U.S. patent application number 13/150319 was filed with the patent office on 2012-12-06 for turbomachine combustor assembly including a liner stop.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to David William Cihlar, Robert Joseph Rohrssen.
Application Number | 20120304655 13/150319 |
Document ID | / |
Family ID | 46148759 |
Filed Date | 2012-12-06 |
United States Patent
Application |
20120304655 |
Kind Code |
A1 |
Rohrssen; Robert Joseph ; et
al. |
December 6, 2012 |
TURBOMACHINE COMBUSTOR ASSEMBLY INCLUDING A LINER STOP
Abstract
A turbomachine combustor assembly includes a combustor housing
and a combustor body. The combustor body defines a combustor liner
having a first end portion that extends to a second end portion
through a combustion chamber. A cap assembly is mounted at the
combustor housing. The cap assembly includes an endcover, a
plurality of fuel nozzles supported by the end cover, and an outer
barrel member. The outer barrel member extends about the plurality
of fuel nozzles. A liner stop is arranged on one of the outer
barrel member and the first end portion of the combustor liner. The
liner stop includes a stepped lip portion that receives the other
of the outer barrel member and the first end portion of the
combustor liner to form substantially smooth liner to outer barrel
interface. The liner stop restricts axial movement of the combustor
liner relative to the outer barrel member.
Inventors: |
Rohrssen; Robert Joseph;
(Simpsonville, SC) ; Cihlar; David William;
(Greenville, SC) |
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
46148759 |
Appl. No.: |
13/150319 |
Filed: |
June 1, 2011 |
Current U.S.
Class: |
60/752 ;
29/890.01 |
Current CPC
Class: |
Y10T 29/49346 20150115;
F23R 3/002 20130101; F23R 3/60 20130101; F23R 2900/00012
20130101 |
Class at
Publication: |
60/752 ;
29/890.01 |
International
Class: |
F23R 3/00 20060101
F23R003/00; B21D 53/00 20060101 B21D053/00 |
Claims
1. A turbomachine combustor assembly comprising: a combustor
housing having a first end; a combustor body arranged within the
combustor housing, the combustor body defining a combustor liner
having a first end portion that extends to a second end portion
through a combustion chamber; a cap assembly mounted at the first
end of the combustor housing, the cap assembly including an
endcover, a plurality of fuel nozzles supported by the end cover
and an outer barrel member extending between the end cover and the
combustor housing, the outer barrel member extending about the
plurality of fuel nozzles; and a liner stop arranged on one of the
outer barrel member and the first end portion of the combustor
liner, the liner stop including a stepped lip portion that receives
the other of the outer barrel member and the first end portion of
the combustor liner to form substantially smooth liner-to-outer
barrel interface, the liner stop restricting axial movement of the
combustor liner relative to the outer barrel member.
2. The turbomachine combustor assembly according to claim 1,
further comprising: a seal member arranged at the substantially
smooth liner to outer barrel interface.
3. The turbomachine combustor assembly according to claim 2,
wherein the seal member is provided on the stepped lip portion.
4. The turbomachine combustor assembly according to claim 2,
wherein the seal member extends radially about the outer barrel
member at the stepped lip portion.
5. The turbomachine combustor assembly according to claim 2,
wherein the seal member comprises a hula seal.
6. The turbomachine combustor assembly according to claim 1,
wherein the substantially smooth liner-to-outer barrel interface is
configured and disposed to condition a fluid flow passing over the
combustor liner toward the end cover.
7. The turbomachine combustor assembly according to claim 6,
wherein the stepped lip portion is configured and disposed to
promote a substantially laminar flow across the substantially
smooth liner to outer barrel interface.
8. The turbomachine combustor assembly according to claim 1,
wherein the liner stop is provided on the outer barrel member.
