U.S. patent application number 15/477926 was filed with the patent office on 2018-10-04 for combustion panel grommet.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Donald W. Peters, San Quach, Robert M. Sonntag.
Application Number | 20180283695 15/477926 |
Document ID | / |
Family ID | 61868345 |
Filed Date | 2018-10-04 |
United States Patent
Application |
20180283695 |
Kind Code |
A1 |
Quach; San ; et al. |
October 4, 2018 |
COMBUSTION PANEL GROMMET
Abstract
A gas turbine engine and a combustor panel assembly are
disclosed. The gas turbine engine includes a combustor panel with a
panel dilution hole formed therethrough, a combustor liner spaced
apart from the combustor panel, wherein the combustor liner
includes a liner dilution hole formed therethrough, wherein at
least one of the combustor panel and the combustor liner is formed
from a first material, and a grommet with a first end with a first
radius, a second end with a second radius, and a continuous smooth
surface between the first end and the second end, wherein the first
radius is larger than the second radius, the grommet defining a
flow path between the panel dilution hole and the liner dilution
hole, and the grommet is formed from a second material.
Inventors: |
Quach; San; (Southington,
CT) ; Sonntag; Robert M.; (Bolton, CT) ;
Peters; Donald W.; (Colchester, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
61868345 |
Appl. No.: |
15/477926 |
Filed: |
April 3, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 3/007 20130101; F23R 3/06 20130101 |
International
Class: |
F23R 3/60 20060101
F23R003/60; F23R 3/00 20060101 F23R003/00 |
Claims
1. A combustor panel assembly for use with a combustor, the
combustor panel assembly comprising: a combustor panel with a panel
dilution hole formed therethrough; a combustor liner spaced apart
from the combustor panel, wherein the combustor liner includes a
liner dilution hole formed therethrough, wherein at least one of
the combustor panel and the combustor liner is formed from a first
material; and a grommet with a first end with a first radius, a
second end with a second radius, and a continuous smooth surface
between the first end and the second end, wherein the first radius
is larger than the second radius, the grommet defining a flow path
between the panel dilution hole and the liner dilution hole, and
the grommet is formed from a second material.
2. The combustor panel assembly of claim 1, wherein the grommet has
a frustroconical shape.
3. The combustor panel assembly of claim 1, wherein the second
material is a ceramic matric composite.
4. The combustor panel assembly of claim 1, wherein the second
material is a molybdenum alloy.
5. The combustor panel assembly of claim 1, wherein the second
material is a nickel alloy.
6. The combustor panel assembly of claim 1, wherein the second
material is a monolithic ceramic.
7. The combustor panel assembly of claim 1, wherein the grommet is
affixed to the combustor panel.
8. The combustor panel assembly of claim 7, wherein the grommet is
affixed to the combustor panel via a fastener.
9. The combustor panel assembly of claim 7, wherein the grommet is
affixed to the combustor panel via a brazed joint.
10. The combustor panel assembly of claim 7, wherein the grommet is
affixed to the combustor panel via a welded joint.
11. The combustor panel assembly of claim 7, wherein the grommet is
affixed to the combustor panel via a threaded connection.
12. A combustor, comprising: a combustor panel with a panel
dilution hole formed therethrough; a combustor liner spaced apart
from the combustor panel, wherein the combustor liner includes a
liner dilution hole formed therethrough, wherein at least one of
the combustor panel and the combustor liner is formed from a first
material; and a grommet with a first end with a first radius, a
second end with a second radius, and a continuous smooth surface
between the first end and the second end, wherein the first radius
is larger than the second radius, the grommet defining a flow path
between the panel dilution hole and the liner dilution hole, and
the grommet is formed from a second material.
13. The combustor of claim 12, wherein the grommet has a
frustroconical shape.
14. The combustor of claim 12, wherein the second material is a
ceramic matric composite.
15. The combustor of claim 12, wherein the second material is a
molybdenum alloy.
16. The combustor of claim 12, wherein the second material is a
nickel alloy.
