U.S. patent application number 14/673629 was filed with the patent office on 2016-10-06 for combustor configurations for a gas turbine engine.
The applicant listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to Jonathan Jeffery EASTWOOD, David KWOKA, Reza REZVANI.
Application Number | 20160290642 14/673629 |
Document ID | / |
Family ID | 55650220 |
Filed Date | 2016-10-06 |
United States Patent
Application |
20160290642 |
Kind Code |
A1 |
KWOKA; David ; et
al. |
October 6, 2016 |
COMBUSTOR CONFIGURATIONS FOR A GAS TURBINE ENGINE
Abstract
The present disclosure relates to combustor configurations and
components for a gas turbine engine. In one embodiment, a combustor
for a gas turbine engine includes a support structure and a
plurality of panels mounted to the structure. The plurality of
panels define a combustion cavity of the combustor. The plurality
of panels include a first panel having a leading and trailing edge,
and a second panel having a leading edge and trailing edge, wherein
a trailing edge of the first panel extends beyond the leading edge
of the second panel and wherein the second panel is mounted to the
support structure aft of the first panel.
Inventors: |
KWOKA; David; (South
Glastonbury, CT) ; REZVANI; Reza; (Manchester,
CT) ; EASTWOOD; Jonathan Jeffery; (Newington,
CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Farmington |
CT |
US |
|
|
Family ID: |
55650220 |
Appl. No.: |
14/673629 |
Filed: |
March 30, 2015 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/08 20130101; F23R
3/06 20130101; F23R 3/44 20130101; F23R 3/002 20130101 |
International
Class: |
F23R 3/00 20060101
F23R003/00; F23R 3/44 20060101 F23R003/44; F23R 3/06 20060101
F23R003/06 |
Claims
1. A combustor for a gas turbine engine, the combustor comprising:
a support structure; and a plurality of panels mounted to the
structure, the plurality of panels defining a combustion cavity of
the combustor, wherein the plurality of panels include a first
panel having a leading and trailing edge, and a second panel having
a leading edge and trailing edge, wherein a trailing edge of the
first panel extends beyond the leading edge of the second panel and
wherein the second panel is mounted to the support structure aft of
the first panel.
2. The combustor of claim 1, wherein the support structure is an
annular structure including an inner diameter structure and outer
diameter structure, and wherein the plurality of panels are mounted
to at least one of the inner diameter structure and outer diameter
structure.
3. The combustor of claim 1, wherein the plurality of panels are
heat shield panels.
4. The combustor of claim 1, wherein an air gap between the
trailing edge of the first panel and the leading edge of the second
panel forms at least a portion of a circumferential air gap for the
combustor.
5. The combustor of claim 1, wherein the trailing edge of the first
panel extends beyond the leading edge of the second panel to
provide an air flow gap between the first and second panels and
wherein portion of the first panel associated with the leading edge
is configured to prevent a gas path flow within the combustor to
enter the air flow gap.
6. The combustor of claim 1, wherein the first panel extends over
the second panel along the entire length of the first panel by an
amount within the range of 0.5 cm to 2 cm.
7. The combustor of claim 1, wherein the second panel includes
effusion holes positioned along the leading edge of the second
panel.
8. The combustor of claim 1, wherein leading edge of the second
panel is chamfered.
9. The combustor of claim 1, wherein leading edge of the second
panel includes one or more features to provide airflow when the
trailing edge of the first panel contacts the leading edge of the
second panel.
10. The combustor of claim 9, wherein the one or more features
include groves in the leading edge of the second panel to provide
said airflow.
11. A gas turbine engine comprising: a combustor having a support
structure; and a plurality of panels mounted to the support
structure, the plurality of panels defining a combustion cavity of
the combustor, wherein the plurality of panels include a first
panel having a leading and trailing edge, and a second panel having
a leading edge and trailing edge, wherein a trailing edge of the
first panel extends beyond the leading edge of the second panel and
wherein the second panel is mounted to the support structure aft of
the first panel.
12. The gas turbine engine of claim 10, wherein the support
structure is an annular structure including an inner diameter
structure and outer diameter structure, and wherein the plurality
of panels are mounted to at least one of the inner diameter
structure and outer diameter structure.
13. The gas turbine engine of claim 10, wherein the plurality of
panels are heat shield panels.
14. The gas turbine engine of claim 10, wherein an air gap between
the trailing edge of the first panel and the leading edge of the
second panel forms at least a portion of a circumferential air gap
for the combustor.
15. The gas turbine engine of claim 10, wherein the trailing edge
of the first panel extends beyond the leading edge of the second
panel to provide an air flow gap between the first and second
panels and wherein portion of the first panel associated with the
leading edge is configured to prevent a gas path flow within the
combustor to enter the air flow gap.
