U.S. patent application number 15/378291 was filed with the patent office on 2018-06-14 for fuel nozzle assembly with inlet flow conditioner.
The applicant listed for this patent is General Electric Company. Invention is credited to Donald Mark Bailey, David William Cihlar, Lucas John Stoia.
Application Number | 20180163968 15/378291 |
Document ID | / |
Family ID | 62489958 |
Filed Date | 2018-06-14 |
United States Patent
Application |
20180163968 |
Kind Code |
A1 |
Bailey; Donald Mark ; et
al. |
June 14, 2018 |
Fuel Nozzle Assembly with Inlet Flow Conditioner
Abstract
A combustor includes an inlet flow conditioner having a sleeve
and a conditioner plate. The conditioner plate defines a plurality
of apertures. The sleeve extends axially from the conditioner plate
to a forward plate of a nozzle segment. The sleeve, the conditioner
plate and the forward plate define an inlet flow plenum. The inlet
flow plenum is in fluid communication with an inlet of a tube that
defines a premix passage of the nozzle segment.
Inventors: |
Bailey; Donald Mark;
(Simpsonville, SC) ; Cihlar; David William;
(Greenville, SC) ; Stoia; Lucas John; (Taylors,
SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
62489958 |
Appl. No.: |
15/378291 |
Filed: |
December 14, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/286 20130101;
F23R 3/10 20130101 |
International
Class: |
F23R 3/28 20060101
F23R003/28; F23R 3/10 20060101 F23R003/10 |
Claims
1. A combustor, comprising: an inlet flow conditioner including a
sleeve and a conditioner plate defining a plurality of apertures,
wherein the sleeve extends axially from the conditioner plate to a
forward plate of a nozzle segment, wherein the sleeve, the
conditioner plate and the forward plate define an inlet flow
plenum, and wherein the inlet flow plenum is in fluid communication
with an inlet of a tube that defines a premix passage of the nozzle
segment.
2. The combustor as in claim 1, further comprising a head end
volume at least partially defined between an endcover and the
conditioner plate, wherein the inlet flow plenum is in fluid
communication with the head end volume via the plurality of
apertures.
3. The combustor as in claim 1, wherein at least one aperture of
the plurality of apertures is non-round.
4. The combustor as in claim 1, where a first aperture of the
plurality of apertures has a diameter that is less than a diameter
of a second aperture of the plurality of apertures.
5. The combustor as in claim 1, wherein the conditioner plate is
wedge shaped.
6. The combustor as in claim 1, wherein the sleeve defines a
plurality of holes radially oriented and circumferentially spaced
around the sleeve, wherein the plurality of holes provide for fluid
communication into the inlet flow plenum.
7. The combustor as in claim 1, further comprising a fluid conduit
that extends axially through the conditioner plate, wherein the
fluid conduit provides fuel to the premix passage.
8. The combustor as in claim 1, wherein the nozzle segment further
comprises an aft plate axially spaced from the forward plate, an
outer band that extends between the forward plate and the aft
plate, and a fuel plenum defined between the forward plate and the
aft plate, wherein the tube extends through the forward plate, the
fuel plenum and the aft plate.
9. The combustor as in claim 7, wherein the tube is in fluid
communication with the fuel plenum.
10. A combustor, comprising: an inlet flow conditioner including a
sleeve and a conditioner plate defining a plurality of apertures,
wherein the sleeve extends axially from the conditioner plate to a
forward plate of a fuel nozzle forming an inlet flow plenum
therein, and wherein the inlet flow plenum is in fluid
communication with a plurality of premix passages defined by a
plurality of tubes of the fuel nozzle.
11. The combustor as in claim 10, further comprising a head end
volume at least partially defined between an endcover and the
conditioner plate, wherein the inlet flow plenum is in fluid
communication with the head end volume via the plurality of
apertures.
12. The combustor as in claim 10, wherein at least one aperture of
the plurality of apertures is non-round.
13. The combustor as in claim 10, where a first aperture of the
plurality of apertures has a diameter that is less than a diameter
of a second aperture of the plurality of apertures.
14. The combustor as in claim 10, wherein the conditioner plate is
circular shaped.
