U.S. patent application number 16/527299 was filed with the patent office on 2020-01-23 for dual-wall impingement, convection, effusion combustor tile.
The applicant listed for this patent is Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.. Invention is credited to Michael S. Bell, Tab M. Heffernan, Jack D. Petty, SR., Mohan Razdan, Michel S. Smallwood.
Application Number | 20200025378 16/527299 |
Document ID | / |
Family ID | 50943516 |
Filed Date | 2020-01-23 |
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United States Patent
Application |
20200025378 |
Kind Code |
A1 |
Petty, SR.; Jack D. ; et
al. |
January 23, 2020 |
DUAL-WALL IMPINGEMENT, CONVECTION, EFFUSION COMBUSTOR TILE
Abstract
A gas turbine engine includes a combustor having a dual-wall
impingement convention effusion combustor tile assembly. The
dual-wall tile assembly provides a cooling air flow channel and
attachments for securing the tile to the cold skin liner of the
combustor. Cooling is more efficient in part due to the dual wall
construction and in part due to reduced parasitic leakage, and the
design is less sensitive to attachment features which operate at
lower temperatures.
Inventors: |
Petty, SR.; Jack D.;
(Indianapolis, IN) ; Razdan; Mohan; (Indianapolis,
IN) ; Bell; Michael S.; (Indianapolis, IN) ;
Smallwood; Michel S.; (Greenwood, IN) ; Heffernan;
Tab M.; (Plainfield, IN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rolls-Royce Corporation
Rolls-Royce North American Technologies, Inc. |
Indianapolis
Indianapolis |
IN
IN |
US
US |
|
|
Family ID: |
50943516 |
Appl. No.: |
16/527299 |
Filed: |
July 31, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
14137267 |
Dec 20, 2013 |
10451276 |
|
|
16527299 |
|
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|
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61773082 |
Mar 5, 2013 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2260/202 20130101;
Y02T 50/60 20130101; Y02T 50/675 20130101; F23R 3/007 20130101;
F23R 3/002 20130101; F23R 3/06 20130101; F05D 2230/21 20130101;
F23R 2900/03043 20130101; F23R 2900/03042 20130101; F23R 2900/03041
20130101; F05D 2260/201 20130101; F05D 2230/22 20130101; F23R
2900/03044 20130101; F23R 3/60 20130101 |
International
Class: |
F23R 3/00 20060101
F23R003/00; F23R 3/60 20060101 F23R003/60; F23R 3/06 20060101
F23R003/06 |
Claims
1.-20. (canceled)
21. A gas turbine engine having a combustor comprising: a liner
having an inner surface, the inner surface having a plurality of
arcuately shaped surfaces; and a plurality of tile assemblies, each
tile assembly including a first wall element and a second wall
element spaced radially from the first wall element, each of the
plurality of tile assemblies secured to the inner surface of the
liner via at least one securing member for securing each tile
assembly to the liner, each tile assembly forming a cooling plenum
between the inner surface of the liner and the first wall element;
wherein a first tile assembly of the plurality of tile assemblies
is positioned on a first surface of the plurality of arcuately
shaped surfaces, and a second tile assembly of the plurality of
tile assemblies is positioned on a second surface of the arcuately
shaped surfaces adjacent to and radially offset from the first
surface, such that a first edge of the first tile assembly is
positioned proximate a second edge of the second tile assembly and
the first edge and the second edge are radially offset from each
other forming a radial gap.
22. The gas turbine of claim 21, further comprising a plurality of
pedestal members positioned between the first wall element and the
second wall element, such that an interconnected plurality of air
channels is formed between the first wall element and the second
wall element in each tile assembly.
23. The gas turbine of claim 22, wherein each tile assembly of the
plurality of tile assemblies includes the first wall element formed
as a first substantially planar or curved member, the second wall
element formed respectively as a second substantially planar or
curved member, wherein the plurality of pedestal members form
spacers for offsetting the first substantially planar or curved
member from the second substantially planar or curved member.
24. The gas turbine of claim 23, wherein the at least one securing
member is connected to one of the first substantially planar or
curved member and the second substantially planar or curved
member.