16. The gas turbine engine of claim 10, wherein the first panel
extends over the second panel along the entire length of the first
panel by an amount within the range of 0.5 cm to 2 cm.
17. The gas turbine engine of claim 10, wherein the second panel
includes effusion holes positioned along the leading edge of the
second panel.
18. The gas turbine engine of claim 10, wherein leading edge of the
second panel is chamfered.
19. The gas turbine engine of claim 10, wherein leading edge of the
second panel includes one or more features to provide airflow when
the trailing edge of the first panel contacts the leading edge of
the second panel.
20. The gas turbine engine of claim 19, wherein the one or more
features include groves in the leading edge of the second panel to
provide said airflow.
Description
CROSS-REFERENCE TO RELATED APPLICATION
[0001] This application is related to the concurrently filed
application titled: COMBUSTOR PANELS AND CONFIGURATIONS FOR A GAS
TURBINE ENGINE filed on Mar. 30, 2015 and assigned patent
application Ser. No. ______, the disclosure of which is expressly
incorporated by reference.
FIELD
[0002] The present disclosure relates to combustors for gas turbine
engines and, in particular, to combustor configurations and
components for gas turbine engines.
BACKGROUND
[0003] Gas turbine engines are required to operate efficiently
during operation and flight. Theses engines create a tremendous
amount of force and generate high levels of heat. As such,
components of these engines are subjected to high levels of stress,
temperature and pressure. It is necessary to provide components
that can withstand the demands of a gas turbine engine. It is also
desirable to provide components with increased operating
longevity.
[0004] Conventional gas turbine engine combustors can include a
combustor shell. The conventional combustor shell and its typical
arrangement provide air flow to a combustor cavity. However, the
conventional arrangements may result in regions experiencing
distress due to the hot gas environment of the engine. Accordingly,
there is a desire to improve combustion cooling and provide a
configuration that allows for improved cooling characteristics.
There is also a desire to improve the configuration of gas turbine
engines and combustors.
BRIEF SUMMARY OF THE EMBODIMENTS
[0005] Disclosed and claimed herein are combustor configurations
and components for gas turbine engines. One embodiment is directed
to a combustor for a gas turbine engine, the combustor including a
support structure and a plurality of panels mounted to the
structure, the plurality of panels defining a combustion cavity of
the combustor. The plurality of panels include a first panel having
a leading and trailing edge and a second panel having a leading
edge and trailing edge, wherein a trailing edge of the first panel
extends beyond the leading edge of the second panel and wherein the
second panel is mounted to the support structure aft of the first
panel.
[0006] In one embodiment, the support structure is an annular
structure including an inner diameter structure and outer diameter
structure, and wherein the plurality of panels are mounted to at
least one of the inner diameter structure and outer diameter
structure.
[0007] In one embodiment, the plurality of panels are heat shield
panels.
[0008] In one embodiment, an air gap between the trailing edge of
the first panel and the leading edge of the second panel forms at
least a portion of a circumferential air gap for the combustor.
[0009] In one embodiment, the trailing edge of the first panel
extends beyond the leading edge of the second panel to provide an
air flow gap between the first and second panels and wherein
portion of the first panel associated with the leading edge is
configured to prevent a gas path flow within the combustor to enter
the air flow gap.
[0010] In one embodiment, the first panel extends over the second
panel along the entire length of the first panel by an amount
within the range of 0.5 cm to 2 cm.
[0011] In one embodiment, the second panel includes effusion holes
positioned along the leading edge of the second panel.
[0012] In one embodiment, the leading edge of the second panel is
chamfered.
[0013] In one embodiment, the leading edge of the second panel
includes one or more features to provide airflow when the trailing
edge of the first panel contacts the leading edge of the second
panel.
[0014] In one embodiment, the one or more features include groves
in the leading edge of the second panel to provide said
airflow.
[0015] Another embodiment is directed to a gas turbine engine
including a combustor having a support structure and a plurality of
panels mounted to the support structure. The plurality of panels
define a combustion cavity of the combustor. The plurality of
panels include a first panel having a leading and trailing edge,
and a second panel having a leading edge and trailing edge, wherein
a trailing edge of the first panel extends beyond the leading edge
of the second panel and wherein the second panel is mounted to the
support structure aft of the first panel.
[0016] In one embodiment, the support structure is an annular
structure including an inner diameter structure and outer diameter
structure, and wherein the plurality of panels are mounted to at
least one of the inner diameter structure and outer diameter
structure.
[0017] In one embodiment, the plurality of panels are heat shield
panels.
[0018] In one embodiment, an air gap between the trailing edge of
the first panel and the leading edge of the second panel forms at
least a portion of a circumferential air gap for the combustor.