9. A turbomachine comprising: a compressor portion; a turbine
portion operatively connected to the compressor portion; and a
combustor assembly fluidly connecting the compressor portion and
the turbine portion, the combustor assembly comprising: a combustor
housing having a first end; a combustor body arranged within the
combustor housing, the combustor body defining a combustor liner
having a first end portion that extends to a second end portion
through a combustion chamber; a cap assembly mounted at the first
end of the combustor housing, the cap assembly including an
endcover, a plurality of fuel nozzles supported by the end cover
and an outer barrel member extending between the end cover and the
combustor housing, the outer barrel member extending about the
plurality of fuel nozzles; and a liner stop arranged on one of the
outer barrel member and the first end portion of the combustor
liner, the liner stop including a stepped lip portion that receives
the other of the outer barrel member and the first end portion of
the combustor liner to form substantially smooth liner to outer
barrel interface, the liner stop restricting axial movement of the
combustor liner relative to the outer barrel member.
10. The turbomachine according to claim 9, further comprising: a
seal member arranged at the substantially smooth liner to outer
barrel interface.
11. The turbomachine according to claim 9, wherein the seal member
is provided on the stepped lip portion.
12. The turbomachine according to claim 9, wherein the seal member
extends radially about the outer barrel member at the stepped lip
portion.
13. The turbomachine according to claim 9, wherein the seal member
comprises a hula seal.
14. The turbomachine according to claim 9, wherein the
substantially smooth liner-to-outer barrel interface is configured
and disposed to condition a fluid flow passing over the combustor
liner toward the end cover.
15. The turbomachine according to claim 14, wherein stepped lip
portion is configured and disposed to promote a substantially
laminar flow across the substantially smooth liner to outer barrel
interface.
16. The turbomachine according to claim 9, wherein the liner stop
is provided on the outer barrel member.
17. A method of joining a cap assembly to a turbomachine combustor
housing, the method comprising: aligning an outer barrel member
carried by the cap assembly with a combustor liner extending about
a combustion chamber in the combustor housing; inserting a stepped
lip portion provided on one of the outer barrel member and the
combustor liner into the other of the outer barrel member and the
combustor liner to form a liner to outer barrel interface; and
securing the cap assembly to the turbomachine combustor
housing.
18. The method of claim 17, further comprising: sealing the liner
to outer barrel interface.
19. The method of claim 17, wherein inserting the stepped lip
portion provided on one of the outer barrel member and the
combustor liner into the other of the outer barrel member and the
combustor liner includes compressing seal provided on the stepped
lip portion.
20. The method of claim 17, further comprising: restricting axial
movement of the combustor liner relative to the outer barrel member
with the stepped lip portion.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to the art of
turbomachines and, more particularly, to turbomachine combustor
assembly including a liner stop.
[0002] In conventional turbomachines, a first fluid, such as fuel,
is directed into a combustor cap prior to being mixed with another
fluid, such as air, and combusted in a combustion chamber to form
hot gases. The first fluid enters the combustor cap through a fuel
manifold joined to the combustor casing. Compressor discharge air
passes through a passageway that extends between a cap liner and
the combustion chamber into the combustion cap to mix with the
fuel. The cap liner is supported in a spaced relationship between
the combustion chamber and an outer combustor casing. The
combustion cap generally includes several liner stops that engage
with the liner to restrict axial movement of the cap liner during
turbomachine operation.
BRIEF DESCRIPTION OF THE INVENTION
[0003] According to one aspect of the exemplary embodiment, a
turbomachine combustor assembly includes a combustor housing having
a first end, and a combustor body arranged within the combustor
housing. The combustor body defines a combustor liner having a
first end portion that extends to a second end portion through a
combustion chamber. A cap assembly is mounted at the first end of
the combustor housing. The cap assembly includes an endcover, a
plurality of fuel nozzles supported by the end cover, and an outer
barrel member extending between the end cover and the combustor
housing. The outer barrel member extends about the plurality of
fuel nozzles. A liner stop is arranged on one of the outer barrel
member and the first end portion of the combustor liner. The liner
stop includes a stepped lip portion that receives the other of the
outer barrel member and the first end portion of the combustor
liner to form substantially smooth liner to outer barrel interface.