25. The gas turbine of claim 22, wherein each pedestal member of
the plurality of pedestal members is square-shaped.
26. The gas turbine of claim 21, wherein the first wall element
includes a plurality of cooling entry holes that are arranged on
the first wall element in a first array comprising multiple rows of
the cooling entry holes, and the second wall element includes a
plurality of exit holes that are arranged on the second wall
element in a second array comprising multiple rows of the exit
holes.
27. The gas turbine of claim 26, wherein the cooling plenum passes
air orthogonally from the cooling plenum through the plurality of
cooling entry holes and to the interconnected plurality of air
channels between the first wall element and the second wall
element, and through the plurality of exit holes.
28. The gas turbine of claim 27, further comprising a rail formed
on each tile assembly and extending around an outer perimeter of
each tile assembly, the rail extending from the first wall element
and engaging the inner surface of the liner to form the cooling
plenum of each tile assembly.
29. The gas turbine of claim 21, wherein each tile assembly of the
plurality of tile assemblies is a single piece tile.
30. The gas turbine of claim 21, wherein each tile assembly is
formed of a ceramic composite material or a metallic material.
31. The gas turbine of claim 21, wherein each of the first wall
element and second wall element of each tile assembly includes a
small dilution port and/or a large dilution port that is larger
than the small dilution port.
32. The gas turbine of claim 21, wherein the at least one securing
member further comprises a mounting stud passing through the liner
and secured at one end to one of the first wall element and second
wall element, the mounting stud secured at another end to a wall of
the liner.
33. The gas turbine of claim 21, wherein the single piece tile is a
single piece cast tile.
34. The gas turbine of claim 21, wherein the single piece tile is a
direct metal laser sintered tile.
35. The gas turbine of claim 21, wherein the plurality of pedestal
members is a two-dimensional array of pedestals arranged in a
pattern forming the interconnected plurality of air channels, the
two-dimensional array of pedestals forming multiple rows of
pedestals positioned side-by-side and extending in a first
direction, and forming multiple rows of pedestals positioned
side-by-side and extending in a second direction that is
approximately orthogonal to the first direction.
36. The gas turbine of claim 21, wherein the first surface and the
second surface are stepped forming a stepped location between the
first surface and the second surface, and the first edge and the
second edge are proximate the stepped location such that the radial
gap is formed at the stepped location.
37. A combustor for a gas turbine engine, comprising: a liner
having an inner surface, the inner surface having arcuately shaped
surfaces; two tile assemblies, each tile assembly including a first
wall element and a second wall element spaced radially from the
first wall element, each of the plurality of tile assemblies
secured to the inner surface of the liner via a respective securing
member for securing each tile assembly to the liner, each tile
assembly forming a cooling plenum between the inner surface of the
liner and the first wall element; wherein one of the two tile
assemblies is positioned on a first surface of the arcuately shaped
surfaces, and another of the two tile assemblies is positioned on a
second surface of the arcuately shaped surfaces adjacent to and
radially offset from the first surface, such that one edge of one
of the two tile assemblies is positioned proximate one edge of the
other of the two tile assemblies, and the edges are radially offset
from each other forming a radial gap.
38. The combustor of claim 37, further comprising a plurality of
pedestal members positioned between the first wall element and the
second wall element, such that an interconnected plurality of air
channels is formed between the first wall element and the second
wall element in each tile assembly.
39. The combustor of claim 38, wherein each tile assembly of the
two tile assemblies includes the first wall element formed as a
first substantially planar or curved member, the second wall
element formed respectively as a second substantially planar or
curved member, wherein the plurality of pedestal members form
spacers for offsetting the first substantially planar or curved
member from the second substantially planar or curved member.
40. The combustor claim 39, wherein the respective securing member
is connected to one of the first substantially planar or curved
member and the second substantially planar or curved member.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation of U.S. patent
application Ser. No. 14/137,267, filed Dec. 20, 2013, which claims
priority to U.S. Provisional Patent Application No. 61/773,082,
filed Mar. 5, 2013, the contents of which are hereby incorporated
in their entirety.