17. A gas turbine engine, comprising: a combustor, including: a
combustor panel with a panel dilution hole formed therethrough; a
combustor liner spaced apart from the combustor panel, wherein the
combustor liner includes a liner dilution hole formed therethrough,
wherein at least one of the combustor panel and the combustor liner
is formed from a first material; and a grommet with a first end
with a first radius, a second end with a second radius, and a
continuous smooth surface between the first end and the second end,
wherein the first radius is larger than the second radius, the
grommet defining a flow path between the panel dilution hole and
the liner dilution hole, and the grommet is formed from a second
material.
18. The gas turbine engine of claim 17, wherein the grommet has a
frustroconical shape.
19. The gas turbine engine of claim 17, wherein the second material
is a ceramic matric composite.
20. The gas turbine engine of claim 17, wherein the second material
is a molybdenum alloy.
Description
BACKGROUND
[0001] The present disclosure relates to grommets for gas turbine
engines, and more particularly to grommets for use with combustors
for gas turbine engines.
[0002] Dilution holes and grommets can be utilized within
combustors of gas turbine engines to condition combustion gases
prior to entering the turbine for reliable operation and
performance. During operation, the dilution hole grommets may
experience high temperatures, oxidize, and contain features that
reduce flow.
[0003] Accordingly, it is desirable to provide conditioning
features that resist high temperatures and do not restrict dilution
flow.
BRIEF SUMMARY
[0004] According to an embodiment, a combustor panel assembly for
use with a combustor includes a combustor panel with a panel
dilution hole formed therethrough, a combustor liner spaced apart
from the combustor panel, wherein the combustor liner includes a
liner dilution hole formed therethrough, wherein at least one of
the combustor panel and the combustor liner is formed from a first
material, and a grommet with a first end with a first radius, a
second end with a second radius, and a continuous smooth surface
between the first end and the second end, wherein the first radius
is larger than the second radius, the grommet defining a flow path
between the panel dilution hole and the liner dilution hole, and
the grommet is formed from a second material.
[0005] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet has a frustroconical shape.
[0006] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a ceramic matric composite.
[0007] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a molybdenum alloy.
[0008] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a nickel alloy.
[0009] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a monolithic ceramic.
[0010] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet is affixed to the combustor panel.
[0011] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet is affixed to the combustor panel via a fastener.
[0012] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet is affixed to the combustor panel via a brazed joint.
[0013] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet is affixed to the combustor panel via a welded joint.
[0014] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet is affixed to the combustor panel via a threaded
connection.
[0015] According to an embodiment, a combustor includes a combustor
panel with a panel dilution hole formed therethrough, a combustor
liner spaced apart from the combustor panel, wherein the combustor
liner includes a liner dilution hole formed therethrough, wherein
at least one of the combustor panel and the combustor liner is
formed from a first material, and a grommet with a first end with a
first radius, a second end with a second radius, and a continuous
smooth surface between the first end and the second end, wherein
the first radius is larger than the second radius, the grommet
defining a flow path between the panel dilution hole and the liner
dilution hole, and the grommet is formed from a second
material.
[0016] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet has a frustroconical shape.
[0017] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a ceramic matric composite.
[0018] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a molybdenum alloy.
[0019] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a nickel alloy.
[0020] According to an embodiment, a gas turbine engine includes a
combustor, including a combustor panel with a panel dilution hole
formed therethrough, a combustor liner spaced apart from the
combustor panel, wherein the combustor liner includes a liner
dilution hole formed therethrough, wherein at least one of the
combustor panel and the combustor liner is formed from a first
material, and a grommet with a first end with a first radius, a
second end with a second radius, and a continuous smooth surface
between the first end and the second end, wherein the first radius
is larger than the second radius, the grommet defining a flow path
between the panel dilution hole and the liner dilution hole, and
the grommet is formed from a second material.
[0021] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
grommet has a frustroconical shape.
[0022] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a ceramic matric composite.
[0023] In addition to one or more of the features described above,
or as an alternative, further embodiments could include that the
second material is a molybdenum alloy.