15. The combustor as in claim 10, wherein the sleeve defines a
plurality of holes radially oriented and circumferentially spaced
around the sleeve, wherein the plurality of holes provide for fluid
communication into the inlet flow plenum.
16. The combustor as in claim 10, further comprising a fluid
conduit that extends axially through the conditioner plate, wherein
the fluid conduit provides fuel to the fuel nozzle and each premix
passage of the plurality of premix passages.
17. The combustor as in claim 10, wherein the fuel nozzle further
comprises an aft plate axially spaced from the forward plate, an
outer band that extends between the forward plate and the aft
plate, and a fuel plenum defined between the forward plate and the
aft plate, wherein the tube extends through the forward plate, the
fuel plenum and the aft plate.
18. The combustor as in claim 17, wherein each tube is in fluid
communication with the fuel plenum.
19. The combustor as in claim 10, further comparing a plurality of
nozzle segments annularly arranged around the fuel nozzle, wherein
each nozzle segment includes a sleeve and a conditioner plate
defining a plurality of apertures, wherein the sleeve extends
axially from the conditioner plate to a forward plate, wherein the
sleeve, the conditioner plate and the forward plate define an inlet
flow plenum, and wherein the inlet flow plenum is in fluid
communication with a plurality of premix passages defined by a
plurality of tubes of the nozzle segment.
Description
FIELD OF THE TECHNOLOGY
[0001] The present invention generally involves a combustor for a
gas turbine. More specifically, the invention relates to a system
for mitigating non-uniform flow upstream from an inlet to a premix
passage of a fuel nozzle.
BACKGROUND
[0002] During operation of a gas turbine engine, pressurized air
from a compressor flows into a head end volume defined within the
combustor. The pressurized air flows from the head end volume into
an inlet to a corresponding premix passage of a respective fuel
nozzle. Fuel is injected into the flow of pressurized air within
the premix passage where it mixes with the pressurized air so as to
provide a fuel and air mixture to a combustion zone or chamber
defined downstream from the fuel nozzle. The flow of pressurized
air is typically non-uniform as it approaches the inlet to the
respective fuel nozzle which may be undesirable for efficient
combustor operations.
BRIEF DESCRIPTION OF THE TECHNOLOGY
[0003] Aspects and advantages are set forth below in the following
description, or may be obvious from the description, or may be
learned through practice.
[0004] One embodiment of the present disclosure is a combustor. The
combustor includes an inlet flow conditioner having a sleeve and a
conditioner plate. The conditioner plate defines a plurality of
apertures. The sleeve extends axially from the conditioner plate to
a forward plate of a nozzle segment. The sleeve, the conditioner
plate and the forward plate define an inlet flow plenum. The inlet
flow plenum is in fluid communication with an inlet of a tube that
defines a premix passage of the nozzle segment.
[0005] Another embodiment of the present disclosure is a combustor.
The combustor includes an inlet flow conditioner including a sleeve
and a conditioner plate. The conditioner plate defines a plurality
of apertures. The sleeve extends axially from the conditioner plate
to a forward plate of a fuel nozzle and forms an inlet flow plenum
therein. The inlet flow plenum is in fluid communication with a
plurality of premix passages which is defined by a plurality of
tubes of the fuel nozzle.
[0006] Those of ordinary skill in the art will better appreciate
the features and aspects of such embodiments, and others, upon
review of the specification.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] A full and enabling disclosure of the of various
embodiments, including the best mode thereof to one skilled in the
art, is set forth more particularly in the remainder of the
specification, including reference to the accompanying figures, in
which:
[0008] FIG. 1 is a functional block diagram of an exemplary gas
turbine that may incorporate various embodiments of the present
disclosure;
[0009] FIG. 2 is a simplified cross-section side view of an
exemplary combustor as may incorporate various embodiments of the
present disclosure;
[0010] FIG. 3 is an upstream view of an exemplary fuel nozzle
assembly according to at least one embodiment of the present
disclosure;
[0011] FIG. 4 is a cross-sectioned perspective view of an exemplary
nozzle segment according to at least one embodiment of the present
disclosure;
[0012] FIG. 5 is a perspective view of an exemplary conditioner
plate according to at least one embodiment of the present
disclosure;
[0013] FIG. 6 is a cross-sectioned perspective view of an exemplary
fuel nozzle according to at least one embodiment of the present
disclosure; and
[0014] FIG. 7 is a perspective view of an exemplary conditioner
plate according to at least one embodiment of the present
disclosure.