[0019] In one embodiment, the trailing edge of the first panel
extends beyond the leading edge of the second panel to provide an
air flow gap between the first and second panels and wherein
portion of the first panel associated with the leading edge is
configured to prevent a gas path flow within the combustor to enter
the air flow gap.
[0020] In one embodiment, the first panel extends over the second
panel along the entire length of the first panel by an amount
within the range of 0.5 cm to 2 cm.
[0021] In one embodiment, the second panel includes effusion holes
positioned along the leading edge of the second panel.
[0022] In one embodiment, leading edge of the second panel is
chamfered.
[0023] In one embodiment, leading edge of the second panel includes
one or more features to provide airflow when the trailing edge of
the first panel contacts the leading edge of the second panel.
[0024] In one embodiment, the one or more features include groves
in the leading edge of the second panel to provide said
airflow.
[0025] Other aspects, features, and techniques will be apparent to
one skilled in the relevant art in view of the following detailed
description of the embodiments.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] The features, objects, and advantages of the present
disclosure will become more apparent from the detailed description
set forth below when taken in conjunction with the drawings in
which like reference characters identify correspondingly throughout
and wherein:
[0027] FIG. 1 depicts a graphical representation of a gas turbine
engine and combustor configuration according to one or more
embodiments;
[0028] FIGS. 2A-2B depict graphical representations of a panel
configuration according to one or more embodiments; and
[0029] FIGS. 3A-3C depict graphical representations of combustor
panels according to one or more embodiments.
DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS
Overview and Terminology
[0030] One aspect of this disclosure relates to configurations for
combustors according to one or more embodiments. In one embodiment,
a configuration is provided for a combustor to prevent hot air/gas
path egress to one or more air gaps of the combustor. According to
one embodiment, panels may be configured with an extended portion
to allow for the trailing edge of panels to extend over the leading
edge of adjacent and downstream panels. In addition, one or more
features may be provided to account for thermal growth of the panel
interface.
[0031] As used herein, the terms "a" or "an" shall mean one or more
than one. The term "plurality" shall mean two or more than two. The
term "another" is defined as a second or more. The terms
"including" and/or "having" are open ended (e.g., comprising). The
term "or" as used herein is to be interpreted as inclusive or
meaning any one or any combination. Therefore, "A, B or C" means
"any of the following: A; B; C; A and B; A and C; B and C; A, B and
C". An exception to this definition will occur only when a
combination of elements, functions, steps or acts are in some way
inherently mutually exclusive.
[0032] Reference throughout this document to "one embodiment,"
"certain embodiments," "an embodiment," or similar term means that
a particular feature, structure, or characteristic described in
connection with the embodiment is included in at least one
embodiment. Thus, the appearances of such phrases in various places
throughout this specification are not necessarily all referring to
the same embodiment. Furthermore, the particular features,
structures, or characteristics may be combined in any suitable
manner on one or more embodiments without limitation.
Exemplary Embodiments
[0033] FIG. 1 depicts a graphical representation of a gas turbine
engine and combustor configuration according to one or more
embodiments. FIG. 1 depicts a cross-sectional representation of a
gas turbine engine 100 including a combustor 105 according to one
or more embodiments. Combustor 105 includes a combustor structure
110 and a plurality of panel elements shown as 115. According to
one embodiment, combustor 105 employs combustor structure 110 to
support the plurality of panel elements 115. The plurality of panel
elements 115 may be heat shield panels to form the combustion
cavity 120 of combustor 105. Combustor 105 may be an annular
structure including outer diameter structure 112 and inner diameter
structure 113 of combustor 105. The plurality of panels 115 are
mounted to at least one of the inner diameter structure 113 and
outer diameter structure 112. Combustion cavity 120 of combustor
105 may be positioned between outer diameter structure 112 and
inner diameter structure 113. Combustor 105 may interface with fuel
injector 111.
[0034] According to one embodiment, combustor 105 may include one
or more air gaps between panels 115. Air gaps between panels 115
may be associated with outer diameter structure 112 and/or inner
diameter structure 113 of combustor 105. Exemplary regions for
including air gaps are shown as 124 and 125 associated with outer
diameter structure 112 and inner diameter structure 113,
respectively. According to one embodiment, panels 115 associated
with an air gap may include one or more features and
configurations. FIG. 1 depicts an exploded view of region 125
associated with inner diameter structure 113.
[0035] According to one embodiment, panels 115 may include a first
panel 126 and a second panel 127 mounted to structure 110. First
and second panels 126 and 127 have leading and trailing edges.
Second panel 127 is mounted to the support structure aft of the
first panel 126.