FIELD OF TECHNOLOGY
[0002] A gas turbine engine uses a combustor and a combustor liner,
and more particularly, a liner having wall elements to form a dual
wall cooling system.
BACKGROUND
[0003] Gas turbine engines are used extensively in high performance
aircraft and they employ fans, compressors, combustors and turbines
and during operation they generate energies and air flows that
impact the performance of the engine's systems. A gas turbine may
employ one or more combustors that serve as the fuel preparation
and ignition chambers for generating the temperature rise which is
required to drive the turbine blades. Typical combustors may use
inner and outer liners that define an annular combustion chamber in
which the fuel and air mixtures are combusted. The inner and outer
liners are radially offset from the combustor casings such that
inner and outer passage ways are defined between the respective
inner and outer liners and casings.
[0004] In order to improve the thrust and fuel consumption of gas
turbine engines, i.e., the thermal efficiency, it is necessary to
use high compressor exit pressures and combustion exit
temperatures. Higher compressor pressures also give rise to higher
compressor exit temperatures supplied to the combustion chamber,
which results in a combustor chamber experiencing much higher
temperatures than are present in most conventional combustor
designs.
[0005] A need exists to provide effective cooling of the combustion
chamber walls. Various cooling methods have been proposed including
the provision of a doubled walled combustion chamber whereby
cooling air is directed into a gap between spaced outer and inner
walls, thus cooling the inner wall. This air is then exhausted into
the combustion chamber through apertures in the inner wall. The
inner wall may be comprised of a number of heat resistant
tiles.
[0006] Combustion chamber walls which comprise two or more layers
are advantageous in that they only require a relatively small flow
of air to achieve adequate wall cooling. However, hot spots may
form in certain areas of the combustion chamber wall. This problem
is heightened as temperatures within the combustion chamber which
can exceed 3,500 degrees F. Such harsh environmental conditions may
prematurely reduce the life of the liner of the combustor. In
addition, loss of tile attachment and subsequent component distress
remains an engineering challenge in current combustor
technology.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] While the claims are not limited to a specific illustration,
an appreciation of the various aspects is best gained through a
discussion of various examples thereof. Referring now to the
drawings, exemplary illustrations are shown in detail. Although the
drawings represent the illustrations, the drawings are not
necessarily to scale and certain features may be exaggerated to
better illustrate and explain an innovative aspect of an example.
Further, the exemplary illustrations described herein are not
intended to be exhaustive or otherwise limiting or restricted to
the precise form and configuration shown in the drawings and
disclosed in the following detailed description. Exemplary
illustrations are described in detail by referring to the drawings
as follows:
[0008] FIG. 1 illustrates a schematic diagram of a gas turbine
engine employing an improved combustor assembly;
[0009] FIG. 2 illustrates a side sectional view of a gas turbine
engine with an improved tiled combustor assembly;
[0010] FIG. 3 illustrates a partial perspective sectional view of a
gas turbine engine with a tiled combustor assembly;
[0011] FIG. 4 illustrates a partial sectional view of a combustor
assembly showing the installation of a DICE tile;
[0012] FIG. 5 illustrates a perspective view a Dual-Wall
Impingement, Convection, Effusion (DICE) combustor tile, showing
the hot side and a cold side;
[0013] FIG. 6 illustrates an enlarged perspective view of the cold
side of the DICE tile, showing a cut away depicting the pedestals
and air channels; and
[0014] FIG. 7 illustrates an enlarged side cross-sectional view of
a DICE tile assembly for use in a combustor of a gas turbine
engine.
DETAILED DESCRIPTION
[0015] A gas turbine engine combustor tile design includes an
exemplary high temperature capable dual wall combustor tile
attached to a lower temperature capable cold skin of a combustor
liner. The wall cooling is accomplished by feeding air through
holes in the cold skin. The air impinges on the back side of the
hot tile and then flows out ejection slots or holes into the hot
flow path. The gap formed between the cold skin and the tile hot
side surface forms a cooling channel which may be enhanced by the
presence of turbulators or pin fins. This interface gap is
maintained by pulling the hot tile into the cold skin via
attachment features such as studs. Standoffs on the back side of
the tile land against the cold skin and react against the fastener
preload in order to maintain position of the tiles during engine
operation.
