U.S. patent application number 12/759042 was filed with the patent office on 2011-10-13 for apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly.
Invention is credited to Ajay Kumar Gupta, William Kirk Hessler, Jeffrey Lebegue, Predrag POPOVIC, Derrick Walter Simons, Krishna Kumar Venkataraman.
Application Number | 20110247340 12/759042 |
Document ID | / |
Family ID | 44262859 |
Filed Date | 2011-10-13 |
United States Patent
Application |
20110247340 |
Kind Code |
A1 |
POPOVIC; Predrag ; et
al. |
October 13, 2011 |
APPARATUS AND METHOD FOR MINIMIZING AND/OR ELIMINATING DILUTION AIR
LEAKAGE IN A COMBUSTION LINER ASSEMBLY
Abstract
A combustion liner assembly for a gas turbine includes an outer
liner, the outer liner having a flange at a forward end. An inner
liner is disposed within the outer liner. The inner liner has a
first inner wall. A venturi includes a second inner wall, a venturi
throat, and the first inner wall of the inner liner. A slip joint
is connected to the second inner wall. The slip joint receives the
flange of the outer liner. Alternatively, or additionally, the
combustion liner assembly includes a slip joint between the inner
or outer liner and an aft section.
Inventors: |
POPOVIC; Predrag;
(Greenville, SC) ; Venkataraman; Krishna Kumar;
(Simpsonville, SC) ; Simons; Derrick Walter;
(Greer, SC) ; Gupta; Ajay Kumar; (Alpharetta,
GA) ; Hessler; William Kirk; (Philadelphia, PA)
; Lebegue; Jeffrey; (Simpsonville, SC) |
Family ID: |
44262859 |
Appl. No.: |
12/759042 |
Filed: |
April 13, 2010 |
Current U.S.
Class: |
60/752 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 3/02 20130101; F23R 2900/00001 20130101 |
Class at
Publication: |
60/752 |
International
Class: |
F23R 3/42 20060101
F23R003/42 |
Claims
1. A combustion liner assembly for a gas turbine, comprising: an
outer liner, the outer liner having a flange at a forward end; an
inner liner disposed within the outer liner, the inner liner having
a first inner wall; a venturi comprising a second inner wall, a
venturi throat, and the first inner wall of the inner liner; and a
slip joint connected to the second inner wall, the slip joint
receiving the flange of the outer liner.
2. A combustion liner assembly according to claim 1, further
comprising an aft section provided at aft ends of the outer liner
and the inner liner.
3. A combustion liner assembly according to claim 1, further
comprising: a second slip joint connecting the aft section and the
outer liner or the inner liner.
4. A combustion liner assembly according to claim 1, wherein the
outer liner comprises a plurality of radial drain or dump
holes.
5. A combustion liner assembly according to claim 2, wherein the
aft section comprises a plurality of radial drain or dump
holes.
6. A combustion liner assembly according to claim 5, wherein the
aft section further comprises a plurality of axial drain or dump
holes.
7. A combustion liner assembly according to claim 2, wherein the
aft section comprises a plurality of axial drain or dump holes.
8. A combustion liner assembly according to claim 2, wherein the
aft section comprises a plurality of holes at an intersection of a
cylindrical section of the aft section and a conical section of the
aft section.
9. A combustion liner assembly according to claim 1, wherein the
slip joint is formed of a nickel alloy and the flange is formed of
stainless steel.
10. A combustion liner assembly according to claim 1, wherein the
slip joint comprises a wear coating.
11. A combustor for a gas turbine, comprising: a liner sleeve; and
a combustion liner assembly according to claim 1, wherein the
combustion liner assembly is welded to the liner sleeve at least at
the slip joint.
12. A combustion liner assembly for a gas turbine, comprising: an
outer liner; an inner liner disposed within the outer liner, the
inner liner having a first inner wall; a venturi comprising a
second inner wall, a venturi throat, and the first inner wall of
the inner liner; an aft section connected to aft ends of the outer
liner and the inner liner; and a slip joint provided between the
aft section and the inner liner.
13. A combustion liner assembly according to claim 12, wherein the
aft section further comprises a bellows.
14. A combustion liner assembly according to claim 12, wherein the
outer liner comprises a plurality of radial drain or dump
holes.
15. A combustion liner assembly according to claim 12, wherein the
aft section comprises a plurality of radial drain or dump
holes.
16. A combustion liner assembly according to claim 15, wherein the
aft section further comprises a plurality of axial drain or dump
holes.
17. A combustion liner assembly according to claim 12, wherein the
aft section comprises a plurality of axial drain or dump holes.
18. A combustion liner assembly according to claim 12, wherein the
aft section comprises a plurality of holes at an intersection of a
cylindrical section of the aft section and a conical section of the
aft section.
19. A combustion liner assembly according to claim 12, wherein the
slip joint comprises a wear coating.
