U.S. patent application number 17/166477 was filed with the patent office on 2022-08-04 for systems and methods for spraying fuel in an augmented gas turbine engine.
The applicant listed for this patent is General Electric Company. Invention is credited to Michael A. Benjamin, Aaron J. Glaser, Nicholas R. Overman, Brett A. Rich.
Application Number | 20220243915 17/166477 |
Document ID | / |
Family ID | 1000005388444 |
Filed Date | 2022-08-04 |
United States Patent
Application |
20220243915 |
Kind Code |
A1 |
Rich; Brett A. ; et
al. |
August 4, 2022 |
SYSTEMS AND METHODS FOR SPRAYING FUEL IN AN AUGMENTED GAS TURBINE
ENGINE
Abstract
In some embodiments, systems, apparatuses and methods are
provided herein useful for spraying fuel in an augmented gas
turbine engine. The embodiments may include a spray bar with a fuel
injection aperture to inject a fuel jet into a fuel conduit; the
fuel conduit having a fuel window to discharge the fuel jet into a
core exhaust flow of an augmented gas turbine engine; a first
airflow conduit having a first orifice to discharge a first air
stream into the core exhaust flow; and a second airflow conduit
having a second orifice to discharge a second air stream into the
core exhaust flow. The first orifice and the second orifice may be
paired with the fuel window to cooperatively shape the fuel jet
coming out of the fuel window.
Inventors: |
Rich; Brett A.; (Edgewood,
KY) ; Benjamin; Michael A.; (Cincinnati, OH) ;
Overman; Nicholas R.; (Sharonville, OH) ; Glaser;
Aaron J.; (Cincinnati, OH) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
1000005388444 |
Appl. No.: |
17/166477 |
Filed: |
February 3, 2021 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F02K 3/10 20130101; F23R
3/20 20130101; F23R 3/28 20130101 |
International
Class: |
F23R 3/20 20060101
F23R003/20; F23R 3/28 20060101 F23R003/28 |
Claims
1. A fuel spray apparatus for spraying fuel in an augmented gas
turbine engine comprising: a spray bar with a fuel injection
aperture to inject a fuel jet into a fuel conduit; the fuel conduit
having a fuel window to discharge the fuel jet into a core exhaust
flow of an augmented gas turbine engine; a first airflow conduit
having a first orifice to discharge a first air stream into the
core exhaust flow; and a second airflow conduit having a second
orifice to discharge a second air stream into the core exhaust
flow, wherein the first orifice and the second orifice are paired
with the fuel window to cooperatively shape the fuel jet coming out
of the fuel window.
2. The fuel spray apparatus of claim 1, further comprising: a
second spray bar with a second fuel injection aperture to inject a
second fuel jet into a second fuel conduit; the second fuel conduit
having a second fuel window to discharge the second fuel jet into
the core exhaust flow; a third airflow conduit having a third
orifice to discharge a third air stream into the core exhaust flow;
and a fourth airflow conduit having a fourth orifice to discharge a
fourth air stream into the core exhaust flow, wherein the third
orifice and the fourth orifice are paired with the second fuel
window to cooperatively shape the second fuel jet coming out of the
second fuel window, wherein the first orifice is a first distance
relative to the fuel window and the second orifice is a second
distance relative to the fuel window, and wherein the third orifice
is a third distance relative to the second fuel window and the
second orifice is a fourth distance relative to the second fuel
window.
3. The fuel spray apparatus of claim 1, wherein the first airflow
conduit splits into a first subchannel and a second subchannel, and
wherein the first orifice is located at a terminal end of the first
subchannel and the second subchannel terminates at a first opening
into the fuel conduit.
4. The fuel spray apparatus of claim 3, wherein the second airflow
conduit splits into a third subchannel and a fourth subchannel,
wherein the second orifice is located at a terminal end of the
third subchannel and the fourth subchannel terminates at a second
opening into the fuel conduit.
5. The fuel spray apparatus of claim 4, wherein the first opening
into the fuel conduit is positioned substantially horizontally
across the second opening into the fuel conduit.
6. The fuel spray apparatus of claim 1, wherein a first centerline
of the first airflow conduit is at a first angle relative to a
second centerline of the fuel conduit, and wherein a third
centerline of the second airflow conduit is at a second angle
relative to the second centerline of the fuel conduit.
7. The fuel spray apparatus of claim 1, further comprising: a main
airflow conduit to direct air into the first airflow conduit and
the second airflow conduit; and a heat shield wall at least
partially surrounding the spray bar proximate the fuel injection
aperture, wherein the air is directed to flow into a gap between
the heat shield wall and the spray bar to cooperatively impinge the
fuel jet into the shape as the fuel jet comes out of the fuel
window and form an air curtain to shield the fuel jet from the core
exhaust flow.
8. The fuel spray apparatus of claim 1, wherein at least one of a
first shape of the first orifice and a second shape of the second
orifice comprises a circular shape.
9. The fuel spray apparatus of claim 1, wherein the fuel window is
approximately equidistant from both the first orifice and the
second orifice.
10. The fuel spray apparatus of claim 1, wherein the first orifice
is positioned substantially across the second orifice relative to
the fuel window.
11. The fuel spray apparatus of claim 1, wherein the first airflow
conduit and the second airflow conduit are configured to receive at
least one of bypass air and bleed air of the augmented gas turbine
engine.
12. A system for spraying fuel in an augmented gas turbine engine,
the system comprising: a gas turbine engine having an augmentor
portion for burning fuel; and at least one fuel spray bar for
spraying fuel within the augmentor portion, the at least one fuel
spray bar comprising: a first spray bar with a fuel injection
aperture to inject a first fuel jet into a first fuel conduit; the
first fuel conduit having a first fuel window to discharge the
first fuel jet into a core exhaust flow of the augmentor portion; a
first airflow conduit having a first orifice to discharge a first
air stream into the core exhaust flow; and a second airflow conduit
having a second orifice to discharge a second air stream into the
core exhaust flow, wherein the first orifice and the second orifice
are paired with the first fuel window to cooperatively shape the
first fuel jet coming out of the first fuel window.
13. The system of claim 12, wherein the at least one fuel spray bar
further comprises: a second spray bar with a second fuel injection
aperture to inject a second fuel jet into a second fuel conduit;
the second fuel conduit having a second fuel window to discharge
the second fuel jet into the core exhaust flow; a third airflow
conduit having a third orifice to discharge a third air stream into
the core exhaust flow; and a fourth airflow conduit having a fourth
orifice to discharge a fourth air stream into the core exhaust
flow, wherein the third orifice and the fourth orifice are paired
with the second fuel window to cooperatively shape the second fuel
jet coming out of the second fuel window, wherein the first orifice
is a first distance relative to the first fuel window and the
second orifice is a second distance relative to the first fuel
window, and wherein the third orifice is a third distance relative
to the second fuel window and the fourth second orifice is a fourth
distance relative to the second fuel window.
