U.S. patent application number 13/441031 was filed with the patent office on 2013-10-10 for engine hot section vane with tapered flame holder surface.
This patent application is currently assigned to UNITED TECHNOLOGIES CORPORATION. The applicant listed for this patent is Torence P. Brogan, Meredith B. Colket, III, Christopher A. Eckett, Donald J. Hautman, Jeffery A. Lovett. Invention is credited to Torence P. Brogan, Meredith B. Colket, III, Christopher A. Eckett, Donald J. Hautman, Jeffery A. Lovett.
Application Number | 20130263572 13/441031 |
Document ID | / |
Family ID | 49122190 |
Filed Date | 2013-10-10 |
United States Patent
Application |
20130263572 |
Kind Code |
A1 |
Lovett; Jeffery A. ; et
al. |
October 10, 2013 |
ENGINE HOT SECTION VANE WITH TAPERED FLAME HOLDER SURFACE
Abstract
A gas turbine or rocket engine hot section includes a first duct
case, a second duct case, a plurality of vanes arranged about an
axial centerline, and an igniter located with a first of the
plurality of vanes. The first of the plurality of vanes extends
axially between a leading edge and a flame holder surface at a
trailing edge. The flame holder surface extends radially between a
first vane end connected to the first duct case and a second vane
end connected to the second duct case. The flame holder surface
includes a first section that tapers towards the first vane end,
and a second section that tapers away from the first section and
towards the second vane end.
Inventors: |
Lovett; Jeffery A.;
(Tolland, CT) ; Hautman; Donald J.; (Marlborough,
CT) ; Brogan; Torence P.; (Manchester, CT) ;
Eckett; Christopher A.; (New Britain, CT) ; Colket,
III; Meredith B.; (Simsbury, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Lovett; Jeffery A.
Hautman; Donald J.
Brogan; Torence P.
Eckett; Christopher A.
Colket, III; Meredith B. |
Tolland
Marlborough
Manchester
New Britain
Simsbury |
CT
CT
CT
CT
CT |
US
US
US
US
US |
|
|
Assignee: |
UNITED TECHNOLOGIES
CORPORATION
Hartford
CT
|
Family ID: |
49122190 |
Appl. No.: |
13/441031 |
Filed: |
April 6, 2012 |
Current U.S.
Class: |
60/39.821 |
Current CPC
Class: |
F02K 3/10 20130101 |
Class at
Publication: |
60/39.821 |
International
Class: |
F02C 7/264 20060101
F02C007/264 |
Goverment Interests
[0001] This invention was made with government support under
Contract No. N00019-02-C-3003 awarded by the United States Navy.
The government may have certain rights in the invention.
Claims
1. An engine hot section, comprising: a plurality of vanes arranged
about an axial centerline, a first of the plurality of vanes
extends axially between a leading edge and a flame holder surface
at a trailing edge, the flame holder surface extends radially
between a first vane end connected to a first duct case and a
second vane end connected to a second duct case with a first
section that tapers towards the first vane end and a second section
that tapers away from the first section and towards the second vane
end.
2. The engine hot section of claim 1, wherein the first section
comprises a first length that radially extends between a first
section inner end and a first section outer end, the second section
comprises a second length that radially extends between a second
section inner end and a second section outer end, and the first
length is substantially equal to the second length.
3. The engine hot section of claim 1, wherein the first section
comprises a first length that radially extends between a first
section inner end and a first section outer end, the second section
comprises a second length that radially extends between a second
section inner end and a second section outer end, and the first
length is greater than the second length.
4. The engine hot section of claim 1, wherein the first section
comprises a first length that radially extends between a first
section inner end and a first section outer end, the second section
comprises a second length that radially extends between a second
section inner end and a second section outer end, and the first
length is less than the second length.
5. An engine hot section, comprising: a plurality of vanes arranged
about an axial centerline, a first of the plurality of vanes
extending axially between a leading edge and a flame holder surface
at a trailing edge, the flame holder surface that extends radially
between a first vane end connected to a first duct case and a
second vane end connected to a second duct case with a first
section that tapers towards the first vane end and a second section
that tapers away from the first section and towards the second vane
end, the flame holder surface further includes a third section that
extends radially between the first section and the second section
and circumferentially between a first vane side and a second vane
side, the third section with a substantially uniform
circumferential width; and an igniter located adjacent to the first
of the plurality of vanes.