The liner stop restricts axial movement of the combustor liner
relative to the outer barrel member.
[0004] According to another aspect of the exemplary embodiment, a
turbomachine includes a compressor portion, a turbine portion
operatively connected to the compressor portion, and a combustor
assembly fluidly connecting the compressor portion and the turbine
portion. The combustor assembly includes a combustor housing having
a first end, and a combustor body arranged within the combustor
housing. The combustor body defines a combustor liner having a
first end portion that extends to a second end portion through a
combustion chamber. A cap assembly is mounted at the first end of
the combustor housing. The cap assembly includes an endcover, a
plurality of fuel nozzles supported by the end cover, and a flow
sleeve extending between the end cover and the combustor housing.
The flow sleeve includes an outer barrel member that extends about
the plurality of fuel nozzles. A liner stop is arranged on one of
the outer barrel member and the first end portion of the combustor
liner. The liner stop includes a stepped lip portion that receives
the other of the outer barrel member and the first end portion of
the combustor liner to form substantially smooth liner to outer
barrel interface. The liner stop restricts axial movement of the
combustor liner relative to the outer barrel member.
[0005] According to yet another aspect of the exemplary embodiment,
a method of joining a cap assembly to a turbomachine combustor
housing includes aligning an outer barrel member carried by the cap
assembly with a combustor liner extending about a combustion
chamber in the combustor housing, inserting a stepped lip portion
provided on one of the outer barrel member and the combustor liner
into the other of the outer barrel member and the combustor liner
to form a liner to outer barrel interface, and securing the cap
assembly to the turbomachine combustor housing.
[0006] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF THE DRAWING
[0007] The subject matter, which is regarded as the invention, is
particularly pointed out and distinctly claimed in the claims at
the conclusion of the specification. The foregoing and other
features, and advantages of the invention are apparent from the
following detailed description taken in conjunction with the
accompanying drawings in which:
[0008] FIG. 1 is a partial cross-sectional view of a turbomachine
including a combustor assembly having a liner stop in accordance
with an exemplary embodiment;
[0009] FIG. 2 is a partial perspective view of a cap assembly
portion of the combustor assembly illustrating a liner stop in
accordance with the exemplary embodiment;
[0010] FIG. 3 is detail perspective view of the liner stop of FIG.
2; and
[0011] FIG. 4 is a partial plan view of the liner stop of FIG.
2.
[0012] The detailed description explains embodiments of the
invention, together with advantages and features, by way of example
with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0013] The terms "axial" and "axially" as used in this application
refer to directions and orientations extending substantially
parallel to a center longitudinal axis of a combustor assembly. The
terms "radial" and "radially" as used in this application refer to
directions and orientations extending substantially orthogonally to
the center longitudinal axis of the combustor assembly. The terms
"upstream" and "downstream" as used in this application refer to
directions and orientations relative to an axial flow direction
with respect to the center longitudinal axis of the combustor
assembly.
[0014] With reference to FIG. 1, a turbomachine in accordance with
an exemplary embodiment is indicated generally at 2. Turbomachine 2
includes a compressor portion 4 operatively connected to a turbine
portion 6. A combustor assembly 10 fluidly connects compressor
portion 4 with turbine portion 6. Compressor portion 4 includes a
compressor discharge 14 that passes compressor discharge air into
combustor assembly 10. As will be discussed more fully below, a
portion of the combustor discharge air is employed for cooling
various components of combustor assembly 10, and another portion of
the compressor discharge air is mixed with fuel to form a
combustible mixture that is combusted to form hot gases. The hot
gases pass from combustor assembly 10 through a transition piece 16
into turbine portion 6. Turbine portion 6 converts thermal energy
from the hot gases into mechanical, rotational energy used to power
various systems such as generators, pumps and the like.
[0015] In accordance with the exemplary embodiment shown, combustor
assembly 10 includes a combustor housing 20 having a first end 22
that extends to a second end (not shown). Combustor assembly 10
includes a combustor body 30 arranged within combustor housing 20.