DETAILED DESCRIPTION
[0015] Reference will now be made in detail to present embodiments
of the disclosure, one or more examples of which are illustrated in
the accompanying drawings. The detailed description uses numerical
and letter designations to refer to features in the drawings. Like
or similar designations in the drawings and description have been
used to refer to like or similar parts of the disclosure.
[0016] As used herein, the terms "first," "second," and "third" may
be used interchangeably to distinguish one component from another
and are not intended to signify location or importance of the
individual components. The terms "upstream" and "downstream" refer
to the relative direction with respect to fluid flow in a fluid
pathway. For example, "upstream" refers to the direction from which
the fluid flows, and "downstream" refers to the direction to which
the fluid flows. The term "radially" refers to the relative
direction that is substantially perpendicular to an axial
centerline of a particular component, the term "axially" refers to
the relative direction that is substantially parallel and/or
coaxially aligned to an axial centerline of a particular component,
and the term "circumferentially" refers to the relative direction
that extends around the axial centerline of a particular
component.
[0017] The terminology used herein is for the purpose of describing
particular embodiments only and is not intended to be limiting. As
used herein, the singular forms "a", "an" and "the" are intended to
include the plural forms as well, unless the context clearly
indicates otherwise. It will be further understood that the terms
"comprises" and/or "comprising," when used in this specification,
specify the presence of stated features, integers, steps,
operations, elements, and/or components, but do not preclude the
presence or addition of one or more other features, integers,
steps, operations, elements, components, and/or groups thereof.
[0018] Each example is provided by way of explanation, not
limitation. In fact, it will be apparent to those skilled in the
art that modifications and variations can be made without departing
from the scope or spirit thereof. For instance, features
illustrated or described as part of one embodiment may be used on
another embodiment to yield a still further embodiment. Thus, it is
intended that the present disclosure covers such modifications and
variations as come within the scope of the appended claims and
their equivalents. Although exemplary embodiments of the present
disclosure will be described generally in the context of a
combustor for a land based power generating gas turbine for
purposes of illustration, one of ordinary skill in the art will
readily appreciate that embodiments of the present disclosure may
be applied to any style or type of combustor for a turbomachine and
are not limited to combustors or combustion systems for land based
power generating gas turbines unless specifically recited in the
claims.
[0019] Referring now to the drawings, FIG. 1 illustrates a
schematic diagram of an exemplary gas turbine 10. The gas turbine
10 generally includes a compressor 12, at least one combustor 14
disposed downstream of the compressor 12 and a turbine 16 disposed
downstream of the combustor 14. Additionally, the gas turbine 10
may include one or more shafts 18 that couple the compressor 12 to
the turbine 16.
[0020] During operation, air 20 flows into the compressor 12 where
the air 20 is progressively compressed, thus providing compressed
or pressurized air 22 to the combustor 14. At least a portion of
the compressed air 22 is mixed with a fuel 24 within the combustor
14 and burned to produce combustion gases 26. The combustion gases
26 flow from the combustor 14 into the turbine 16, wherein energy
(kinetic and/or thermal) is transferred from the combustion gases
26 to rotor blades (not shown), thus causing shaft 18 to rotate.
The mechanical rotational energy may then be used for various
purposes such as to power the compressor 12 and/or to generate
electricity. The combustion gases 26 may then be exhausted from the
gas turbine 10.