[0024] Other aspects, features, and techniques of the embodiments
will become more apparent from the following description taken in
conjunction with the drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0025] The subject matter which is regarded as the present
disclosure 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 present disclosure are
apparent from the following detailed description taken in
conjunction with the accompanying drawings in which:
[0026] FIG. 1 is a schematic, partial cross-sectional view of a
turbomachine in accordance with this disclosure;
[0027] FIG. 2 is a detail view of the combustor section for use
with the turbomachine of FIG. 1,
[0028] FIG. 3A is an exploded partial isometric view of the
combustor panel assembly with a grommet for use with the combustor
section of FIG. 2; and
[0029] FIG. 3B is a partial cross-sectional view of the combustor
panel assembly with a grommet for use with the combustor section of
FIG. 2.
DETAILED DESCRIPTION
[0030] Embodiments provide a grommet for use with a combustor panel
assembly. The grommet provides a low restriction flow path for
conditioning airflow while adding high temperature resistant
material to the combustor panel assembly to allow for reliable
operation and desired performance.
[0031] Referring to FIG. 1 a schematic representation of a gas
turbine engine 10 is shown. The gas turbine engine includes a fan
section 12, a compressor section 14, a combustor section 16, and a
turbine section 18 disposed about a longitudinal axis A. The fan
section 12 drives air along a bypass flow path B that may bypass
the compressor section 14, the combustor section 16, and the
turbine section 18. The compressor section 14 draws air in along a
core flow path C where air is compressed by the compressor section
14 and is provided to or communicated to the combustor section 16.
The compressed air is heated by the combustor section 16 to
generate a high pressure exhaust gas stream that expands through
the turbine section 18. The turbine section 18 extracts energy from
the high pressure exhaust gas stream to drive the fan section 12
and the compressor section 14.
[0032] The gas turbine engine 10 further includes a low-speed spool
20 and a high-speed spool 22 that are configured to rotate the fan
section 12, the compressor section 14, and the turbine section 18
about the longitudinal axis A. The low-speed spool 20 may connect a
fan 30 of the fan section 12 and a low-pressure compressor portion
32 of the compressor section 14 to a low-pressure turbine portion
34 of the turbine section 18. In the illustrated embodiment, the
turbine section 18 can include a rotating disc assembly 35. The
high-speed spool 22 may connect a high pressure compressor portion
40 of the compressor section 14 and a high pressure turbine portion
42 of the turbine section 18. The fan 30 includes a fan rotor or
fan hub 50 that carries a fan blade 52. The fan blade 52 radially
extends from the fan hub 50.
[0033] In the illustrated embodiment, the combustor section 16 can
have operating temperatures that exceed the melting point of the
materials forming the combustor section 16 components. The
combustor section 16 can include dilution holes to condition
combustion air.
[0034] Referring to FIG. 2, the combustor section 16 is shown. In
the illustrated embodiment, the combustor section 16 includes a
combustor panel assembly 17 with a combustor liner 60 and a
combustor panel 62. In the illustrated embodiment, the combustor
liner 60 and the combustor panel 62 can be formed from any suitable
material. In the illustrated embodiment, the combustor panel 62
defines an annular shaped combustion chamber. Further, the
combustor liner 60 is spaced apart from the combustor panel 62 to
form an air passage between the combustor panel 62 and the
combustor liner 60 to provide conditioning air. In certain
embodiments, the combustor panel 62 and the combustor liner 60 can
include dilution holes to condition combustion air flow.
[0035] As shown in FIGS. 3A and 3B, in the illustrated embodiment,
the combustor liner 60 includes liner dilution holes 64 and the
combustor panel 62 includes panel dilution holes 66. In the
illustrated embodiment, the air exiting the compressor section 14
of the gas turbine engine 10 is typically split or bifurcated, with
a portion of the compressed air being used for combustion, and a
portion of the compressed air being directed to the liner dilution
holes 64 and the panel dilution holes 66 for conditioning. In the
illustrated embodiment, the liner dilution holes 64 and the panel
dilution holes 66 can receive conditioning airflow and provide
conditioning airflow to combustor components. In certain
embodiments, the panel dilution holes 66 receive airflow from the
liner dilution holes 64.