14. The system of claim 13, wherein the third orifice is adjacent
to the second orifice, the second orifice configured to discharge
the second air stream at a first angular range and the third
orifice configured to discharge the third air stream at a second
angular range different from the first angular range.
15. The system of claim 13, wherein the third orifice is adjacent
to the second orifice, and wherein a first shape of the second
orifice is distinct from a second shape of the third orifice.
16. The system of claim 12, wherein the first orifice is located on
an upstream side of the first fuel window relative to the core
exhaust flow, and wherein the second orifice is located on a
downstream side of the first fuel window relative to the core
exhaust flow.
17. A method for spraying fuel in an augmented gas turbine engine
comprising: directing a fuel jet into a core exhaust flow of an
augmented gas turbine engine via a fuel window of a fuel conduit
configured to receive the fuel jet from a fuel injection aperture
of a spray bar; directing a first air stream into the core exhaust
flow via a first orifice of a first airflow conduit; and directing
a second air stream into the core exhaust flow via a second orifice
of a second airflow conduit, wherein the first air stream and the
second air stream cooperatively impinge the fuel jet into a shape
as the fuel jet comes out of the fuel window, wherein the first
orifice and the second orifice are paired with the fuel window
causing the first air stream and the second air stream to
cooperatively impinge the fuel jet into the shape.
18. The method of claim 17, further comprising directing a third
air stream via a subchannel of the first airflow conduit through a
first opening into the fuel conduit to impinge on the fuel jet as
the fuel jet comes out of the fuel injection aperture.
19. The method of claim 18, further comprising directing a fourth
air stream via a subchannel of the second airflow conduit through a
second opening into the fuel conduit to additionally impinge on the
fuel jet as the fuel jet comes out of the fuel injection
aperture.
20. The method of claim 17, further comprising directing at least
one of bypass air and bleed air of the augmented gas turbine engine
into the first airflow conduit and the second airflow conduit.
Description
TECHNICAL FIELD
[0001] The technology relates generally to spraying fuel in an
augmented gas turbine engine.
BACKGROUND
[0002] Generally, augmentor fueling schemes depend on spray bar and
fuel system design to achieve both core flow path fuel penetration
and dispersion. Generating the required fuel zones to meet
objectives for performance is in part a function of what fuel
pressure ratio can be set and proximity of spray bars to another.
Realizing these goals can affect the weight of the engine by sizing
of the fuel pump and spray bar count.
BRIEF DESCRIPTION
[0003] Aspects and advantages of the present disclosure will be set
forth in part in the following description, or may be obvious from
the description, or may be learned through practice of the present
disclosure.
[0004] In an aspect of the present disclosure, a fuel spray
apparatus for spraying fuel in an augmented gas turbine engine
includes a spray bar with a fuel injection aperture to inject a
fuel jet into a fuel conduit; the fuel conduit having a fuel window
to discharge the fuel jet into a core exhaust flow of an augmented
gas turbine engine; a first airflow conduit having a first orifice
to discharge a first air stream into the core exhaust flow; and a
second airflow conduit having a second orifice to discharge a
second air stream into the core exhaust flow, where the first
orifice and the second orifice are paired with the fuel window to
cooperatively shape the fuel jet coming out of the fuel window.
[0005] In another aspect of the present disclosure, a system for
spraying fuel in an augmented gas turbine engine includes a gas
turbine engine having an augmentor portion for burning fuel; and at
least one fuel spray bar for spraying fuel within the augmentor
portion. In some embodiments, the at least one fuel spray bar
includes a first spray bar with a fuel injection aperture to inject
a first fuel jet into a first fuel conduit; the first fuel conduit
having a first fuel window to discharge the first fuel jet into a
core exhaust flow of the augmentor portion; a first airflow conduit
having a first orifice to discharge a first air stream into the
core exhaust flow; and a second airflow conduit having a second
orifice to discharge a second air stream into the core exhaust
flow, wherein the first orifice and the second orifice are paired
with the first fuel window to cooperatively shape the first fuel
jet coming out of the first fuel window.
[0006] In another aspect of the present disclosure, a method for
spraying fuel in an augmented gas turbine engine includes directing
a fuel jet into a core exhaust flow of an augmented gas turbine
engine via a fuel window of a fuel conduit configured to receive
the fuel jet from a fuel injection aperture of a spray bar;
directing a first air stream into the core exhaust flow via a first
orifice of a first airflow conduit; and directing a second air
stream into the core exhaust flow via a second orifice of a second
airflow conduit, wherein the first air stream and the second air
stream cooperatively impinge the fuel jet into a shape as the fuel
jet comes out of the fuel window.
[0007] These and other features, aspects and advantages of the
present disclosure and/or embodiments will become better understood
with reference to the following description and appended claims.
The accompanying drawings, which are incorporated in and constitute
a part of this specification illustrate embodiments of the present
disclosure and, together with the description, serve to explain the
principles of the present disclosure.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] Disclosed herein are embodiments of systems, apparatuses and
methods pertaining to spraying fuel in an augmented gas turbine
engine. This description includes drawings, wherein:
[0009] FIG. 1 is a partial cross-sectional illustration of an
exemplary augmented gas turbine engine showing exemplary fuel spray
apparatuses for spraying fuel in accordance with some
embodiments;
[0010] FIG. 2 is a simplified illustration of an exemplary fuel
spray apparatus in accordance with some embodiments;
[0011] FIG. 3 is a perspective view of an exemplary fuel spray
apparatus in accordance with some embodiments;
[0012] FIG. 4 is a cross-sectional view of the exemplary fuel spray
apparatus of FIG. 3 taken along line A-A of FIG. 3 in accordance
with some embodiments;
[0013] FIG. 5 is a cross-sectional view of an exemplary paired fuel
window-air orifices of the exemplary fuel spray apparatus of FIG. 3
as taken along line B-B of FIG. 3 in accordance with some
embodiments;
[0014] FIG. 6 is a cross-sectional view of an exemplary paired fuel
window-air orifices of an exemplary fuel spray apparatus in
accordance with some embodiments;
[0015] FIG. 7 is a cross-sectional view of an exemplary paired fuel
window-air orifices of an exemplary fuel spray apparatus in
accordance with some embodiments;
[0016] FIG. 8 is a cross-sectional view of an exemplary paired fuel
window-air orifices of an exemplary fuel spray apparatus in
accordance with some embodiments;
[0017] FIG. 9 is a top-down illustration of an exemplary fuel spray
apparatus in accordance with some embodiments;
[0018] FIG. 10 is a simplified illustration of an exemplary fuel
spray apparatus in accordance with some embodiments;
[0019] FIG. 11 is a schematic illustration of a cross-section of
the exemplary fuel spray apparatus of FIG. 10 showing layer
arrangements of conduits and heat shield walls in accordance with
some embodiments;
[0020] FIG. 12 is a cross-sectional view of an exemplary paired
fuel window-air orifices of an exemplary fuel spray apparatus in
accordance with some embodiments; and
[0021] FIG. 13 shows a flow diagram of an exemplary process of
spraying fuel in an augmented gas turbine engine in accordance with
some embodiments.