20. A combustor for a gas turbine, comprising: a liner sleeve; and
a combustion liner assembly according to claim 12, wherein the
combustion liner assembly is welded to the liner sleeve.
Description
[0001] The present invention relates to apparatus and methods for
minimizing or eliminating dilution air leakage paths in a gas
turbine combustor and particularly relates to apparatus and methods
for managing dilution air leakage to achieve lower emission
levels.
BACKGROUND OF THE INVENTION
[0002] Significant products of combustion in gas turbine emissions
are oxides of nitrogen, i.e., NO and NO.sub.2 collectively called
NO.sub.x, carbon monoxide CO, and unburned hydrocarbons as well as
other particulates. Various systems have been proposed and utilized
for reducing emissions. For example, water or steam injection into
the burning zone of the gas turbine combustor, catalytic clean-up
of NO.sub.x and CO from the gas turbine exhaust and dry low
NO.sub.x combustors have been used in the past. Compressor
discharge dilution air introduced into the liner sleeve of the
combustor and transition piece has also been utilized to reduce
emissions.
BRIEF DESCRIPTION OF THE INVENTION
[0003] According to an embodiment of the invention, a combustion
liner assembly for a gas turbine comprises an outer liner, the
outer liner having a flange at a forward end; an inner liner
disposed within the outer liner, the inner liner having a first
inner wall; a venturi comprising a second inner wall, a venturi
throat, and the first inner wall of the inner liner; and a slip
joint connected to the second inner wall, the slip joint receiving
the flange of the outer liner.
[0004] According to another embodiment of the invention, a
combustion liner assembly for a gas turbine comprises an outer
liner; an inner liner disposed within the outer liner, the inner
liner having a first inner wall; a venturi comprising a second
inner wall, a venturi throat, and the first inner wall of the inner
liner; an aft section connected to aft ends of the outer liner and
the inner liner; and a slip joint provided between the aft section
and the inner liner.
BRIEF DESCRIPTION OF THE DRAWINGS
[0005] FIG. 1 is a schematic illustration of a gas turbine
combustion liner assembly according to an embodiment of the
invention;
[0006] FIG. 2 is a schematic illustration of a venturi throat of
the combustion liner assembly of FIG. 1;
[0007] FIG. 3 is a schematic illustration of a combustion liner
assembly according to another embodiment of the invention;
[0008] FIG. 4 is a schematic illustration of a combustion liner
assembly according to another embodiment of the invention;
[0009] FIG. 5 is a schematic illustration of a combustion liner
assembly according to another embodiment of the invention;
[0010] FIG. 6 is a schematic illustration of an aft, or goose neck,
section of the combustion liner assembly according to another
embodiment of the invention;
[0011] FIG. 7 is a schematic illustration of a combustion liner
assembly according to another embodiment of the invention;
[0012] FIG. 8 is a schematic illustration of a combustion liner
assembly according to another embodiment of the invention; and
[0013] FIG. 9 is a schematic illustration of a flange of the outer
liner and slip joint according to an embodiment of the
invention.
DETAILED DESCRIPTION OF THE INVENTION
[0014] Referring to FIG. 1, a combustion liner assembly 2 comprises
an outer liner 4 and an inner liner 6. A venturi 8 is provided at a
forward end of the combustion liner assembly 2 and includes a
venturi throat 10 which is provided between the inner liner 6 and
an inner wall 12. A flange 14 may be integrally formed with the
outer liner 4 and is received in a slip joint 16 that is connected
to the inner wall 12 of the venturi 8.
[0015] The inner liner 6 includes an inner wall 24 and turbulators
18 provided on an outer surface. An aft section, or gooseneck
section, 20 is connected to the aft portion of the outer liner 4
and the inner liner 6. Radial drain or dump holes 22 are provided
in the inner liner at an area adjacent to the aft section 20.
[0016] The combustion liner assembly 2 may be welded to a liner
sleeve at areas A and B corresponding to the slip joint 16 and the
end of the aft section 20, respectively. The combustion liner
assembly 2 may be circumferentially welded to the liner sleeve,
rather than riveted as in prior art arrangements.
[0017] Referring to FIG. 2, the venturi 10 may be circumferentially
welded to the inner wall 12 and the inner wall 24 of the inner
liner 6. The thickness of the inner wall 24 and the thickness of
the inner wall 24 of the inner liner 6 at the portion containing
the circumferential weld may be thicker than prior art combustion
liner assembly inner liners to increase the structural integrity of
the venturi, as the venturi will be welded to the liner sleeve as
opposed to riveted.
[0018] The radial drain or dump holes 22 of the embodiment shown in
FIGS. 1 and 2 provides a radial discharge of cooling flow into the
flame zone. The embodiments shown in FIGS. 1 and 2 may also have an
increased impingement cooling area combined with the turbulators
18. A small controlled leak may be provided into the cooling
channel between the outer liner 4 and the inner liner 6 as an
alternative to a bellows.