[0036] According to one embodiment, first panel 126 includes a
trailing edge portion 135 which extends over leading edge 140 of
second panel 127. The configuration of first panel 126 and a second
panel 127 provides an air gap between the panels and allows for
airflow 130 in the gap. Airflow 130 serves to both cool the
extended lip of a trailing edge portion 135 of the first panel 126
(e.g., the upstream panel) and also lay a cooling film down on
second panel 127 (e.g., the downstream panel). According to one
embodiment, leading edge 140 of second panel 127 is chamfered.
[0037] According to one embodiment, first panel 126 is upstream
(e.g., forward) from second panel 127. Similarly, second panel 127
is downstream (e.g., aft) of first panel 126. Although region 125
is shown and described as associated with inner diameter structure
113 it is equally appreciated that outer diameter 124 may include a
similar configuration of a forward panel including a portion that
overlaps an adjacent panel. It should also be appreciated that all
panels along the circumferential gas path opening may include an
overlapping configuration. As will be discussed in more detail
below and according to another embodiment, an overlapping
configuration may be employed to lateral portions (e.g., rails) of
panel elements 115.
[0038] FIGS. 2A-2B depict graphical representations of panel
configurations for a combustor according to one or more
embodiments. FIG. 2A depicts a graphical representation of a first
panel 205 (e.g., first panel 126) and a second panel 210 (e.g., a
second panel 127). First panel 205 includes trailing edge 215 which
extends over a leading edge 220 of second panel 210 by a distance
shown as 216. The first panel 205 extends over the second panel 210
along the entire length of the first panel by an amount within the
range of 0.5 cm to 2 cm.
[0039] The position of leading edge 220 is identified as 225 such
that the portion 230 that extends over the first panel 205 is
identified as 230. According to one embodiment, second panel 210
includes chamfered region 235, which is angled down to allow for
portion 230 to extend over chamfered region 235. An air gap between
the trailing edge of the first panel 205 and the leading edge of
the second panel 210 forms at least a portion of a circumferential
air gap for the combustor. The trailing edge 215 of the first panel
205 extends beyond the leading edge 220 of the second panel 210 to
provide an air flow gap between the first and second panels and
wherein portion 230 of the first panel 205 associated with the
leading edge is configured to prevent a gas path flow within the
combustor to enter the air flow gap.
[0040] FIG. 2B depicts an exploded view of first panel 205 (e.g.,
upstream panel) and a second panel 210 (e.g., downstream panel).
According to one embodiment, second panel 210 includes one or more
features 240 in chamfered region 235. Features 240 may provide air
flow paths when the trailing edge of the first panel 205 contacts
the leading edge of the second panel 210. According to one
embodiment, features 240 are grooves or indentations which may be
perpendicular or substantially perpendicular to the leading edge
220 of second panel 210. In certain embodiments, features 240 may
be ridges or raised portions which may be perpendicular or
substantially perpendicular to the leading edge 220 of second panel
210. Features 240 may include effusion holes positioned along the
leading edge of the second panel 210.
[0041] FIGS. 3A-3C depict graphical representations of combustor
panels according to one or more embodiments. FIG. 3A depicts
combustor configuration 300 including panels 305 and 310. The hot
side (e.g., side facing combustor cavity 120) of first panel 305
and 310 are shown. In FIG. 3A, combustor configuration 300 include
a first panel 305 and a second panel 310 mounted to structure 110.
First and second panels 305 and 310 have leading and trailing
edges, such that leading edge 315 of panel 305 extends over panel
310. Leading edge of panel 310 is represented by segment 320.
Trailing edge of second panel 310 is shown as 325. According to one
embodiment, lateral or rail portions of panels 305 and 310 may
include one or more features to provide lateral sealing between
panels. Lateral portions 330 and 335 of first panel 305 may relate
to overhanging or chamfered regions to interface with lateral
portions of another panel, such as panel 350. Panel 350 includes
lateral regions 355 and 360. According to one embodiment, lateral
portion 335 of panel 305 may interface with lateral portion 355 of
panel 350. By way of example, FIG. 3B depicts an exemplary
configuration 365 of panels 305 and 350. Lateral portion 335 may
overhang panel 310 and lateral portion 355 may be chamfered. Panel
305 includes base structure 366 to mount to support structure.
Similarly, panel 350 includes base structure 367 to mount to
support structure.
[0042] FIG. 3C depicts a representation of an inner diameter 371 of
an annular structure 370, such as a combustor inner diameter
structure including panels 305 and 350.
[0043] While this disclosure has been particularly shown and
described with references to exemplary embodiments thereof, it will
be understood by those skilled in the art that various changes in
form and details may be made therein without departing from the
scope of the claimed embodiments.
* * * * *