[0036] In certain embodiments, the combustor panel 62 includes an
alignment stud 68. Similarly, in certain embodiments, the combustor
liner 60 includes an alignment hole 69. In certain embodiments, the
alignment hole 69 can receive the alignment stud 68 to facilitate
alignment and installation. Further, the use of the alignment hole
69 with the alignment stud 68 can allow for the liner dilution
holes 64 to be aligned with the panel dilution holes 66.
[0037] Referring to FIGS. 3A and 3B, a grommet 70 for use with the
combustor panel assembly 17 is shown. In the illustrated
embodiment, the grommet 70 includes an upper radius 72, a lower
radius 74, an inner surface 76 and an outer surface 78. In the
illustrated embodiment, the grommet 70 can be disposed within the
liner dilution hole 64 and the panel dilution hole 66 to provide a
smooth continuous flow path for the conditioning air flow. The use
of the grommet 70 can minimize flow restrictions for conditioning
airflow while providing high-temperature resistance within the
combustor section 16.
[0038] In the illustrated embodiment, the grommet 70 is formed from
a different material than the combustor panel 62 and the combustor
liner 60. In certain embodiments, the grommet 70 is formed from a
ceramic matrix composite. In certain embodiments, the grommet 70 is
formed from monolithic ceramics. In certain embodiments, the
grommet 70 is formed from molybdenum alloys. In certain
embodiments, the grommet 70 is formed from nickel alloys.
Advantageously, the material of grommet 70 is selected to prevent
melting or cracking of the grommet 70. Further, in certain
embodiments, the materials of the grommet 70 are selected to have a
low thermal mass to minimize stored thermal energy. Further, the
material of grommet 70 can prevent the formation of oxidation.
[0039] In the illustrated embodiment, the grommet 70 is generally
shaped to smoothly direct air from the outside the combustor liner
60, through the liner dilution hole 64 and through the panel
dilution hole 66.
[0040] In certain embodiments, the grommet 70 is fastened to the
combustor panel 62 via the panel dilution hole 66. In certain
embodiments, a pressure differential keeps the grommet 70 attached
to the combustor panel 62. In other embodiments, the grommet 70 is
fastened to the combustor liner 60 or a combination of the
combustor panel 62 and the combustor liner 60. In certain
embodiments, the grommet 70 is fastened via fasteners, such as
nuts, bolts, etc., brazing, welding, or a threaded connection.
[0041] In the illustrated embodiment, the geometry of the grommet
70 reduces flow restriction for conditioning flows entering the
liner dilution hole 64 and the panel dilution hole 66, allowing for
less work to be performed by the compressor of the engine. In the
illustrated embodiment, the grommet 70 generally has a
frustroconical shape, with an upper radius 72 and a lower radius
74. In the illustrated embodiment, the grommet 70 converges from
the larger upper radius 72 to the smaller lower radius 74. In the
illustrated embodiment, the inner surface 76 provides a continuous,
uninterrupted flow path that transitions from the larger upper
radius 72 to the smaller lower radius 74. In the illustrated
embodiment, the outer surface 78 can interface with the combustor
liner 60, the liner dilution hole 64, the combustor panel 62, and
the panel dilution hole 66.
[0042] Advantageously, the materials and geometry of the grommet 70
allow for more efficient engine operation, increased durability,
higher temperature operation, prevents thermal and mechanical
failure, and allows for increased "time on wing" metrics.
[0043] While the present disclosure has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the present disclosure is not limited to
such disclosed embodiments. Rather, the present disclosure 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 present
disclosure. Additionally, while various embodiments of the present
disclosure have been described, it is to be understood that aspects
of the present disclosure may include only some of the described
embodiments. Accordingly, the present disclosure is not to be seen
as limited by the foregoing description, but is only limited by the
scope of the appended claims.
* * * * *