A combustor includes radially spaced apart outer and inner liners joined together at upstream ends through an annular dome disposed coaxially about a longitudinal centerline axis. A plurality of circumferentially spaced apart fuel injectors are disposed adjacent to an arcuate a splashplate for injecting fuel thereagainst, the splashplate being arcuate about the centerline axis. Primary air is channeled along the splashplate for mixing with the injected fuel for forming a fuel/air mixture dischargeable from the splashplate into a combustion zone defined between the liners and the dome.

TECHNICAL FIELD 
The present invention relates generally to gas turbine engines, and, more 
specifically, to a combustor therefor. 
BACKGROUND ART 
Gas turbine engines used for powering aircraft, for example, include a 
compressor for compressing ambient air for providing compressed air to a 
combustor disposed axially downstream therefrom. Fuel is mixed with the 
compressed air in the combustor and ignited for generating combustion 
gases which are discharged therefrom axially downstream to a high pressure 
turbine which powers the compressor. 
The fuel is mixed with the compressed air in the combustor typically in a 
plurality of circumferentially spaced apart carburetors each including a 
fuel injector and an air swirler. The carburetors are typically disposed 
in the dome of the combustor radially between the outer and inner 
combustion liners thereof. Since a plurality of circumferentially spaced 
carburetors are utilized, the resulting fuel/air mixtures discharged 
therefrom inherently provide a circumferentially varying profile with a 
corresponding circumferentially varying temperature distribution in the 
combustion gases generated therefrom. 
A pattern factor is a conventionally known parameter which indicates the 
amount of circumferential variation of the combustion gas temperature 
around the combustor outlet and has a value ranging between about 
0.25-0.30 for high performance combustors. Improvements in the pattern 
factor are being considered with levels reduced to about 0.15 which is a 
substantially low value requiring improved circumferential uniformity of 
the fuel/air mixture being discharged from the carburetors of the 
combustor. 
The shorter a combustor is made in the axial direction for reducing weight 
and cooling-air requirements thereof, the greater is the difficulty in 
achieving reduced pattern factor. 
OBJECTS OF THE INVENTION 
Accordingly, one object of the present invention is to provide a new and 
improved gas turbine engine combustor. 
Another object of the present invention is to provide a combustor having 
improved circumferential uniformity of a fuel/air mixture for reducing 
pattern factor, and to do so with fewer fuel injection points. 
Another object of the present invention is to provide a more compact and 
axially shorter combustor and combustor casing, for providing a more 
compact and lower weight engine. 
DISCLOSURE OF INVENTION 
A combustor includes radially spaced apart outer and inner liners joined 
together at upstream ends through an annular dome disposed coaxially about 
a longitudinal centerline axis. A plurality of circumferentially spaced 
apart fuel injectors are disposed adjacent to a splashplate for injecting 
fuel thereagainst, the splashplate being arcuate about the centerline 
axis. Primary air is channeled along the splashplate for mixing with the 
injected fuel for forming a fuel/air mixture dischargeable from the 
splashplate into a combustion zone defined between the liners and the dome 
.

MODE(S) FOR CARRYING OUT THE INVENTION 
Illustrated in FIG. 1 is an exemplary gas turbine engine 10 including an 
annular combustor 12 having an axial, longitudinal centerline axis 14. The 
engine 10 also includes an inlet 16 for receiving ambient air 18 which is 
compressed in a conventional centrifugal compressor 20 which includes a 
conventional diffuser 22 which discharges compressed air 24 around the 
combustor 12. Fuel 26 is provided from a conventional fuel supply 28 and 
channeled to the combustor 12 as further described hereinbelow, mixed with 
the compressed air 24, and conventionally ignited to generate combustion 
gases 30 which are discharged from the combustor 12 through a conventional 
nozzle 32 for flow to a conventional high pressure turbine 34 which is 
conventionally joined to the compressor 20 for powering the compressor 20 
during operation. The combustion gases 30 flow downstream from the turbine 
34 through a conventional low pressure turbine (not shown) for 
conventionally powering an output shaft (not shown), and then are 
discharged from a conventional outlet 36. 
The combustor 12 in accordance with one embodiment of the present invention 
is shown in more particularity in FIG. 2 and is conventionally disposed 
radially inwardly of a conventional annular casing 38 which surrounds the 
engine 10. The combustor 12 includes an annular, radially outer combustion 
liner 40, disposed coaxially about the centerline axis 14, which includes 
a forward or upstream end 40a and a downstream or aft end 40b. An annular 
radially inner combustion liner 42 is disposed coaxially about the 
centerline axis 14 and is spaced radially inwardly from the outer liner 
40, and includes a forward or upstream end 42a and a downstream or aft end 
42b. 