6. An engine hot section, comprising: a plurality of vanes arranged
about an axial centerline, a first of the plurality of vanes that
extends axially between a leading edge and a flame holder surface
at a trailing edge, the flame holder surface that extends radially
between a first vane end connected to a first duct case and a
second vane end connected to a second duct case, the flame holder
surface includes a first section that tapers towards the first vane
end and a second section that tapers away from the first section
and towards the second vane end; and an igniter located adjacent to
first of the plurality of vanes, the first of the plurality of
vanes extends circumferentially between a first vane side and a
second vane side, and the first vane side and the second vane side
each taper from the second vane end to the first vane end.
7. The engine hot section of claim 1, wherein the first duct case
comprises a radial inner duct case, and the second duct case
comprises a radial outer duct case.
8. The engine hot section of claim 1, wherein the first duct case
comprises a radial outer duct case, and the second duct case
comprises a radial inner duct case.
9. The engine hot section of claim 21, wherein the igniter
comprises a pilot flame tube located at the first vane end.
10. The engine hot section of claim 9, wherein the pilot flame tube
is connected to the first duct case.
11. A gas turbine engine, comprising: a compressor section; a
turbine section downstream of the compressor section; an engine hot
section downstream of the turbine section, the engine hot section
includes a vane that extends axially between a leading edge and a
flame holder surface at a trailing edge, the flame holder surface
extends radially between a first vane end connected to a first duct
case and a second vane end connected to a second duct case with a
first section that tapers towards the first vane end and a second
section that tapers away from the first section and towards the
second vane end; and an igniter located adjacent to the vane.
12. The engine of claim 11, further comprising a combustor section,
wherein the engine hot section comprises an augmentor section, and
wherein the compressor section, the combustor section, the turbine
section and the augmentor section are arranged sequentially along
an axial centerline.
13. The engine of claim 11, wherein the first section comprises a
first length that radially extends between a first section inner
end and a first section outer end, the second section comprises a
second length that radially extends between a second section inner
end and a second section outer end, and the first length is
substantially equal to the second length.
14. The engine of claim 11, wherein the first section comprises a
first length that radially extends between a first section inner
end and a first section outer end, the second section comprises a
second length that radially extends between a second section inner
end and a second section outer end, and the first length is greater
than the second length.
15. The engine of claim 11, wherein the first section comprises a
first length that radially extends between a first section inner
end and a first section outer end, the second section comprises a
second length that radially extends between a second section inner
end and a second section outer end, and the first length is less
than the second length.
16. A gas turbine engine, comprising: a compressor section; a
turbine section downstream of the compressor section; and an engine
hot section downstream of said turbine section, the engine hot
section includes a vane that extends axially between a leading edge
and a flame holder surface at a trailing edge, the flame holder
surface extends radially between a first vane end connected to a
first duct case and a second vane end connected to a second duct
case, the flame holder surface further includes a first section
that tapers towards the first vane end and a second section that
tapers away from the first section and towards the second vane end
and a third section extending radially between the first section
and the second section and circumferentially between a first vane
side and a second vane side, the third section includes a
substantially uniform circumferential width; and an igniter located
adjacent to the vane.
17. A gas turbine engine, comprising: a compressor section; a
turbine section downstream of the compressor section; and an engine
hot section downstream of said turbine section, the engine hot
section includes a vane that extends axially between a leading edge
and a flame holder surface at a trailing edge, the flame holder
surface extends radially between a first vane end connected to a
first duct case and a second vane end connected to a second duct
case, the flame holder surface further includes a first section
that tapers towards the first vane end and a second section that
tapers away from the first section and towards the second vane end,
the vane extends circumferentially between a first vane side and a
second vane side, the first vane side and the second vane side each
taper from the second vane end to the first vane end; and an
igniter located adjacent to the vane.
18. The engine of claim 11, wherein the first duct case comprises a
radial inner duct case, and the second duct case comprises a radial
outer duct case.
19. The engine of claim 11, wherein the igniter comprises a pilot
flame tube located at the first vane end.
20. The engine of claim 19, wherein the pilot flame tube is
connected to the first duct case.
21. The engine hot section of claim 1, further comprising an
igniter located adjacent to the first of the plurality of
vanes.
22. The engine hot section of claim 1, wherein the first section
tapers circumferentially inward between a first vane side and a
second vane side towards the first vane end and a second section
that tapers circumferentially inward between the first vane side
and the second vane side away from the first section and towards
the second vane end.
23. The engine of claim 11, wherein the first section tapers
circumferentially inward between a first vane side and a second
vane side towards the first vane end and a second section that
tapers circumferentially inward between the first vane side and the
second vane side away from the first section and towards the second
vane end.