[0022] Elements in the figures are illustrated for simplicity and
clarity and have not necessarily been drawn to scale. For example,
the dimensions and/or relative positioning of some of the elements
in the figures may be exaggerated relative to other elements to
help to improve understanding of various embodiments. Also, common
but well-understood elements that are useful or necessary in a
commercially feasible embodiment are often not depicted in order to
facilitate a less obstructed view of these various embodiments.
Certain actions and/or steps may be described or depicted in a
particular order of occurrence while those skilled in the art will
understand that such specificity with respect to sequence is not
actually required. The terms and expressions used herein have the
ordinary technical meaning as is accorded to such terms and
expressions by persons skilled in the technical field as set forth
above except where different specific meanings have otherwise been
set forth herein.
DETAILED DESCRIPTION
[0023] Generally speaking, pursuant to various embodiments,
systems, apparatuses and methods are provided herein useful for
spraying fuel in an augmented gas turbine engine. In some
embodiments, a fuel spray apparatus for spraying fuel in an
augmented gas turbine engine includes a spray bar with a fuel
injection aperture to inject a fuel jet into a fuel conduit; the
fuel conduit having a fuel window to discharge the fuel jet into a
core exhaust flow of an augmented gas turbine engine; a first
airflow conduit having a first orifice to discharge a first air
stream into the core exhaust flow; and a second airflow conduit
having a second orifice to discharge a second air stream into the
core exhaust flow, where the first orifice and the second orifice
are paired with the fuel window to cooperatively shape the fuel jet
coming out of the fuel window.
[0024] In some embodiments, a system for spraying fuel in an
augmented gas turbine engine includes a gas turbine engine having
an augmentor portion for burning fuel; and at least one fuel spray
bar for spraying fuel within the augmentor portion. In some
embodiments, the at least one fuel spray bar includes a first spray
bar with a fuel injection aperture to inject a first fuel jet into
a first fuel conduit; the first fuel conduit having a first fuel
window to discharge the first fuel jet into a core exhaust flow of
the augmentor portion; a first airflow conduit having a first
orifice to discharge a first air stream into the core exhaust flow;
and a second airflow conduit having a second orifice to discharge a
second air stream into the core exhaust flow, wherein the first
orifice and the second orifice are paired with the first fuel
window to cooperatively shape the first fuel jet coming out of the
first fuel window.
[0025] In some embodiments, a method for spraying fuel in an
augmented gas turbine engine includes directing a fuel jet into a
core exhaust flow of an augmented gas turbine engine via a fuel
window of a fuel conduit configured to receive the fuel jet from a
fuel injection aperture of a spray bar; directing a first air
stream into the core exhaust flow via a first orifice of a first
airflow conduit; and directing a second air stream into the core
exhaust flow via a second orifice of a second airflow conduit,
wherein the first air stream and the second air stream
cooperatively impinge the fuel jet into a shape as the fuel jet
comes out of the fuel window.
[0026] FIG. 1 is a partial cross-sectional illustration of an
exemplary augmented gas turbine engine 100 showing exemplary fuel
spray apparatuses 102 for spraying fuel in accordance with some
embodiments. In some embodiments, the augmented gas turbine engine
100 includes a center body 110, a fan duct 108, a turbine portion
112, an augmentor portion 106, and one or more fuel spray
apparatuses 102 as exemplified in FIG. 1. FIG. 1 generally
illustrates the general area where one or more of a fuel spray
apparatus 102 may be placed in an augmented gas turbine engine 100.
Additionally, the fuel spray apparatus 102 in FIG. 1 is shown in a
spray bar configuration. Those skilled in the art will recognize
that embodiments of a fuel spray apparatus 102 described herein may
be made/manufactured in various shaped configurations (e.g.,
vane-shaped configurations, heat shield configurations, flame
holder configurations). Additionally, those skilled in the art will
recognize that embodiments of a fuel spray apparatus 102 described
herein may be variously arranged/placed in the augmented gas
turbine engine 100 and/or the augmentor portion 106 complimenting
the improved fuel zone coverage brought on by the fuel spray
apparatus 102 described herein without departing from the scope of
the embodiments herein. In some embodiments, core exhaust flow 104
flows from the center body 110 towards the fuel spray apparatus 102
where a fuel stream from the fuel spray apparatus 102 is injected
into the core exhaust flow 104 and combusted. In operation, the
combustion may be aided by a flame holder (not shown), to provide
additional thrust. Those skilled in the art will recognize that
other components and/or sections, such as an inlet guide vanes, a
fan, a compressor, and a combustion chamber, to name a few, are not
shown that are generally included in an augmented gas turbine
engine 100.
[0027] FIG. 2 is a simplified illustration of an exemplary fuel
spray apparatus 102 in accordance with some embodiments. In some
embodiments, the fuel spray apparatus 102 of FIG. 2 corresponds to
the fuel spray apparatus 102 of FIG. 1. In some embodiments, the
fuel spray apparatus 102 includes one or more paired fuel
window-air orifices 202. A paired fuel window-air orifices 202
includes a fuel window 520 and one or more corresponding air
orifices, such as a first orifice 508 and a second orifice 510, as
described herein and shown on FIGS. 2, 3, 5-10, and 12. In some
embodiments, the fuel spray apparatus 102 includes a heat shield
body 210 and the one or more paired fuel window-air orifices 202.
For example, the fuel window 520, the first orifice 508, and the
second orifice 510 are defined in an external surface of the heat
shield body 210 and extend through the fuel conduit 506, the first
airflow conduit 516, and the second airflow conduit 518,
respectively. In some embodiments, the fuel spray apparatus 102
includes one or more fuel spray inlets 114 to receive fuel
discharged by the one or more paired fuel window-air orifices 202.
In some embodiments, a portion of the fuel spray apparatus 102 is
enclosed in the fan duct 108. In some embodiments, the portion of
the fuel spray apparatus 102 enclosed in the fan duct 108 includes
at least one fan duct inlet 204 to receive fan air/bypass air 208.
In some embodiments, portions of the fan air/bypass air 208 flowing
in the fan duct 108 enters the at least one fan duct inlet 204.
Remaining portions of the fan air/bypass air 208 flows around the
fan duct-enclosed portion of the fuel spray apparatus 102 to
continue downstream of the fan duct 108. In some embodiments, the
fuel spray apparatus 102 is secured to the fan duct 108 with one or
more fasteners 206. Such fasteners may include, for example, bolts
used for a flange, nuts, washers, to name a few. The fan air/bypass
air 208 flowing inside the fan duct 108 and portions of the one or
more fuel spray inlets 114 shown inside the fan duct 108 are
depicted as visible in FIG. 2 for illustration purposes. They are
enclosed by the heat shield body 210 and generally not visible.
Portions of the fuel spray apparatus 102 that are enclosed inside
the fan duct 108 are depicted as visible in FIG. 2 for illustration
purposes. Once the fuel spray apparatus 102 is fastened to the fan
duct 108, this portion of the fuel spray apparatus 102 is generally
not visible.