[0016] The exemplary tile assembly 42 is a dual-wall impingement,
convection, effusion combustor tile and method of constructing a
tile which offers significant benefit over conventional combustor
wall cooling systems in terms of temperature capability and cooling
flow requirements. The embodiment disclosed herein blends the
technology of a tiled combustor liner with an integral dual wall
cooling system to form a novel tile assembly.
[0017] FIG. 1 illustrates a gas turbine engine 10, which includes a
fan 12, a low pressure compressor and a high pressure compressor,
14 and 16, a combustor 18, and a high pressure turbine,
intermediate pressure, and low pressure turbine, 20 thru 22,
respectively. The high pressure compressor 16 is connected to a
first rotor shaft 24, the low pressure compressor 14 is connected
to a second rotor shaft 26, and the fan 12 is connected to a third
rotor shaft 43. The shafts extend axially and are parallel to a
longitudinal center line axis 28. It will be appreciated that the
improvements disclosed herein can be used with gas turbine engines
that incorporate a single or two-shaft architecture.
[0018] Ambient air 30 enters the fan 12 and is directed across a
fan rotor 32 in an annular duct 34, which in part is circumscribed
by fan case 36. The bypass airflow 38 provides engine thrust while
the primary gas stream 40 is directed to the compressors 14 and 16,
combustor 18, and the turbines 20 thru 22. The gas turbine engine
10 includes an improved combustor 18 having a tile assembly 42, the
details of the exemplary design are set forth herein.
[0019] FIG. 2 illustrates a side sectional view of the combustor 18
with a plurality of tile assemblies 42 that are secured to a cold
skin or outer surface of a liner 44. A combustor outer case 46
circumscribes a combustor shell 48 and a fuel nozzle 50 provides
pressurized fuel 52 to a combustor chamber 54. The combusted fuel
may be ignited by an igniter (not shown) which in turn subjects the
chamber 54 to elevated temperatures which can exceed 3,500 degrees
F. Such arrangement causes extreme temperatures to impinge upon the
hot surface 56 of each tile assembly 42. A fastener 60 secures each
tile assembly 42 to the liner 44 of the combustor 18. The tile
assembly 42 is serviceable and may be replaced when it is damaged
or is otherwise sufficiently depleted in performance quality.
[0020] FIG. 3 illustrates the shell 48 of the combustor 18 having a
plurality of tile assemblies 42 spaced apart and secured to the
inner surface 58 of the skin 44. The inner surface 58 is protected
by the tile assembly 42 at substantially the entire inner surface
58 of the skin 44. A gap 60 is maintained between the inner surface
58 and the assembly 42. The cooling effectiveness of each dual wall
tile assembly 42 does not rely on accurately maintaining the gap 60
between the tile standoff features and the cold skin 44, as is the
case for conventional tiles. In addition, the tile attachment
feature or fastener 60 will be maintained at a lower temperature as
compared to a conventional tile system. This arrangement results in
a robust mechanical attachment that resists creep and loss of
preload, both of which translate into improved component
reliability/durability and reduced parasitic leakage. Parasitic
leakage which bypasses the cooling circuit translates into lower
overall cooling effectiveness.
[0021] Reduced combustor wall cooling translates into a competitive
advantage in term of combustor pattern factor control, radial
temperature profile control, efficiency, and emissions reduction.
The integral dual wall metallic combustor tile assembly 42 offers
significant advantages over conventional tiles including but not
limited to a reduction in wall cooling flow, a cooler tile
attachment (improved reliability/durability), reduced tile leakage
and the associated penalty in cooling effectiveness due to leakage,
and a more robust mechanical design in terms of less sensitivity to
cold skin and tile geometric tolerances/operating deflections.