Combustor body 30 defines a combustor liner 34. Combustor liner 34
includes a first end portion 37 that extends to a second end
portion 38 through a combustion chamber 40. Combustor assembly 10
also includes an cap assembly 50 mounted at first end 22 of
combustor housing 20. Cap assembly 50 includes an end cover 52 and
a forward casing 53.
[0016] End cover 52 supports a plurality of fuel nozzles, one of
which is indicated at 56, arranged in an annular array. Fuel
nozzles 56 extend from end cover 52 toward combustion chamber 40.
As will be detailed more fully below, fuel and air are mixed in
forward casing 53 forming a combustible mixture that is passed to
fuel nozzles 56. The combustible mixture is combusted and expanded
in combustion chamber 40 and then passed through transition piece
16 toward turbine portion 6. Forward casing 53 includes a body 60
having a first flange 62 that is operatively connected to first end
22 of combustor housing 20 and a second flange 63 to which is
mounted end cover 52. Forward casing 53 includes an outer barrel
member 66 that extends about fuel nozzles 56 and defines, in part,
a passage (not separately labeled) that conducts compressor
discharge air from combustor housing 20 toward end cover 52.
[0017] In accordance with an exemplary embodiment, outer barrel
member 66 includes a body member 67 having a first end section 68
that extends to a second end section 69. Second end section 69
abuts first end portion 37 of combustor liner 34. In order to
restrict axial movement of combustor liner 34, outer barrel member
66 includes a liner stop 80. Liner stop 80 includes a stepped lip
portion 83 provided at second end section 69 of outer barrel member
66. Stepped lip portion 83 includes a first wall section 86 and a
second wall section 87. First wall section 86 extends from body
member 67 radially toward a centerline (not separately labeled) of
combustor assembly 10. Second wall section 87 is radially offset
from body member 67 and extends substantially perpendicularly from
first wall section 86.
[0018] Cap assembly 50 is positioned at combustor housing 20 with
outer barrel member 66 being aligned with combustor liner 34. Cap
assembly 50 is mounted and secured to combustor housing 20 with
stepped lip portion 83 extending into first end portion 37 of
combustor liner 34 forming a substantially smooth liner-to-outer
barrel member interface 90. Within this arrangement, first wall
section 86 restricts axial movement of combustion liner 34 while
stepped lip portion 83 establishes a smooth transition between
combustion liner 34 and outer barrel member 66. The smooth
transition established between combustion liner 34 and outer barrel
portion 66 promotes a substantially laminar flow of compressor
discharge air passing from compressor portion 4 along combustor
body 30. Thus, not only does liner stop 80 limit or restrict axial
movement of combustion liner 34 but also conditions fluid flow to
fuel nozzles 56.
[0019] In further accordance with the exemplary embodiment, liner
stop 80 is provided with a seal member 94 that includes a plurality
of seal segments, one of which is indicated at 96, secured to
second wall section 87 to form a hula seal 99. Seal member 94
restricts fluid flow passing over combustion liner 34 toward end
cover 52 from escaping through liner-to-outer barrel member
interface 90. That is, when outer barrel member 66 inserted into
combustion liner 34, first end portion 37 compresses seal member 84
to form a more robust seal at liner-to-outer barrel member
interface 90. At this point it should be understood that while
shown on outer barrel member 66, stepped lip portion 83 could
alternatively be formed on first end portion 37 of combustion liner
34. In addition, while shown with a seal member formed from
multiple seal segments, it should be understood that a continuous
seal could also be employed.
[0020] While the invention has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the invention is not limited to such
disclosed embodiments. Rather, the invention can be modified to
incorporate any number of variations, alterations, substitutions or
equivalent arrangements not heretofore described, but which are
commensurate with the spirit and scope of the invention.
Additionally, while various embodiments of the invention have been
described, it is to be understood that aspects of the invention may
include only some of the described embodiments. Accordingly, the
invention is not to be seen as limited by the foregoing
description, but is only limited by the scope of the appended
claims.
* * * * *