forward end 81, the oil tip 36
may be realigned relative to the swirler 16, by aligning the radial
projection 82 with the appropriate lobe 78 and subsequently
rethreading the nut 88 along the forward end 81 of the swirler 16.
If the oil tip 36 requires repair or replacement, the oil tip 36
may be removed from the nut 88 and repaired or replaced with a
substitute oil tip. The repaired or replaced oil tip may then be
secured to the nut 88 and the swirler 16 using the above steps.
[0021] While various embodiments have been shown and described
herein, it will be appreciated that such embodiments are provided
by way of example only. Numerous variations, changes and
substitutions may be made without departing from the invention
herein. Accordingly, it is intended that the invention be limited
only by the spirit and scope of the appended claims.
* * * * *