Description
BACKGROUND OF THE INVENTION
[0002] 1. Technical Field
[0003] The present invention relates generally to gas turbine and
rocket engines and, in particular, to a hot section that includes a
vane with a flame holder surface.
[0004] 2. Background Information
[0005] Gas turbine and/or rocket engines may include one or more
engine hot sections such as, for example, a combustor section and
an augmentor (afterburner) section. Such hot sections are typically
configured to (i) inject fuel into a core gas flowing through the
section and (ii) ignite the injected fuel with a flame to generate
thrust.
[0006] One type of gas turbine engine hot section includes a
plurality of bluff body flame holders. Each flame holder may
include a flame holder vane. The flame holder extends radially
between an inner duct case and an outer duct case, and extends
axially from a leading edge to a flame holder surface at a trailing
edge. The flame holder surface is typically configured with a
constant circumferential surface width. The surface width may be
sized to maintain a flame that extends radially between the inner
duct case and the outer duct case adjacent to the flame holder
surface. Typically, the surface width is oversized in order to
increase flame stability. Over sizing the surface width, however,
may also increase the surface area of the flame holder surface and
thereby the weight of the flame holder vane. There is a need in the
art, therefore, for a hot section vane configuration that may
increase flame stability while also decreasing vane surface width
and vane weight.
SUMMARY OF THE DISCLOSURE
[0007] According to a first aspect of the invention, an engine hot
section includes a first duct case, a second duct case, a plurality
of vanes arranged about an axial centerline, and an igniter located
with a first of the plurality of vanes. The first of the plurality
of vanes extends axially between a leading edge and a flame holder
surface at a trailing edge. The flame holder surface extends
radially between a first vane end connected to the first duct case
and a second vane end connected to the second duct case. The flame
holder surface includes a first section that tapers towards the
first vane end, and a second section that tapers away from the
first section and towards the second vane end.
[0008] In an embodiment, the first section includes a first length
that radially extends between a first section inner end and a first
section outer end. The second section includes a second length that
radially extends between a second section inner end and a second
section outer end. In an embodiment, the first length is
substantially equal to the second length. In another embodiment,
the first length is greater than the second length. In still
another embodiment, the first length is less than the second
length.
[0009] In an embodiment, the flame holder surface also includes a
third section with a substantially uniform circumferential width.
The third section extends radially between the first section and
the second section and circumferentially between a first vane side
and a second vane side.
[0010] In an embodiment, the first of the vanes extends
circumferentially between a first vane side and a second vane side.
The first vane side and the second vane side each taper from the
second vane end to the first vane end.
[0011] In an embodiment, the first duct case includes a radial
inner duct case, and the second duct case includes a radial outer
duct case. In another embodiment, the first duct case includes a
radial outer duct case, and the second duct case includes a radial
inner duct case.
[0012] In an embodiment, the igniter includes a pilot flame tube
located at the first vane end. In an embodiment, the pilot flame
tube is connected to the first duct case.
[0013] According to a second aspect of the invention, a gas turbine
engine includes a compressor section, a turbine section and an
engine hot section that includes a first duct case, a second duct
case and an igniter located with a vane. The vane extends axially
between a leading edge and a flame holder surface at a trailing
edge. The flame holder surface extends radially between a first
vane end connected to the first duct case and a second vane end
connected to the second duct case. The flame holder surface
includes a first section that tapers towards the first vane end,
and a second section that tapers away from the first section and
towards the second vane end.
[0014] In an embodiment, the gas turbine engine also includes a
combustor section, and the engine hot section includes an augmentor
section. The compressor section, the combustor section, the turbine
section and the augmentor section are arranged sequentially along
an axial centerline.
[0015] The foregoing features and the operation of the invention
will become more apparent in light of the following description and
the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0016] FIG. 1 is a side-sectional illustration of a gas turbine
engine;
[0017] FIG. 2 is a cross-sectional illustration of a gas turbine
engine hot section;
[0018] FIG. 3 is a side view illustration of a hot section
vane;
[0019] FIG. 4 is an end view illustration of the hot section vane
illustrated in FIG. 3;
[0020] FIG. 5 is an end view illustration of an alternate hot
section vane;
[0021] FIG. 6 is an end view illustration of another alternate hot
section vane;
[0022] FIG. 7 is an end view illustration of yet another alternate
hot section vane;
[0023] FIG. 8 is a side view illustration of still yet another hot
section vane; and
[0024] FIG. 9 is an enlarged cross-sectional illustration of a
trailing edge portion of the hot section vane illustrated in FIG.