[0021] As shown in FIG. 2, the combustor 14 may be at least
partially surrounded by an outer casing 28 such as a compressor
discharge casing. The outer casing 28 may at least partially define
a high pressure plenum 30 that at least partially surrounds various
components of the combustor 14. The high pressure plenum 30 may be
in fluid communication with the compressor 12 (FIG. 1) so as to
receive the compressed air 22 therefrom. An endcover 32 may be
coupled to the outer casing 28. One or more combustion liners or
ducts 34 may at least partially define a combustion chamber or zone
36 for combusting the fuel-air mixture and/or may at least
partially define a hot gas path through the combustor 14 for
directing the combustion gases 26 towards an inlet 38 to the
turbine 16.
[0022] In particular embodiments, the combustion liner 34 is at
last partially circumferentially surrounded by a flow sleeve 40.
The flow sleeve 40 may be formed as a single component or by
multiple flow sleeve segments. The flow sleeve 40 is radially
spaced from the combustion liner 34 so as to define a flow passage
or annular flow passage 42 therebetween. The flow sleeve 40 may
define a plurality of inlets or holes 44 which provide for fluid
communication between the flow passage 42 and the high pressure
plenum 30. In particular embodiments, the endcover 32 and the outer
casing 28 at least partially define a head end volume or plenum 46
of the combustor 14. The head end volume 46 may be in fluid
communication with the high pressure plenum 30 via the flow passage
42. In various embodiments, as shown in FIG. 2, the combustor 14
includes a fuel nozzle assembly 48.
[0023] FIG. 3 provides an upstream view of an exemplary fuel nozzle
assembly 48 according to at least one embodiment of the present
disclosure. In particular embodiments, as shown in FIG. 3, the fuel
nozzle assembly 48 includes a plurality of nozzle segments 100
annularly arranged about a fuel nozzle or center fuel nozzle 200.
Although FIG. 3 illustrates four individual nozzle segments 100,
the combustor 14 may include two or more nozzle segments 100 and is
not limited to four nozzles segments 100 unless otherwise recited
in the claims. For example, in an exemplary embodiment, the fuel
nozzle assembly 48 may include five nozzle segments annularly
arranged around a center fuel nozzle 200. In other embodiments,
fuel nozzle assembly 48 may include just a single fuel nozzle 200.
As shown in FIG. 2, each of the nozzle segments 100 and/or the fuel
nozzle 200 may be coupled to the endcover 32 via one or more
conduits 50.
[0024] FIG. 4 provides a cross-sectioned perspective view of an
exemplary nozzle segment 100 according to at least one embodiment
of the present disclosure. As shown in FIG. 4, each nozzle segment
100 of the plurality of nozzle segments 100 includes a forward
plate 102, an aft plate 104 that is axially offset from the forward
plate 102 with respect to an axial centerline of the combustor 14
and an outer band 106 that at least partially defines a radially
outer perimeter of the nozzle segment 100. The outer band 106
extends from the forward plate 102 to the aft plate 104. A fuel
plenum 108 may be at least partially defined between the forward
plate 102, the aft plate 104 and the outer band 106.
[0025] A plurality of tubes 110 extends through the forward plate
102, the fuel plenum 108 and the aft plate 104. Each tube 110
includes an inlet end or opening 112 disposed at or upstream from
the forward plate 102 and an outlet end or opening 114 disposed
downstream and/or extending axially away from the aft plate 104. In
various embodiments one or more of the tubes 110 includes one or
more fuel ports or holes 116 in fluid communication with the fuel
plenum 108. Each tube 110 defines a passage or premix passage 118
through the respective nozzle segment 100. In operation, fuel may
be supplied to the fuel plenum 108 via a corresponding fluid
conduit 50. The fuel from the fuel plenum 108 may be injected into
a respective premix passage 118 via fuel port(s) 116 where it is
mixed with the compressed air 22 from the high pressure plenum 30.
The fuel-air mixture is then injected from the respective tube 110
outlet 114 into the combustion chamber 36 where it is burned to
produce the combustion gases 26.
[0026] In various embodiments, as shown in FIG. 4, the nozzle
segment 100 includes an inlet flow conditioner 120. In particular
embodiments, as shown in FIG. 4, the inlet flow conditioner 120
includes a sleeve 122 that is annularly shaped and that
circumferentially surrounds a portion of fluid conduit 50. The
sleeve 122 extends axially upstream from the forward plate 102. The
sleeve 122 extends circumferentially around the respective inlets
112 to each respective tube 110 of the plurality of tubes 110. In
particular embodiments, the sleeve 122 defines a plurality of
apertures or holes 124 radially oriented and circumferentially
spaced about the sleeve 122. In particular embodiments, the
plurality of apertures 124 may be uniformly spaced or distributed
or may be non-uniformly spaced or distributed along the sleeve 122.
