U.S. patent application number 14/884506 was filed with the patent office on 2016-09-15 for modified floatwall panel dilution hole cooling.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to James B. Hoke, David Kwoka.
Application Number | 20160265777 14/884506 |
Document ID | / |
Family ID | 54364971 |
Filed Date | 2016-09-15 |
United States Patent
Application |
20160265777 |
Kind Code |
A1 |
Hoke; James B. ; et
al. |
September 15, 2016 |
MODIFIED FLOATWALL PANEL DILUTION HOLE COOLING
Abstract
Aspects of the disclosure are directed to a liner of an
aircraft. The liner comprises a panel including at least one
dilution hole, a rail coupled to the panel, and at least one
effusion cooling hole located between a wall of the at least one
dilution hole and a side of the rail. The liner may be associated
with a combustion engine of the aircraft.
Inventors: |
Hoke; James B.; (Tolland,
CT) ; Kwoka; David; (South Glastonbury, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Hartford |
CT |
US |
|
|
Family ID: |
54364971 |
Appl. No.: |
14/884506 |
Filed: |
October 15, 2015 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
62065312 |
Oct 17, 2014 |
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/06 20130101; F23R
2900/03041 20130101; F23R 3/60 20130101; Y02T 50/675 20130101; Y02T
50/60 20130101; F23R 3/002 20130101 |
International
Class: |
F23R 3/06 20060101
F23R003/06; F23R 3/60 20060101 F23R003/60; F23R 3/00 20060101
F23R003/00 |
Claims
1. A liner of an aircraft, comprising: a panel including at least
one dilution hole; a rail coupled to the panel; and at least one
effusion cooling hole located between a wall of the at least one
dilution hole and a side of the rail.
2. The liner of claim 1, wherein the at least one effusion cooling
hole includes a plurality of effusion cooling holes.
3. The liner of claim 1, wherein the rail is spaced from the wall
by a distance of approximately 6.4 millimeters.
4. The liner of claim 3, wherein the rail is spaced from the wall
in a radial direction away from the at least one dilution hole.
5. The liner of claim 1, further comprising: at least a second
effusion cooling hole located between a second side of the rail and
a perimeter of the panel.
6. The liner of claim 1, further comprising: a shell coupled to the
panel.
7. The liner of claim 6, wherein the rail is configured to seal the
panel against the shell to prevent leakage.
8. The liner of claim 1, wherein the liner is associated with a
combustion engine of the aircraft.
Description
[0001] This application claims priority to U.S. patent application
Ser. No. 62/065,312 filed Oct. 17, 2014.
BACKGROUND
[0002] Engine combustors have exhibited hot metal temperatures in
liner panels in proximity to combustion/dilution holes. These high
temperatures are largely a result of the difficulty in delivering a
cooling fluid (e.g., air) to the metal mass (e.g., grommet) that
surrounds the hole. Accordingly, a change is needed to the panel
and an associating holding structure (e.g., shell) in the region
around the dilution holes in order to enhance the availability and
reliability of the liner.
BRIEF SUMMARY
[0003] The following presents a simplified summary in order to
provide a basic understanding of some aspects of the disclosure.
The summary is not an extensive overview of the disclosure. It is
neither intended to identify key or critical elements of the
disclosure nor to delineate the scope of the disclosure. The
following summary merely presents some concepts of the disclosure
in a simplified form as a prelude to the description below.
[0004] Aspects of the disclosure are directed to a liner of an
aircraft, comprising: a panel including at least one dilution hole,
a rail coupled to the panel, and at least one effusion cooling hole
located between a wall of the at least one dilution hole and a side
of the rail. In some embodiments, the at least one effusion cooling
hole includes a plurality of effusion cooling holes. In some
embodiments, the rail is spaced from the wall by a distance of
approximately 6.4 millimeters. In some embodiments, the rail is
spaced from the wall in a radial direction away from the at least
one dilution hole. In some embodiments, the liner further comprises
at least a second effusion cooling hole located between a second
side of the rail and a perimeter of the panel. In some embodiments,
the liner further comprises a shell coupled to the panel. In some
embodiments, the rail is configured to seal the panel against the
shell to prevent leakage. In some embodiments, the liner is
associated with a combustion engine of the aircraft.
BRIEF DESCRIPTION OF THE DRAWINGS
[0005] The present disclosure is illustrated by way of example and
not limited in the accompanying figures in which like reference
numerals indicate similar elements.
[0006] FIG. 1 illustrates an exemplary gas turbine engine.
[0007] FIG. 2 illustrates a portion of a liner incorporating
grommets in accordance with the prior art.
[0008] FIG. 3 illustrates the liner of FIG. 2 incorporating a shell
in accordance with the prior art.
[0009] FIG. 4 illustrates a first view of a liner incorporating a
rail and effusion cooling holes in accordance with aspects of the
disclosure.
[0010] FIG. 5 illustrates a second view of the liner of FIG. 4.