[0028] FIG. 3 is a perspective view of an exemplary fuel spray
apparatus 102 in accordance with some embodiments. In some
embodiments, the fuel spray apparatus 102 corresponds to the fuel
spray apparatus 102 of FIG. 2 and/or the fuel spray apparatus 102
of FIG. 1.
[0029] FIG. 4 is a cross-sectional view of the exemplary fuel spray
apparatus 102 of FIG. 3 as taken along line A-A of FIG. 3 in
accordance with some embodiments. In FIG. 4, the heat shield wall
406 is a top layer forming a surface of the fuel spray apparatus
102. In some embodiments, the heat shield wall 406 provides
protection/shielding to one or more spray bars 502 of FIGS. 5-9 of
the fuel spray apparatus 102 from the temperature environment
inside the augmented gas turbine engine 100. In some embodiments, a
main airflow conduit 402 directs the fan air/bypass air 208 to at
least partially surround a spray bar 502 that directs fuel to the
one or more fuel apertures 504. In some embodiments, the at least
one fan duct inlet 204 of FIG. 2 defines an opening to the main
airflow conduit 402 that directs the fan air/bypass air 208 to the
first airflow conduit 516 and/or the second airflow conduit 518 of
FIGS. 5, 6, and 8. In some embodiments, the first airflow conduit
516 and the second airflow conduit 518 are defined from cavities
through the heat shield wall 406 that terminate at distal ends
proximate to openings to the main airflow conduit 402 as shown in
FIG. 5. In some embodiments, the conduits, channels, cavities,
openings, orifices of the fuel spray apparatuses 102 described
herein are manufactured using one or more types of manufacturing
processes (e.g., 3D printing or additive manufacturing, CNC
machining, polymer casting, rotational molding, vacuum forming,
injection molding, extrusion, and blow molding, to name a few).
[0030] FIG. 5 is a cross-sectional view of an exemplary paired fuel
window-air orifices 202 of the exemplary fuel spray apparatus 102
of FIG. 3 as taken along line B-B of FIG. 3 in accordance with some
embodiments. In some embodiments, a paired fuel window-air orifices
202 includes a spray bar 502 with a fuel injection aperture 504 for
injecting a fuel jet into a fuel conduit 506. In some embodiments,
the paired fuel window-air orifices 202 includes the fuel conduit
506 having a fuel window 520 to discharge the fuel jet into a core
exhaust flow 104 of an augmented gas turbine engine 100. In some
embodiments, the paired fuel window-air orifices 202 includes a
first airflow conduit 516 having a first orifice 508 to discharge a
first air stream into the core exhaust flow 104. In some
embodiments, the paired fuel window-air orifices 202 includes a
second airflow conduit 518 having a second orifice 510 to discharge
a second air stream into the core exhaust flow 104. The first
orifice 508 and the second orifice 510 are paired with the fuel
window 520 to cooperatively shape the fuel jet coming out of the
fuel window 520. At least one of the benefits of shaping the fuel
jet as it comes out of the fuel window 520 is to improve fuel zone
coverage. Better fuel flow penetration into the core of the
augmented gas turbine engine 100 as well as dispersion and
atomization of the fuel are achieved by pairing one or more air
orifices 508, 510 with the fuel window 520.
[0031] For example, in some embodiments, at least one of a first
shape of the first orifice 508 and a second shape of the second
orifice 510 may include, for example, a circular shape, oval shape,
rectangular shape, square shape, triangular shape, and/or
trapezoidal shape, among other geometrical shapes. In some
embodiments, the first orifice 508 and/or the second orifice 510
may be sized based on a predetermined and/or desired fuel zone
coverage, dispersion, and/or atomization of the fuel. In some
embodiments, the first orifice 508 and the second orifice 510 are
substantially shaped and/or sized similarly and/or equally. In some
embodiments, the first orifice 508 and the second orifice 510 are
differently and/or distinctively shaped and/or sized. In some
embodiments, the first orifice 508 is configured to discharge a
first air stream having a first angular range 514. In some
embodiments, the second orifice 510 is configured to discharge a
second air stream having a second angular range 512. In some
embodiments, the first angular range 514 and the second angular
range 512 are substantially the same. In some embodiments, the
first angular range 514 is different and/or distinct from the
second angular range 512. In some embodiments, the first angular
range 514 and/or the second angular range 512 comprise an angular
range from 20 degrees to 90 degrees. In some embodiments, the first
orifice 508 and the second orifice 510 are shaped, sized, and/or
configured to have a particular angular range 512, 514 to achieve a
predetermined and/or desired fuel zone coverage, dispersion, and/or
atomization of the fuel.
[0032] In some embodiments, one of the benefits of having the main
airflow conduit 402 run along a radial length of the fuel spray
apparatus 102 is to cooperatively shape the fuel jet coming out of
the fuel window 520. This may be achieved by supplying air to the
first airflow conduit 516, the second airflow conduit 518, the
first subchannel 802, the third subchannel 804, the second
subchannel 602, the fourth subchannel 604, the upstream gap 702,
and/or the downstream gap 704. In some embodiments, another benefit
of having the main airflow conduit 402 defined along a radial
length of the fuel spray apparatus 102 is to remove heat from the
fuel spray apparatus 102 as air flows through the fuel spray
apparatus 102 and out of the first airflow conduit 516, the second
airflow conduit 518, the first subchannel 802, the third subchannel
804, the second subchannel 602, the fourth subchannel 604, the
upstream gap 702, and/or the downstream gap 704 as shown and/or
described in FIG. 8 below.
[0033] In some embodiments, a first centerline 522 of the first
airflow conduit 516 is at a first angle relative to a second
centerline 526 of the fuel conduit 506. In some embodiments, a
third centerline 524 of the second airflow conduit 518 is at a
second angle relative to the second centerline 526 of the fuel
conduit 506. For example, during the manufacturing process, each of
the first airflow conduit 516 and the second airflow conduit 518
along with the first orifice 508 and the second orifice 510 may be
formed, molded, machined, and/or printed at a particular angle
relative to the second centerline 526 of the fuel conduit 506 to
cooperatively shape the fuel jet coming out of the fuel window 520.
In some embodiments, each paired fuel window-air orifices 202 in
the fuel spray apparatus 102 may be formed, molded, machined,
and/or printed based on its location, position, and/or placement
relative to the core exhaust flow 104 in the augmented gas turbine
engine 100. In some embodiments, the fuel window 520 is
approximately equidistant from both the first orifice 508 and the
second orifice 510.