In particular embodiments, the plurality of apertures 124 may be
uniformly sized or may be sized differently at various axial
locations along the sleeve 122. In particular embodiments, the
plurality of apertures 124 may be uniformly shaped or may have
different shapes defined at various axial locations along the
sleeve 122.
[0027] In particular embodiments, as shown in FIG. 4, the inlet
flow conditioner 120 includes conditioner plate 126. In particular
embodiments, the sleeve 122 extends from the conditioner plate 126
to the forward plate 102 of the nozzle segment 100. In particular
embodiments, the conditioner plate 126 extends radially outwardly
from and at least partially circumferentially around the fluid
conduit 50. The conditioner plate 126, the sleeve 122 and the
forward plate 102 at least partially define an inlet flow plenum
128 therebetween. The respective inlet 112 of each respective tube
110 is in fluid communication with the inlet flow plenum 128.
[0028] FIG. 5 provides a perspective view of an exemplary
conditioner plate 126 according to at least one embodiment of the
present disclosure. In particular embodiments, as shown in FIG. 5,
the conditioner plate 126 may be wedge or pie shaped. As shown in
FIG. 5, the conditioner plate 126 defines and/or includes a
plurality of apertures 130. The plurality of apertures 130 is
distributed across the conditioner plate 126. The flow area of the
apertures 130 may be sized equally or may be sized differently with
the flow area of some apertures 130 being smaller or larger than
the flow area of other apertures 130. For example, in one
embodiment a first aperture 130 of the plurality of apertures 130
may have a first diameter or flow area D1 and a second aperture 130
of the plurality of apertures 130 may have a second diameter or
flow area D2 that is less than the first diameter D1.
[0029] Although the apertures 130 are illustrated in FIG. 5 as
having a round shape, the particular shape of the apertures 130 is
not limited to round or circular unless otherwise recited in the
claims. For example, one or more of the apertures 130 may be
oblong, square, rectangular, trapezoidal, triangular or have other
shapes so as to have a desired effect on air flowing through the
conditioner plate 126 into the inlet flow plenum 128.
[0030] FIG. 6 provides a cross-sectioned perspective view of an
exemplary fuel nozzle 200 according to at least one embodiment of
the present disclosure. As shown in FIG. 6, each fuel nozzle 200
includes a forward plate 202, an aft plate 204 that is axially
offset from the forward plate 202 with respect to an axial
centerline of the combustor 14 and an outer band 206 that at least
partially defines a radially outer perimeter of the fuel nozzle
200. The outer band 206 extends from the forward plate 202 to the
aft plate 204. A fuel plenum 208 may be at least partially defined
between the forward plate 202, the aft plate 204 and the outer band
206.
[0031] A plurality of tubes 210 extends through the forward plate
202, the fuel plenum 208 and the aft plate 204. Each tube 210
includes an inlet end or opening 212 disposed at or upstream from
the forward plate 202 and an outlet end or opening 214 disposed
downstream and/or extending axially away from the aft plate 204. In
various embodiments one or more of the tubes 210 includes one or
more fuel ports or holes 216 in fluid communication with the fuel
plenum 208. Each tube 210 defines a passage or premix passage 218
through the respective fuel nozzle 200.
[0032] In operation, fuel may be supplied to the fuel plenum 208
via a corresponding fluid conduit 50. The fuel from the fuel plenum
208 may be injected into a respective premix passage 218 via fuel
port(s) 216 where it is mixed with the compressed air 22 from the
high pressure plenum 30. The fuel-air mixture is then injected from
the respective tube 210 outlet 214 into the combustion chamber 36
where it is burned to produce the combustion gases 26.