[0019] Referring to FIG. 3, according to another embodiment of the
invention, the combustion liner assembly 2 includes the aft
section, or gooseneck section 20 which comprises axial drain or
dump holes 24, rather than radial drain or dump holes. It has been
found that the use of radial drain or dump holes, as shown in the
embodiment of FIGS. 1 and 2, may trigger high frequency combustion
instability, or screech, during transfer to the premix combustion
and at the turndown when the flame temperature is reduced. However,
the axial drain or dump holes 24 do not trigger high frequency
instability with the integral venturi of the embodiment shown in
FIG. 3.
[0020] As shown in FIGS. 1 and 2, the venturi cooling is rerouted
to have an axial discharge with the same effective area as the
radial discharge of the venturi of the embodiment shown in FIG.
3.
[0021] Referring to FIGS. 4 and 5, a combustion liner assembly 2
according to another embodiment comprises an outer liner 4 and an
inner liner 6. The outer liner 4 includes a flange 14 that is
received in a slip joint 16 that is connected to an inner wall 12
of a venturi 8 that comprises a venturi throat 10 that connects the
inner wall 12 and a portion of the inner liners 6 having axial
drain or dump holes 24. At the aft section or, gooseneck section
20, the combustion liner assembly 2 comprises radial drain or dump
holes 22 formed in the inner liner 6.
[0022] Referring to FIG. 6, according to another embodiment, the
dump holes 26 may be provided as holes on the face of the aft
section 20, i.e. at the intersection of the cylindrical and conical
portions of the aft section 20.
[0023] Referring to FIG. 7, a combustion liner assembly according
to another embodiment comprises an outer liner 4 and an inner liner
6. A venturi 8 is provided at a forward section of the combustion
liner assembly 2 and includes a venturi throat 10 and an inner wall
12. The venturi 8 also includes an inner wall 24 connected between
the venturi throat 10 and the inner liner 6. An aft section 20 is
connected to the outer liner 4 and the inner liner 6 by an aft slip
joint 30. The combustion liner assembly 2 comprises radial drain or
dump holes 22 provided in the inner liner 6.
[0024] The aft end of the combustion liner assembly 2 comprises a
bellows 28, as well as a slip joint 30 as disclosed in the previous
embodiments.
[0025] Referring to FIG. 8, according to another embodiment of the
invention, a combustion liner assembly 2 includes an outer liner 4
and an inner liner 6. A venturi 8 comprises a venturi throat 10
welded to an inner wall 12 and an inner wall 24 connected to the
inner liner 6. A flange 14 of the outer liner 4 is received in a
slip joint 16 at the forward end of the combustion liner assembly
2. An aft section 20 of the combustion liner 2 is connected to the
outer liner 4 and the inner liner 6 by an aft slip joint 30.
[0026] Referring to FIG. 9 the slip joint 16 may be formed of, for
example, an alloy of primarily nickel, such as Hastelloy.RTM., and
the flange 14 may be formed of, for example, stainless steel. The
slip joint 16 may also be provided with a wear resistant coating.
The slip joint 16 provides a double seal on both sides of the
flange 14 and may be machined to tight tolerances. As the
temperature of the combustion liner assembly 2 increases during
operation of the gas turbine, the small leakage area between the
flange 14 and the slip joint 16 decreases as the flange 14 expands
into the slip joint 16.
[0027] The combustion liner assemblies reduce, or eliminate,
airflow losses in between the venturi wall and the liner wall so
that airflow can be used and more evenly dispersed. Reduction, or
elimination, of variance to air flow will allow more consistent air
flow to be utilized in fuel air mixture in the head end combustion
zone rather than leak air flow into direct "stream". The combustion
liner assemblies are relatively easy to manufacture and produce a
more repeatable air flow from can to can and in turn help to create
better fuel air mixture pattern than current design and lower
combustion emissions. These are improvements to variation and
mixing fuel air better through the mixing holes than would happen
through the current design.
[0028] The combustion liner assemblies reduce, or eliminate, leaks
so airflow in more non-critical areas is conserved and made more
consistent, i.e. can to can variation is lowered. The combustion
liner assemblies also increase airflow in useable areas in a more
dispersed and even mixing through the mixing holes than would
happen through current designs.
[0029] The combustion liner assemblies can be replaced in the field
easily. The existing liners can be pulled out and replaced with the
combustion liner assemblies disclosed herein. The combustion liner
assemblies may also use current production methods and machining to
produce. The combustion liner assemblies do not change the fit,
form or function of the overall liner assembly.
[0030] While the invention has been described in connection with
what is presently considered to be the most practical and preferred
embodiments, it is to be understood that the invention is not to be
limited to the disclosed embodiments, but on the contrary, is
intended to cover various modifications and equivalent arrangements
included within the spirit and scope of the appended claims.
* * * * *