8.
DETAILED DESCRIPTION OF THE INVENTION
[0025] FIG. 1 is a side-sectional illustration of a 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.
[0026] Referring to FIG. 2, the second engine hot section 18
includes a first (e.g., annular, radial inner) duct case 26, a
second (e.g., annular, radial outer) duct case 28, one or more hot
section vanes 30, and one or more igniters 32 (e.g., pilot flame
tubes and/or spark plugs). The second engine hot section 18 may
also include an augmentor fuel delivery system with one or more
augmentor spray bars, which is not shown in order to simplify the
drawings. Examples of such an augmentor fuel delivery system,
however, are disclosed in U.S. Pat. Nos. 7,578,131, 7,647,775 and
7,712,315, which are hereby incorporated by reference in their
entirety, and which are assigned to the assignee of the present
invention.
[0027] Referring to FIG. 3, each of the vanes 30 may include a vane
airfoil 34 and a trailing edge box 36, which may be configured to
house a respective one of the augmentor spray bars. Each of the
vanes 30 extends axially between a vane leading edge 38 and a vane
trailing edge 40. Each of the vanes 30 extends radially between a
first (e.g., radial inner) vane end 42 and a second (e.g., radial
outer) vane end 44. Referring to FIG. 4, each of the vanes 30 also
extends circumferentially between a first vane (e.g., pressure)
side 46 and a second vane (e.g., suction) side 48. Referring again
to FIG. 3, the first vane side 46 and the second vane side 48 may
each have an axial width 50 that decreases as the respective vane
side extends radially from the second vane end 44 to the first vane
end 42; e.g., the first and second vane sides 46 and 48 taper from
the second vane end 44 to the first vane end 42.
[0028] One or more of the vanes 30 also includes a (e.g., planar)
flame holder surface 52 located at a respective vane trailing edge
40. Referring to FIG. 4, the flame holder surface 52 may extend
radially from the first vane end 42 to the second vane end 44. The
flame holder surface 52 may also extend circumferentially between
the first vane side 46 and the second vane side 48.
[0029] Referring to FIGS. 4-7, the flame holder surface 52 may have
a plurality of (e.g., planar) flame holder surface sections
including, for example, a tapered first (e.g., radial inner)
section 54 and a tapered second (e.g., radial outer) section 56.
The first section 54 may circumferentially taper as the section
extends radially towards the first vane end 42. The second section
56 may circumferentially taper as the section extends radially away
from the first section 54, and towards the second vane end 44.
Referring to FIGS. 4-6, the flame holder surface 52 may also
include a (e.g., non-tapered) third section 58 that, for example,
extends radially between the first section 54 and the second
section 56.
[0030] Referring to the flame holder surface 52 illustrated in FIG.
5, the first section 54 has a first length 60 that extends radially
between a first section inner end 62 and a first section outer end
64. The first section 54 also has a first width 66 that extends
circumferentially between the first vane side 46 and the second
vane side 48. The first width 66 increases as the first section 54
extends radially from the first section inner end 62 to the first
section outer end 64. The second section 56 has a second length 68
that extends radially between a second section inner end 70 and a
second section outer end 72. The second section 56 also has a
second width 74 that extends circumferentially between the first
vane side 46 and the second vane side 48. The second width 74
decreases as the second section 56 extends radially from the second
section inner end 70 to the second section outer end 72. The third
section 58 has a third length 76 that extends radially between the
first section outer end 64 and the second section inner end 70. The
third section 58 also has a (e.g., substantially uniform) third
width 78 that extends between the first vane side 46 and the second
vane side 48.
[0031] The aforesaid lengths and/or widths of the flame holder
surface sections (e.g., 54, 56 and/or 58) may be sized to reduce
weight and radar signature of the vanes 30. The first width 66, the
second width 74 and/or the third length 76, for example, may be
sized such that the flame holder surface 52 has a relatively small
surface area, which may reduce vane 30 weight and radar signature.
The lengths and/or widths of the flame holder surface sections
(e.g., 54, 56 and/or 58) may also be sized to increase flame
stability in the second engine hot section 18, which is described
below in further detail.
[0032] Referring to FIG. 2, the vanes 30 and the igniters 32 are
respectively arranged circumferentially around the axial centerline
20. Referring to FIGS. 3 and 4, each first vane end 42 is connected
to the first duct case 26, and each second vane end 44 is connected
to the second duct case 28. Each of the igniters 32 may be
respectively located at the first vane end 42 and connected to the
first duct case 26.