An annular dome 44 is disposed coaxially about the centerline axis 14 and 
is conventionally fixedly joined to the outer and inner liner forward ends 
40a and 42a. The outer liner 40, the inner liner 42, and the dome 44 
define therebetween a combustion zone 46 which extends from the dome 44 
axially downstream to the liner aft ends 40b and 42b which define radially 
therebetween an annular combustor outlet 48 disposed coaxially about the 
centerline axis 14. 
In accordance with the present invention, an arcuate slinger or splashplate 
50 is fixedly joined to one of the outer liner 40, the inner liner 42, and 
the dome 44 and is disposed coaxially about the centerline axis 14 in flow 
communication with the combustion zone 46. In the embodiment illustrated 
in FIG. 2, the splashplate 50 is joined to the outer liner 40 and spaced 
aft from the dome 44 at a predetermined axial distance L.sub.1. Also in 
the embodiment illustrated in FIG. 2, the splashplate 50 is annular, or a 
full 360.degree. ring disposed radially outwardly from the centerline axis 
14 at an inner radius R. The splashplate 50 is preferably fixedly joined 
to the outer liner 40 by being disposed in an annular housing 52 disposed 
coaxially about the centerline axis 14 and may be formed integrally 
therewith as a conventional casting. The splashplate 50 includes first and 
second opposite, arcuate surfaces 50a and 50b, a leading end 50c and a 
trailing edge 50d. In the embodiment illustrated in FIG. 2, the 
splashplate first surface 50a is disposed radially outwardly from the 
splashplate second surface 50b, with the former being convex and the 
latter being concave about the centerline axis 14. 
Extending radially inwardly into the housing 52 are a plurality of 
circumferentially spaced apart conventional fuel injectors 54 which may be 
in the exemplary form of plain jet atomizing fuel injectors. Each of the 
fuel injectors 54 includes an outlet 54a disposed adjacent to the 
splashplate 50 for injecting the fuel 26 against the splashplate 50. As 
illustrated in more particularity in FIG. 3, the fuel injector outlets 54a 
are preferably inclined tangentially to the splashplate 50 at an acute 
angle A, of about 30.degree. for example, for injecting the fuel 26 
tangentially, also at the acute angle A, against the splashplate first 
surface 50a in a circumferential direction D.sub.c. 
Referring again to FIG. 2, means are provided for channeling a portion of 
the compressed air 24 as primary air 24a along the splashplate 50 for 
mixing with the injected fuel 26 for forming a fuel/air mixture 56 which 
is discharged from the splashplate 50 into the combustion zone 46. 
As illustrated in more particularity in FIG. 4, the air channeling means 
includes an annular first channel 58 disposed in the housing 52 adjacent 
to the splashplate first surface 50a and coaxially about the centerline 
axis 14. The first channel 58 extends axially along the splashplate first 
surface 50a and includes a first inlet portion 58a for receiving the 
primary air 24a followed in turn by a first intermediate portion 58b which 
extends axially forward from, in the upstream direction relative to the 
flow of the combustion gases 30, the first inlet portion 58a in flow 
communication therewith for receiving the primary air 24a therefrom. The 
fuel injections 54 extend through the housing 52 through apertures 60 
therein which join to the outer surface of the channel first intermediate 
portion 58b for being disposed in flow communication therewith. The fuel 
26 from the injectors 54 mixes in the first intermediate portion 58b with 
the primary air 24a for forming the fuel/air mixture 56. The first channel 
58 also includes a first outlet 58c disposed in flow communication with 
the forward end of the first intermediate portion 58b at the splashplate 
trailing edge 50d for discharging the fuel/air mixture 56 toward the dome 
44 in the upstream direction in the combustion zone 46 relative to the 
combustion gases 30 which flow generally downstream therein. 
As shown in FIG. 2, the combustion zone 46 includes a primary zone 46a 
extending from the dome 44 downstream to about the axial plane of the fuel 
injectors 54 and splashplate 50. Since the splashplate 50 extends 
generally axially, with the first channel 58 extending in a generally 
upstream direction with the channel first outlet 58c facing upstream 
toward the dome 44, the primary air 24a channeled through the first 
channel 58 will mix with the fuel 26 injected into the channel first 
intermediate portion 58b against the splashplate first surface 50a and 
purge the fuel 26 from the first channel 58 toward the dome 44 in the 
primary zone 46a. Since the fuel 26 is injected against the splashplate 
first surface 50a at the angle A as illustrated in FIG. 3, the resulting 
fuel/air mixture 56 will experience velocity components both in the 
circumferential direction D.sub.c and in an upstream axial direction 
D.sub.a, as shown in FIG. 2, toward the dome 44. Accordingly, the 
splashplate 50 will sling the fuel/air mixture 56 in the circumferential 
direction D.sub.c for forming a substantially annular sheet of atomized 
fuel, i.e. fuel/air mixture 56 into the primary zone 46a. In this way, a 
more uniform circumferential distribution of the fuel/air mixture 56 may 
be obtained with a resulting reduction in pattern factor of the combustion 
gases 30 discharged from the outlet 48 of the combustor 12. 