[0034] In some embodiments, the centerline of the fuel window 520
is approximately equidistant from both centerlines of the first
orifice 508 and the second orifice 510. In some embodiments, the
first orifice 508 is positioned substantially across from the
second orifice 510 relative to the fuel window 520. In one example,
the centerlines of the fuel window 520, the first orifice 508, and
the second orifice 510 are axially aligned. In some embodiments, a
shape of the fuel window 520 may be geometrically shaped (for e.g.,
a circular shape, oval shape, rectangular shape, square shape,
triangular shape, and/or trapezoidal shape, etc.). In some
embodiments, the first airflow conduit 516 and the second airflow
conduit 518 are configured to receive at least one of bypass air
and bleed air of the augmented gas turbine engine. In some
embodiments, the bypass air is an air stream from a fan of the
augmented gas turbine engine 100 that bypasses the engine core of
the augmented gas turbine engine 100. In some embodiments, the
bleed air is sourced from a compressor bleed offtake and/or
elsewhere on the augmented gas turbine engine 100.
[0035] In some embodiments, the corresponding one or more air
orifices paired with the fuel window 520 are defined in one or more
openings to the fuel conduit 506 as shown in FIG. 6. FIG. 6 is a
cross-sectional view of an exemplary paired fuel window-air
orifices 202 of an exemplary fuel spray apparatus 102 in accordance
with some embodiments. In some embodiments, the first airflow
conduit 516 terminates at a distal end proximate a second
subchannel 602 terminating at a first opening 606 into the fuel
conduit 506. In some embodiments, the second subchannel 602
terminates perpendicularly at the first opening 606 relative to the
fuel conduit 506. In some embodiments, the second airflow conduit
518 terminates at a distal end proximate a fourth subchannel 604
terminating at a second opening 608 into the fuel conduit 506. In
some embodiments, the fourth subchannel 604 terminates
perpendicularly at the second opening 608 relative to the fuel
conduit 506. In some embodiments, one or both of the second
subchannel 602 and the fourth subchannel 604 terminates at an
oblique-angle that allows an air stream to be discharged at an
angular range from 0 degrees to 60 degrees at its corresponding
opening relative to the fuel conduit 506 as shown in FIG. 8.
[0036] In some embodiments, the first opening 606 is configured to
discharge an air stream at a third angular range 610. In some
embodiments, the second opening 608 is configured to discharge an
air stream at a fourth angular range 612. In some embodiments, the
third angular range 610 and the fourth angular range 612 are
substantially the same. In some embodiments, the third angular
range 610 is different and/or distinct from the fourth angular
range 612. In some embodiments, the third angular range 610 and/or
the fourth angular range 612 comprise an angular range from 0
degrees to 60 degrees, where 0 degrees is perpendicular relative to
the fuel conduit 506. The angular range is measured between 0
degrees and 60 degrees. In some embodiments, the first opening 606
and the second opening 608 are shaped, sized, and/or configured to
have a particular angular range 610, 612 to achieve a predetermined
and/or desired fuel zone coverage, dispersion, and/or atomization
of the fuel. In some embodiments, the first opening 606 into the
fuel conduit 506 is positioned substantially horizontally across
from the second opening 608 into the fuel conduit 506.
[0037] In some embodiments, the corresponding one or more air
orifices paired with the fuel window 520 are defined in one or more
gaps formed between the heat shield wall 406 and the spray bar 502
as shown in FIG. 7. FIG. 7 is a cross-sectional view of an
exemplary paired fuel window-air orifices 202 of an exemplary fuel
spray apparatus 102 in accordance with some embodiments. In some
embodiments, the heat shield wall 406 at least partially surrounds
the spray bar 502 proximate to the fuel injection aperture 504. In
some embodiments, the air from the main airflow conduit 402 is
directed to flow into an upstream gap 702 and a downstream gap 704
terminating at the fuel conduit 506. In some embodiments, the
upstream gap 702 and the downstream gap 704 are formed between the
heat shield wall 406 and the spray bar 502 to direct the air that
flows through these gaps to cooperatively impinge the fuel jet into
a shape as the fuel jet comes out of the fuel injection aperture
504 to the fuel conduit 506 and out of the fuel window 520. In some
embodiments, the fan air/bypass air 208 directed through the
upstream gap 702 and the downstream gap 704 forms an air curtain
exiting the fuel window 520 to shield the fuel jet from the core
exhaust flow 104.
[0038] In some embodiments, the corresponding one or more air
orifices paired with the fuel window 520 includes one or more
combination of air orifices shown and/or described in FIGS. 5-7. In
an illustrative non-limiting embodiment, the corresponding one or
more air orifices paired with the fuel window 520 may be as shown
and/or described in FIG. 8. FIG. 8 is a cross-sectional view of an
exemplary paired fuel window-air orifices 202 of an exemplary fuel
spray apparatus 102 in accordance with some embodiments. In some
embodiments, the first airflow conduit 516 splits into a first
subchannel 802 and the second subchannel 602. In some embodiments,
the first orifice 508 is located at a terminal end of the first
subchannel 802 and the second subchannel 602 terminates at the
first opening 606 into the fuel conduit 506. In some embodiments,
the second airflow conduit 518 splits into a third subchannel 804
and the fourth subchannel 604. In some embodiments, the second
orifice 510 is located at a terminal end of the third subchannel
804 and the fourth subchannel 604 terminates at the second opening
608 into the fuel conduit 506. In some embodiments, a centerline of
the first subchannel 802 is at an oblique-angle relative to the
second centerline 526 of the fuel conduit 506. In some embodiments,
a centerline of the third subchannel 804 is parallel relative to
the second centerline 526 of the fuel conduit 506. In some
embodiments, a centerline of the third subchannel 804 is parallel
to the second centerline 526 of the fuel conduit 506.
[0039] To further illustrate, FIG. 8 is described along with an
exemplary process/method 1300 shown in FIG. 13. FIG. 13 shows a
flow diagram of the exemplary process/method 1300 of spraying fuel
in an augmented gas turbine engine 100 in accordance with some
embodiments. In some embodiments, the exemplary process/method 1300
is applicable to the paired fuel window-air orifices 202 and/or the
fuel spray apparatus 102 shown and/or described in FIGS. 1-12. In
some embodiments, the method 1300 includes directing a fuel jet 810
into the core exhaust flow 104 of an augmented gas turbine engine
100 via a fuel window 520 of the fuel conduit 506 configured to
receive the fuel jet 810 from the fuel injection aperture 504 of
the spray bar 502, at step 1302. In some embodiments, the method
1300 includes directing a first air stream 806 into the core
exhaust flow 104 via the first orifice 508, at step 1304. In some
embodiments, the main airflow conduit 402 directs the fan
air/bypass air 208 to the first airflow conduit 516. In some
embodiments, the first subchannel 802 directs portions of the fan
air/bypass air 208 out of the first orifice 508 and discharges the
first air stream 806 into the core exhaust flow 104. In some
embodiments, the first air stream 806 shapes and/or steers
downwardly the fuel jet 810, thereby controlling the fuel zone
coverage, dispersion, and/or atomization of the fuel in the
augmented gas turbine engine 100. In some embodiments, the first
air stream 806 shields the fuel jet 810 flow from high momentum
core flow (e.g., the core exhaust flow 104) to improve fuel
penetration into the core of the augmented gas turbine engine 100.