[0033] In various embodiments, as shown in FIG. 6, the fuel nozzle
200 includes an inlet flow conditioner 220. In particular
embodiments, as shown in FIG. 6, the inlet flow conditioner 220
includes a sleeve 222 that is annularly shaped and that
circumferentially surrounds a portion of fluid conduit 50. The
sleeve 222 extends axially upstream from the forward plate 202. The
sleeve 222 extends circumferentially around the respective inlet
212 to each respective tube 210 of the plurality of tubes 210. In
particular embodiments, the sleeve 222 defines a plurality of
apertures or holes 224 circumferentially spaced about the sleeve
222. In particular embodiments, the plurality of apertures 224 may
be uniformly spaced or distributed or may be non-uniformly spaced
or distributed along the sleeve 222. In particular embodiments, the
plurality of apertures 224 may be uniformly sized or may be sized
differently at various axial locations along the sleeve 222. In
particular embodiments, the plurality of apertures 224 may be
uniformly shaped or may have different shapes defined at various
axial locations along the sleeve 222.
[0034] In particular embodiments, as shown in FIG. 6, the inlet
flow conditioner 220 includes conditioner plate 226. In particular
embodiments, the sleeve 222 extends from the conditioner plate 226
to the forward plate 202 of the fuel nozzle 200. In particular
embodiments, the conditioner plate 226 extends radially outwardly
from and at least partially circumferentially around the fluid
conduit 50. The conditioner plate 226, the sleeve 222 and the
forward plate 202 at least partially define an inlet flow plenum
228 therebetween. The respective inlet 212 of each respective tube
210 is in fluid communication with the inlet flow plenum 228.
[0035] FIG. 7 provides a perspective view of an exemplary
conditioner plate 226 according to at least one embodiment of the
present disclosure. As shown in FIG. 7, the conditioner plate 226
defines and/or includes a plurality of apertures 230. The plurality
of apertures 230 is distributed across the conditioner plate 226.
The flow area of the apertures 230 may be sized equally or may be
sized differently with the flow area of some apertures 230 being
smaller or larger than the flow area of other apertures 230. For
example, in one embodiment a first aperture 230 of the plurality of
apertures 230 may have a first diameter or flow area D1 and a
second aperture 230 of the plurality of apertures 230 may have a
second diameter or flow area D2 that is less than the first
diameter D1
[0036] Although the apertures 230 are illustrated in FIG. 7 as
having a round shape, the particular shape of the apertures 230 is
not limited to round unless otherwise recited in the claims. For
example, one or more of the apertures 230 may be oblong, square,
rectangular, trapezoidal, triangular or have other shapes so as to
have a desired effect on air flowing through the conditioner plate
226 into the inlet flow plenum 228.
[0037] During operation, as shown in FIGS. 2 through 7
collectively, compressed air 22 from the high pressure plenum 30
flows from the high pressure plenum towards the head end volume 46.
A portion of the compressed air 22 may flow through apertures 124,
224 defined in the corresponding sleeve 122, 222 and into the
corresponding flow distribution plenum 128, 228. A portion of the
compressed air 22 then flows to the head end volume 46 where it
reverses direction and flows through the corresponding apertures
130, 230 of the respective conditioning plate 126, 230.
[0038] The apertures 124, 224 reduce non-uniformity of the
compressed air 22 as it enters the respective inlet flow plenums
128, 228 from the head end volume 46. The compressed air 22 having
a substantially uniform flow field, enters the inlet(s) 112, 212 of
the premix passage(s) 118, 218 in a substantially uniform fashion
where fuel from the respective fuel plenums 108, 208 is injected
into the flow of the compressed air 22 via the fuel ports 116, 216.
The fuel and compressed air 22 mix within the respective premix
passages 118, 218 and the mixture is then injected into the primary
combustion chamber 36 where it is burned to produce combustion
gases. The reduction in non-uniformity of the compressed air 22
provided by the respective conditioner plates 126, 226 as it enters
the respective inlet flow plenums 128, 228 from the head end volume
46 improves mixing of the fuel and air within the premix passages
118, 218, thereby reducing overall NOx emissions of the combustor
14.
[0039] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they include structural elements that do not
differ from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal language of the claims.
* * * * *