[0022] FIG. 4 illustrates a cut away of the combustor 18 showing
one tile assembly 42 shown offset from the cold skin inner surface
58 of a combustor 18. A tile mounting surface 62 on the cold skin
inner surface 58 provides a mounting space for receiving each tile
assembly 42. The tile assembly 42 is shown offset from the surface
62 for illustrative purposes. The tile mounting surface 62 has
substantially the same profile as the profile of the tile assembly
42. The mounting surface 62 has a plurality of apertures 64 for
providing cooling air flow. Small and large dilution ports, 66 and
68, provide large airflow passageways through the skin 44. Surface
70 of the tile assembly 42 represents the hot side of the tile
which is subjected to extreme heat conditions.
[0023] FIG. 5 illustrates an exploded view showing a first wall or
cold side 72 and a second wall or hot side 70 of the tile assembly
42. The walls 70 and 72 may be substantially planner or of high
curvature in configuration. The cold side 72 and the hot side 70
are shown split apart for illustration purposes only. The hot side
70 represents a front side of the assembly 42 and the cold side 72
represents a back side of the assembly 42. The assembly 42 could be
constructed from metal or a composite ceramic material.
[0024] The hot side 70 includes cooling exit holes or slots 74,
small dilutions holes 76, and large dilution holes 78. The cold
side 72 of the tile assembly 42 includes cooling entry holes 73,
and co-aligned small dilution ports 76 and large dilution ports 78.
The hot side of the tile assembly 42 also includes a plurality of
cooling exit holes 74. A plurality of threaded studs or fasteners
60 extend from a surface 80 of the first wall 72. A rail or lip 82
protrudes from the surface 80 around the perimeter of the first
wall 72 and is rhombus shaped but other shapes are contemplated.
The rail 82 may be integral with the surface 80. A surface of the
rail 82 impinges upon the inner surface 58 of the cold skin 44. The
rail creates a plenum 92 to feed the cooling holes 74 and operates
to create an offset from a surface of the cold skin.
[0025] FIG. 6 illustrates an enlarged perspective view of the first
wall or cold side 72 which is the cold side of the assembly 42. A
cut away section 84 is depicted in the lower portion of FIG. 6
which illustrates, under the outer surface 80, a plurality of
square-shaped pedestals 86 that are offset by air channels 88. The
pedestal pattern 90 consisting of the pedestals 86 and air channels
88 shown is exemplary in nature and other geometric configurations
are contemplated. The pattern 90 extends underneath substantially
the entire surface 80 and provides air flow channels 88 for aiding
cooler air distribution about the first and second walls 70 and
72.
[0026] FIG. 7 illustrates a cross-sectional view taken from line
7-7 of FIG. 2, depicting a tile assembly 42 secured to a cold skin
44. The tile assembly 42 may be constructed primarily of a
composite ceramic material (CMC), but other configurations could
include a metallic two-piece diffusion or braze bonded assembly of
cast, wrought, or direct metal laser sintered (a/k/a direct laser
deposition or additive manufactured) components, or a single piece
cast or direct metal laser sintered tile. The tile's hot surface
can either be as manufactured or can have a thermal and/or
environmental barrier coating applied. The coating could be
ceramic. The cross-section that is shown in FIG. 7 includes a stud
60 extending through the cold skin 44 of the combustor. A nut or
other anchor 61 can be provided as well so as to provide a
mechanical securing mechanism for attaching each assembly 42 to the
skin 44. The cool side of the DICE tile assembly 42 has a rail 82
upwardly impinging upon the underside 58 of the cold skin 44, thus
creating a plenum 92. The wall of the cold side 72 is offset from
the wall 70 of the hot side by pedestals 86, the distance of which
can be modified to enhance air channel 88 capacities and volumes.
Normal, angled, and/or shaped cooling holes 74 may extend from the
air channels 88, through the hot side wall 72, and then into the
interior 54 of the combustion chamber 18.
[0027] It will be appreciated that the aforementioned method and
devices may be modified to have some components and steps removed,
or may have additional components and steps added, all of which are
deemed to be within the spirit of the present disclosure. Even
though the present disclosure has been described in detail with
reference to specific embodiments, it will be appreciated that the
various modifications and changes can be made to these embodiments
without departing from the scope of the present disclosure as set
forth in the claims. The specification and the drawings are to be
regarded as an illustrative thought instead of merely restrictive
thought.
* * * * *