In some embodiments, the method 1300 includes directing a third air
stream via the second subchannel 602 of the first airflow conduit
516 through the first opening 606 into the fuel conduit 506. In
some embodiments, the third air stream impinges on the fuel jet 810
as the fuel jet 810 comes out of the fuel injection aperture 504.
In some embodiments, the third air stream further shapes the
upstream side of the fuel jet 810.
[0040] In some embodiments, the method 1300 includes directing a
second air stream 808 into the core exhaust flow 104 via the second
orifice 510, at step 1306. In some embodiments, the main airflow
conduit 402 directs the fan air/bypass air 208 to the second
airflow conduit 518. In some embodiments, the third subchannel 804
directs portions of the fan air/bypass air 208 out of the second
orifice 510 and discharges the second air stream 808 into the core
exhaust flow 104. In some embodiments, the second air stream 808
shapes the fuel jet 810 to control the fuel zone coverage,
dispersion, and/or atomization of the fuel in the augmented gas
turbine engine 100. In some embodiments, the second air stream 808
builds a film layer that cools the component surface of the fuel
spray apparatus 102. In some embodiments, the second air stream 808
provides an air buffer from the fuel sprayed into the freestream
and/or the core exhaust flow 104 to abate against distress that
generally results from fuel wetting of the component surface and
temperature magnitude or gradient.
[0041] In some embodiments, the method 1300 includes directing a
fourth air stream via the fourth subchannel 604 of the second
airflow conduit 518 through the second opening 608 into the fuel
conduit 506 to additionally impinge on the fuel jet 810 as the fuel
jet 810 comes out of the fuel injection aperture 504. In some
embodiments, the method 1300 includes directing at least one of the
fan air/bypass air 208 and bleed air of the augmented gas turbine
engine 100 into the first airflow conduit 516 and the second
airflow conduit 518. In some embodiments, the method 1300 includes
directing the fan air/bypass air 208 to flow into the upstream gap
702 and/or downstream gap 704. In some embodiments, the upstream
gap 702 and the downstream gap 704 are formed between the heat
shield wall 406 and the spray bar 502 to cooperatively impinge the
fuel jet 810 into a shape as the fuel jet 810 comes out of the fuel
window 520. In some embodiments, the main airflow conduit 402
directs the fan air/bypass air 208 into the first airflow conduit
516 and the second airflow conduit 518.
[0042] FIG. 9 is a top-down view illustration of an exemplary fuel
spray apparatus 102 in accordance with some embodiments. In some
embodiments, the fuel spray apparatus 102 includes a plurality of
paired fuel window-air orifices 202. In some embodiments, each of a
first paired fuel window-air orifices 902, a second paired fuel
window-air orifices 904, a third paired fuel window-air orifices
906, and a fourth paired fuel window-air orifices 908 are variously
and/or distinctly configured relative to the others based at least
on a predetermined and/or desired fuel zone coverage, dispersion,
and/or atomization of the fuel. Variation in each of the plurality
of paired fuel window-air orifices 202 can be based on radial
groupings, axial groupings, and/or for every air orifice and/or on
each design parameter (e.g., directionality, shape, and/or size of
air orifices, to name a few, as described herein) of the paired
fuel window-air orifices 202. In some embodiments, each of the
plurality of paired fuel window-air orifices 202 can be
particularly optimized for corresponding fuel window throughout the
radial length of the fuel spray apparatus 102. In some embodiments,
each orifice of a paired fuel window-air orifices 202 can be offset
from the corresponding fuel window to align with the core exhaust
flow 104 and/or core flow streamlines. In some embodiments, pairing
of a particularly configured air orifices with a particular fuel
window for spraying fuel in an augmented gas turbine engine as
described herein improves flame holding capability, combustion
dynamics, and/or heat release distribution.
[0043] In an illustrative non-limiting example, the second orifice
510 associated with the first paired fuel window-air orifices 902
is of a circular shape while the first orifice 508 associated with
the second paired fuel window-air orifices 904 is of a square
shape. In another illustrative non-limiting example, the first
orifice 508 and the second orifice 510 associated with the third
paired fuel window-air orifices 906 are both of a circular shape
while the first orifice 508 and the second orifice 510 associated
with the fourth paired fuel window-air orifices 908 may both of an
oblong shape. In some embodiments, each paired fuel window-air
orifices 202 on a first side of the fuel spray apparatus 102 is
paired with substantially similarly configured paired fuel
window-air orifices 202 on an opposite to the first side of the
fuel spray apparatus 102 as shown in FIG. 9.
[0044] In some embodiments, the plurality of paired fuel window-air
orifices 202 are arranged in a fuel spray bar configuration for
spraying fuel within the augmentor portion 106. In an illustrative
non-limiting example, the first paired fuel window-air orifices 902
includes a spray bar 502 with a fuel injection aperture 504 to
inject a first fuel jet into a first fuel conduit 506. In some
embodiments, the first paired fuel window-air orifices 902 includes
the first fuel conduit 506 having a fuel window 520 to discharge
the first fuel jet into a core exhaust flow 104 in the augmentor
portion 106. In some embodiments, the first paired fuel window-air
orifices 902 includes a first airflow conduit 516 having a first
orifice 508 to discharge a first air stream 806 into the core
exhaust flow 104. In some embodiments, the first paired fuel
window-air orifices 902 includes a second airflow conduit 518
having a second orifice 510 to discharge a second air stream 808
into the core exhaust flow 104. The first orifice 508 and the
second orifice 510 are paired with the fuel window 520 to
cooperatively shape the first fuel jet coming out of the fuel
window 520. In some embodiments, the first orifice 508 is a first
distance 910 relative to the fuel window 520 while the second
orifice 510 is a second distance 912 relative to the fuel window
520. In some embodiments, the first orifice 508 is located on an
upstream side of the fuel window 520 relative to the core exhaust
flow 104. In some embodiments, the second orifice 510 is located on
a downstream side of the fuel window 520 relative to the core
exhaust flow 104.
[0045] In another illustrative non-limiting example, the second
paired fuel window-air orifices 904 includes a spray bar 502 with a
fuel injection aperture 504 to inject a second fuel jet into a fuel
conduit 506. In some embodiments, the fuel conduit 506 having a
fuel window 520 to discharge the second fuel jet into the core
exhaust flow 104. In some embodiments, a first airflow conduit 516
having a first orifice 508 to discharge a third air stream into the
core exhaust flow 104 and a second airflow conduit 518 having a
second orifice 510 to discharge a fourth air stream into the core
exhaust flow 104. In some embodiments, the first orifice 508 and
the second orifice 510 are paired with the fuel window 520 to
cooperatively shape the second fuel jet coming out of the fuel
window 520. In some embodiments, the first orifice 508 is a third
distance 914 relative to the fuel window 520 while the second
orifice 510 is a fourth distance 916 relative to the fuel window
520.