DETAILED DESCRIPTION
[0011] It is noted that various connections are set forth between
elements in the following description and in the drawings (the
contents of which are included in this disclosure by way of
reference). It is noted that these connections are general and,
unless specified otherwise, may be direct or indirect and that this
specification is not intended to be limiting in this respect. A
coupling between two or more entities may refer to a direct
connection or an indirect connection. An indirect connection may
incorporate one or more intervening entities.
[0012] In accordance with various aspects of the disclosure,
apparatuses, systems and methods are described for cooling a liner
of an aircraft combustor. The liner may include a panel coupled to
a holding structure/shell. The coupling may be facilitated by one
or more rails. Effusion cooling holes may be incorporated into the
panel in order to cool the panel.
[0013] Aspects of the disclosure may be applied in connection with
an aircraft, or portion thereof. For example, aspects of the
disclosure may be applied in connection with a gas turbine engine.
FIG. 1 is a side-sectional illustration of an exemplary gas turbine
engine 10. The engine 10 includes a compressor section 12, a
turbine section 14 and one or more engine hot sections. The engine
hot sections may include, for example, a first engine hot section
16 configured as a combustor section and a second engine hot
section 18 configured as an augmentor section. The compressor
section 12, the first engine hot section 16, the turbine section 14
and the second engine hot section 18 may be sequentially aligned
along an axial centerline 20 between a forward engine airflow inlet
22 and an aft engine airflow exhaust 24.
[0014] Referring to FIG. 2, a portion of a liner 200 is shown. The
liner 200 includes a panel 204. The panel 204 may be referred to
as, or correspond to, a float wall panel. A float wall panel is a
panel that is designed to expand under a heat-load without
cracking. The panel 204 may take the form of a tiled structure that
includes threaded studs 206 that allow the panel 204 to be bolted
to a shell 302 (see FIG. 3). The panel 204 includes grommets 208.
At the center of the grommets 208 are dilution holes 210 that
provide a combustion flow to the panel 204 and the associated
combustor (e.g., first engine hot section 16 of FIG. 1). The panel
204 interfaces to the high temperatures associated with the
combustor.
[0015] Referring to FIG. 3, the liner 200 of FIG. 2 is shown in
more detail. The liner 200 includes the shell 302 at least
partially coupled to the panel 204 via a grommet 208. The shell 302
may include impingement holes (not shown) as would be known to one
of skill in the art. Also shown is a cooling hole 312 incorporated
into the panel 204. For purposes of reference, a center line
associated with the dilution hole 210 is shown via a dashed line in
FIG. 3. A size (e.g., a diameter) of the dilution hole 210 may be
referenced with respect to an edge/wall 208a of the grommet
208.
[0016] As described above, in can be difficult to provide a
sufficient cooling flow to the panel 204 in the proximity of the
grommet 208 (via, e.g., the cooling hole 312), due in large to the
mass/thickness of the grommet 208 relative to the remainder of the
panel 204. If an insufficient cooling flow is provided, the panel
204/grommet 208 may be subject to distress (e.g., melting and
oxidation).
[0017] FIGS. 4-5 illustrate various views of a liner 400. The liner
400 includes a shell 402 (which may be similar to, or correspond
to, the shell 302 of FIG. 3) coupled to a panel 404. The shell 402
may be at least partially coupled to the panel 404 via one or more
rails 418. For example, the rail 418 may seal the panel 404 against
the shell 402 to prevent leakage. The rail 418 may be cast in
connection with the panel 404, such that the rail 418 may be
integral to, and may be made of the same material as, the panel
404.
[0018] The rail 418 may be spaced (in a radial direction) from an
edge/wall 408a associated with the dilution hole 210 by a distance
D. In some embodiments, the distance D may be approximately 6.4
millimeters. The spacing D allows for the insertion of one or more
effusion cooling holes 412 adjacent to the wall 408a, or in a
location corresponding to a region of the panel 404 between the
wall 408a and a first side of the rail 418. The holes 412 have a
high pressure loss through them. Additional cooling holes 422 may
be included in the panel 404 on the other/second side of the rail
418, in between the rail 418 and a perimeter 504a of the panel
404.
[0019] Technical effects and benefits of this disclosure include a
cost-effective design for cooling a panel. Cooling may be provided
via effusion holes incorporated in the panel between a rail and an
edge/wall of a dilution hole.
[0020] Aspects of the disclosure have been described in terms of
illustrative embodiments thereof Numerous other embodiments,
modifications, and variations within the scope and spirit of the
appended claims will occur to persons of ordinary skill in the art
from a review of this disclosure. For example, one of ordinary
skill in the art will appreciate that the steps described in
conjunction with the illustrative figures may be performed in other
than the recited order, and that one or more steps illustrated may
be optional in accordance with aspects of the disclosure. One or
more features described in connection with a first embodiment may
be combined with one or more features of one or more additional
embodiments.
* * * * *