[0033] During operation of the engine hot section 80 illustrated in
FIGS. 8 and 9, a radially elongated low pressure and velocity
region 82 may be formed adjacent to the flame holder surface 52
between the first duct case 26 and the second duct case 28 as a
core gas 84 is directed around each respective vane 30. Fuel may be
injected into the core gas 84 by one or more augmentor spray bar
fuel injectors 86 arranged with the respective vane 30. A first
portion of the fuel 87 may enter the low pressure region 82
adjacent the flame holder surface 52, and may be ignited by a pilot
flame or a spark provided by the respective igniter 32. At least a
portion of the ignited fuel 87 may re-circulate within the low
pressure region 82 along the flame holder surface 52 between the
first vane end 42 and the second vane end 44. The re-circulating
ignited fuel 87 within the low pressure region 82 may form a
substantially stable flame 90 adjacent to the vane trailing edge
40. The flame 90 may be utilized for igniting, for example, a
second (e.g., larger) portion of the fuel 89 injected into the core
gas 84 by the fuel injectors 86.
[0034] The low pressure region 82 may have a radial pressure
gradient that changes radially along the flame holder surface 52
and therefore may affect the stability of the flame 90. The
pressure gradient may be created by, for example, the angling the
flame holder surface 50 in the radial plane and/or the aerodynamics
of the flow passage. The pressure gradient may include, for
example, a low pressure zone 92 that is located radially between a
plurality of high pressure zones 94 and 96. The low pressure zone
92 is formed by the core gas 84 passing the relatively wide third
section 58, and the high pressure zones 94 and 96 are respectively
formed by the core gas 84 passing the tapered first section 54 and
the tapered second section 56.
[0035] The radial location of the low pressure zone 92 along the
flame holder surface 52 is defined by the radial location of the
third section 58. The magnitude of the pressure differential
between the low pressure zone 92 and the high pressure zones 94 and
96 is defined by the size differential between the third width 78
and the tapering first and second widths 66 and 74 (see FIG. 5).
The lengths and/or widths of the flame holder surface sections
(e.g., 54, 56 and/or 58) therefore may be sized to tailor the
pressure gradient and thus flow dynamics of the flame 90. The
length and/or width of the third section may be increased, for
example, to decrease pressure in the low pressure zone 92 and
thereby increase the flame 90 stability within the second engine
hot section 18.
[0036] In the some embodiments, for example as illustrated in FIGS.
5 and 7, the second length 68 may be sized less than the first
length 60. In other embodiments, for example as illustrated in FIG.
6, the second length 68 may be sized greater than the first length
60. In still other embodiments, for example as illustrated in FIG.
4, the second length 68 may be sized substantially equal to the
first length 60.
[0037] In some embodiments, for example as illustrated in FIG. 5,
the third length 76 may be sized less than the first length 60
and/or the second length 68. In other embodiments, for example as
illustrated in FIG. 6, the third length 76 may be sized greater
than the first length 60 and/or the second length 68. In still
other embodiments, for example as illustrated in FIG. 4, the third
length 76 may be sized substantially equal to the second length 68
and/or the third length 76.
[0038] A person of ordinary skill in the art will recognize that
the tapered sections of the flame holder surface 52 may have
various alternative geometries to those illustrated in the
drawings. In some embodiments, for example, one or more of the
tapered sections may include a plurality of tapered subsections
that taper according to different slopes. In other embodiments, one
or more of the tapered sections may have curved tapered
geometries.
[0039] In an alternate embodiment, each of the igniters may be
respectively located at the second vane end and connected to the
second duct case.
[0040] The hot section vanes 30 are described above as being
included in an augmentor section of a gas turbine engine. A person
of ordinary skill in the art, however, will recognize that the
disclosed vanes may be included in various other gas turbine engine
hot sections and/or various other engine configurations that
utilize, for example, bluff body flame holders. In some
embodiments, for example, the disclosed vanes may be included in a
combustor section of a gas turbine engine. In other embodiments,
the disclosed vanes may be included in a combustor section of a
rocket engine. In still other embodiments, the flame holders may be
oriented circumferentially.
[0041] While various embodiments of the present invention have been
disclosed, it will be apparent to those of ordinary skill in the
art that many more embodiments and implementations are possible
within the scope of the invention. Accordingly, the present
invention is not to be restricted except in light of the attached
claims and their equivalents.
* * * * *