[0046] In another illustrative non-limiting example, the first
orifice 508 of the second paired fuel window-air orifices 904 is
adjacent to the second orifice 510 of the first paired fuel
window-air orifices 902. In some embodiments, the second orifice
510 of the first paired fuel window-air orifices 902 may be
configured to discharge the second air stream 808 at a first
angular range and the first orifice 508 of the second paired fuel
window-air orifices 904 may be configured to discharge the third
air stream 806 at a second angular range different from the first
angular range. In another illustrative non-limiting example, a
first shape of the second orifice 510 of the first paired fuel
window-air orifices 902 is distinct from a second shape of the
first orifice 508 of the second paired fuel window-air orifices
904.
[0047] FIG. 10 is a simplified illustration of an exemplary fuel
spray apparatus 1000 in accordance with some embodiments. In some
embodiments, the fuel spray apparatus 1000 includes one or more
paired fuel window-air orifices 202. In some embodiments, the fuel
spray apparatus 1000 includes a heat shield body 210 integrated
with the one or more paired fuel window-air orifices 202. In some
embodiments, the fuel spray apparatus 1000 includes one or more
fuel spray inlets 114 to receive fuel discharged by the one or more
paired fuel window-air orifices 202. In some embodiments, a portion
of the fuel spray apparatus 1000 is enclosed in the fan duct 108.
In some embodiments, the portion of the fuel spray apparatus 1000
enclosed in the fan duct 108 includes at least one fan duct inlet
1010 to receive fan air/bypass air 208. In some embodiments,
portions of the fan air/bypass air 208 flowing in the fan duct 108
enters the at least one fan duct inlet 1010 while the remaining
portions of the fan air/bypass air 208 flows around/bypasses the
fan duct-enclosed portion of the fuel spray apparatus 102 to
continue downstream of the fan duct 108. In some embodiments, the
fuel spray apparatus 1000 is secured to the fan duct 108 with one
or more fasteners 206. In some embodiments, the fuel spray
apparatus 1000 includes a bleed air supply pipe 1004, a bleed air
manifold 1006, and/or one or more control valves 1008. In some
embodiments, the bleed air supply pipe 1004 receives bleed air 1002
sourced from a compressor bleed offtake and/or elsewhere on the
augmented gas turbine engine 100. In some embodiments, the bleed
air from the bleed air supply pipe 1004 enters the bleed air
manifold 1006 and individually directs air to each bleed air
conduit 1102. The fan air/bypass air 208 flowing inside the fan
duct 108 and portions of the one or more fuel spray inlets 114 and
the bleed air supply pipe 1004 shown inside the fan duct 108 are
depicted as visible in FIG. 10 for illustration purposes. They are
enclosed by the heat shield body 210 and generally not visible.
Portions of the fuel spray apparatus 1000 including the at least
one fan duct inlet 1010 that are enclosed inside the fan duct 108
are depicted as visible in FIG. 10 for illustration purposes. Once
the fuel spray apparatus 102 is fastened to the fan duct 108, this
portion of the fuel spray apparatus 102 is generally not
visible.
[0048] To further illustrate, another illustrative non-limiting
examples of one or more paired fuel window-air orifices are shown
and described in FIGS. 11 and 10. FIG. 11 is a schematic
illustration of a cross-section of the exemplary fuel spray
apparatus 1000 of FIG. 10 showing layers of conduits and heat
shield walls arrangements 1100 in accordance with some embodiments.
FIG. 12 is a cross-sectional view of two exemplary paired fuel
window-air orifices 1200 of an exemplary fuel spray apparatus 1000,
in accordance with some embodiments. In some embodiments, a
distinction between the fuel spray apparatus 102 previously
described above and the fuel spray apparatus 1000 described below
is the alternative source of air supplying the first airflow
conduit 516, the second airflow conduit 518, the first subchannel
802, the third subchannel 804, the second subchannel 602, and/or
the fourth subchannel 604.
[0049] In FIG. 11, a heat shield external wall 1104 is a top layer
forming a surface and/or the heat shield body 210 of the fuel spray
apparatus 1000. In some embodiments, the heat shield external wall
1104 provides protection/shielding to spray bars 502 of FIG. 12
from the temperature environment inside the augmented gas turbine
engine 100. In some embodiments, the main airflow conduit 402
directs the fan air/bypass air 208 to at least partially surround a
spray bar 502 of FIG. 10. In some embodiments, the spray bar 502
directs fuel to the one or more fuel apertures 504 of the fuel
spray apparatus 1000. In some embodiments, the at least one fan
duct inlet 1010 of FIG. 10 is an opening to the main airflow
conduit 402 that receives the fan air/bypass air 208 from the fan
duct 108.
[0050] In some embodiments, the air from the main airflow conduit
402 is directed to flow into an upstream gap 702 and a downstream
gap 704 terminating at the fuel conduit 506. In some embodiments,
the upstream gap 702 and the downstream gap 704 are formed between
a heat shield internal wall 1106 and the spray bar 502 to direct
the air that flows through these gaps to cooperatively impinge the
fuel jet into a shape as the fuel jet comes out of the fuel
injection aperture 504 to the fuel conduit 506 and out of the fuel
window 520. In some embodiments, the first airflow conduit 516, the
second subchannel 602, and the first subchannel 802 are grown
within the heat shield internal wall 1106 and the heat shield
external wall 1104 using 3D printing or additive manufacturing
process. In some embodiments, the third subchannel 804, the fourth
subchannel 604, and the second airflow conduit 518 are grown within
the heat shield internal wall 1106 and the heat shield external
wall 1104 using 3D printing or additive manufacturing process. In
some embodiments, the bleed air flowing through the one or more
control valves 1008 supplies each of the first airflow conduit 516,
the second subchannel 602, the first subchannel 802, the third
subchannel 804, the fourth subchannel 604, and the second airflow
conduit 518 via the bleed air conduit 1102.
[0051] In some embodiments, the third subchannel 804 includes an
oblique subchannel portion 1202 and a parallel subchannel portion
1204. In some embodiments, a centerline of the oblique subchannel
portion 1202 is at an oblique angle relative to the second
centerline 526 of the fuel conduit 506. In some embodiments, the
oblique subchannel portion 1202 terminates at a distal end 1206 of
the parallel subchannel portion 1204. In some embodiments, the
parallel subchannel portion 1204 terminates at the second orifice
510. In some embodiments, a centerline of the parallel subchannel
portion 1204 is parallel relative to the second centerline 526 of
the fuel conduit 506.
[0052] The inventive subject matter is not limited to the specific
aspects described and illustrated herein. Different aspects and
adaptations besides those shown herein and described, as well as
many variations, modifications and equivalent arrangements will now
be apparent or will be reasonably suggested by the foregoing
specification and drawings, without departing from the substance or
scope of the inventive subject matter.
[0053] This written description uses examples to describe aspects
of the disclosure described herein, including the best mode, and
also to enable any person skilled in the art to practice aspects of
the disclosure, including making and using any devices or systems
and performing any incorporated methods.
[0054] Further aspects of the disclosure are provided by the
subject matter of the following clauses:
[0055] A fuel spray apparatus for spraying fuel in an augmented gas
turbine engine including a spray bar with a fuel injection aperture
to inject a fuel jet into a fuel conduit, the fuel conduit having a
fuel window to discharge the fuel jet into a core exhaust flow of
an augmented gas turbine engine, a first airflow conduit having a
first orifice to discharge a first air stream into the core exhaust
flow, and a second airflow conduit having a second orifice to
discharge a second air stream into the core exhaust flow, wherein
the first orifice and the second orifice are paired with the fuel
window to cooperatively shape the fuel jet coming out of the fuel
window.
[0056] The fuel spray apparatus of any preceding clause further
includes a second spray bar with a second fuel injection aperture
to inject a second fuel jet into a second fuel conduit, the second
fuel conduit having a second fuel window to discharge the second
fuel jet into the core exhaust flow, a third airflow conduit having
a third orifice to discharge a third air stream into the core
exhaust flow, and a fourth airflow conduit having a fourth orifice
to discharge a fourth air stream into the core exhaust flow,
wherein the third orifice and the fourth orifice are paired with
the second fuel window to cooperatively shape the second fuel jet
coming out of the second fuel window, wherein the first orifice is
a first distance relative to the fuel window and the second orifice
is a second distance relative to the fuel window, and wherein the
third orifice is a third distance relative to the second fuel
window and the second orifice is a fourth distance relative to the
second fuel window.
[0057] The fuel spray apparatus of any preceding clause wherein the
first airflow conduit splits into a first subchannel and a second
subchannel, and wherein the first orifice is located at a terminal
end of the first subchannel and the second subchannel terminates at
a first opening into the fuel conduit.
[0058] The fuel spray apparatus of any preceding clause wherein the
second airflow conduit splits into a third subchannel and a fourth
subchannel, wherein the second orifice is located at a terminal end
of the third subchannel and the fourth subchannel terminates at a
second opening into the fuel conduit.
[0059] The fuel spray apparatus of any preceding clause wherein the
first opening into the fuel conduit is positioned substantially
horizontally across the second opening into the fuel conduit.
[0060] The fuel spray apparatus of any preceding clause wherein a
first centerline of the first airflow conduit is at a first angle
relative to a second centerline of the fuel conduit, and wherein a
third centerline of the second airflow conduit is at a second angle
relative to the second centerline of the fuel conduit.
[0061] The fuel spray apparatus of any preceding clause further
including a main airflow conduit to direct air into the first
airflow conduit and the second airflow conduit, and a heat shield
wall at least partially surrounding the spray bar proximate the
fuel injection aperture, wherein the air is directed to flow into a
gap between the heat shield wall and the spray bar to cooperatively
impinge the fuel jet into the shape as the fuel jet comes out of
the fuel window and form an air curtain to shield the fuel jet from
the core exhaust flow.
[0062] The fuel spray apparatus of any preceding clause wherein at
least one of a first shape of the first orifice and a second shape
of the second orifice comprises a circular shape.
[0063] The fuel spray apparatus of any preceding clause wherein the
fuel window is approximately equidistant from both the first
orifice and the second orifice.
[0064] The fuel spray apparatus of any preceding clause wherein the
first orifice is positioned substantially across the second orifice
relative to the fuel window.
[0065] The fuel spray apparatus of any preceding clause wherein the
first airflow conduit and the second airflow conduit are configured
to receive at least one of bypass air and bleed air of the
augmented gas turbine engine.
[0066] A system for spraying fuel in an augmented gas turbine
engine, the system including a gas turbine engine having an
augmentor portion for burning fuel, and at least one fuel spray bar
for spraying fuel within the augmentor portion, the at least one
fuel spray bar including a first spray bar with a fuel injection
aperture to inject a first fuel jet into a first fuel conduit, the
first fuel conduit having a first fuel window to discharge the
first fuel jet into a core exhaust flow of the augmentor portion, a
first airflow conduit having a first orifice to discharge a first
air stream into the core exhaust flow, and a second airflow conduit
having a second orifice to discharge a second air stream into the
core exhaust flow, wherein the first orifice and the second orifice
are paired with the first fuel window to cooperatively shape the
first fuel jet coming out of the first fuel window.
[0067] The fuel spray apparatus of any preceding clause wherein the
at least one fuel spray bar further including a second spray bar
with a second fuel injection aperture to inject a second fuel jet
into a second fuel conduit, the second fuel conduit having a second
fuel window to discharge the second fuel jet into the core exhaust
flow, a third airflow conduit having a third orifice to discharge a
third air stream into the core exhaust flow, and a fourth airflow
conduit having a fourth orifice to discharge a fourth air stream
into the core exhaust flow, wherein the third orifice and the
fourth orifice are paired with the second fuel window to
cooperatively shape the second fuel jet coming out of the second
fuel window, wherein the first orifice is a first distance relative
to the fuel window and the second orifice is a second distance
relative to the fuel window, and wherein the third orifice is a
third distance relative to the second fuel window and the second
orifice is a fourth distance relative to the second fuel
window.
[0068] The fuel spray apparatus of any preceding clause wherein the
third orifice is adjacent to the second orifice, the second orifice
configured to discharge the second air stream at a first angular
range and the third orifice configured to discharge the third air
stream at a second angular range different from the first angular
range.
[0069] The fuel spray apparatus of any preceding clause wherein the
third orifice is adjacent to the second orifice, and wherein a
first shape of the second orifice is distinct from a second shape
of the third orifice.
[0070] The fuel spray apparatus of any preceding clause wherein the
first orifice is located on an upstream side of the fuel window
relative to the core exhaust flow, and wherein the second orifice
is located on a downstream side of the fuel window relative to the
core exhaust flow.
[0071] A method for spraying fuel in an augmented gas turbine
engine including directing a fuel jet into a core exhaust flow of
an augmented gas turbine engine via a fuel window of a fuel conduit
configured to receive the fuel jet from a fuel injection aperture
of a spray bar, directing a first air stream into the core exhaust
flow via a first orifice of a first airflow conduit, and directing
a second air stream into the core exhaust flow via a second orifice
of a second airflow conduit, wherein the first air stream and the
second air stream cooperatively impinge the fuel jet into a shape
as the fuel jet comes out of the fuel window.
[0072] The fuel spray apparatus of any preceding clause further
including directing a third air stream via a subchannel of the
first airflow conduit through a first opening into the fuel conduit
to impinge on the fuel jet as the fuel jet comes out of the fuel
injection aperture.
[0073] The fuel spray apparatus of any preceding clause further
including directing a fourth air stream via a subchannel of the
second airflow conduit through a second opening into the fuel
conduit to additionally impinge on the fuel jet as the fuel jet
comes out of the fuel injection aperture.
[0074] The fuel spray apparatus of any preceding clause further
including directing at least one of bypass air and bleed air of the
augmented gas turbine engine into the first airflow conduit and the
second airflow conduit.
* * * * *