The degree of circumferential uniformity of the fuel/air mixture 56 
discharged from the annular first outlet 58c is directly related to the 
number of fuel injectors 54 disposed around the circumference of the 
combustor 12 and the velocity of the primary air 24a channeled through the 
first channel 58. It is also related to the inclination or impingement 
angle A of the fuel 26 from the injector outlets 54a against the 
splashplate first surface 50a. Referring to FIGS. 5 and 6, the fuel 
injectors 54 are shown aligned in a single axial plane for injecting the 
fuel 26 at the acute angle A. However, the fuel injectors 54 could also be 
inclined in the axial direction as well as the circumferential direction 
for discharging the fuel 26 with both a circumferential component of 
velocity (D.sub.c) as well as an axial component of velocity in the 
upstream direction (D.sub.a) if desired. In order to improve the 
circumferential spreading or slinging of the fuel/air mixture 56 in the 
circumferential direction D.sub.c, the channel first inlet portion 58a is 
in the exemplary form of a plurality of circumferentially spaced apart 
first apertures, also designated 58a, each inclined circumferentially at 
an acute angle B measured in the upstream direction toward the dome 44 
from the circumferential direction D.sub.c for discharging the primary air 
24a into the channel first intermediate portion 58b with a component of 
velocity in the circumferential direction D.sub.c, and, preferably with a 
velocity component in the upstream axial direction D.sub.a as well. The 
velocity components of the fuel 26 and the primary air 24a are preferably 
co-rotational in the same circumferential direction D.sub.c for increasing 
the circumferential slinging of the fuel/air mixture 56 from the first 
outlet 58c into the primary zone 46a. 
In order to additionally control or increase the circumferential spreading 
of the fuel/air mixture discharged from the first outlet 58c, the housing 
52 further includes an annular second channel 62 as illustrated in FIGS. 4 
and 6. The second channel 62 is disposed adjacent to the splashplate 
second, or flameside, surface 50b and coaxially about the centerline axis 
14. The second channel 62 includes a second inlet portion 62a, also 
preferably in the form of a plurality of circumferentially spaced apart 
second apertures, for receiving a portion of the compressed air 24 as 
secondary air 24b. A second intermediate portion 62b extends axially from 
the second inlet portion 62a along the splashplate 50 toward the trailing 
edge 50d in flow communication with the second inlet portion 62a for 
receiving the secondary air 24b therefrom. A second outlet 62c is disposed 
in flow communication with the second intermediate portion 62b at the 
splashplate trailing edge 50d for discharging the secondary air 24b 
adjacent to the fuel/air mixture 56 discharged from the first outlet 58 c. 
The secondary air 24b thusly cools the flameside of the splashplate 50, 
i.e. the splashplate second surface 50b, and assists in further atomizing 
the fuel 26 contained in the fuel/air mixture 56. In the preferred 
embodiment of the present invention, the second inlet portion apertures 
62a as shown in FIG. 6 are also preferably inclined in the circumferential 
direction at an acute angle C which may be equal to the acute angle B, for 
example, for discharging the secondary air 24b into the second 
intermediate portion 62b with a component of velocity in the 
circumferential direction D.sub.c, and, preferably with a velocity 
component in the upstream axial direction D.sub.a. The secondary air 24b 
is thusly caused to swirl in the circumferential direction D.sub.c and 
upon discharge from the second outlet 62c promotes the circumferential 
spreading of the fuel/air mixture 56 as well as further atomizes the fuel 
26 therein. 
In the exemplary embodiment of the invention illustrated in FIG. 2, 4 and 6 
wherein the splashplate 50 is joined to the outer liner 40 downstream from 
the dome 44, the first and second inlet portions 58a and 62a face toward 
the outer liner aft end 40b, and the first and second outlets 58c and 62c 
and the splashplate trailing edge 50d face toward the dome 44 for 
channeling the primary air 24a and the secondary air 24b through the outer 
liner 40 axially upstream toward the dome 44 in the axial direction 
D.sub.a as well as in the circumferential direction D.sub.c. In this way, 
an annular or toroidal main vortex 64 is formed coaxially about the 
centerline axis 14 in the primary zone 46a. Since the fuel/air mixture 56 
is injected into the primary zone 46a from the first outlet 58c which is a 
360.degree. annular slot, and is directed radially inwardly toward the 
dome 44, and since the inner liner 42 extends axially downstream from the 
dome 44, a toroid or toroidal vortex recirculation is formed which spins 
counterclockwise in its top half as illustrated in FIG. 2. Since the 
fuel/air mixture 56 also includes a circumferential component of velocity 
as shown in FIG. 6, the main vortex 64 also circulates circumferentially 
around the centerline axis 14. The main vortex 64 is formed of the 
fuel/air mixture 56 which may be conventionally ignited by a conventional 
igniter extending through the outer liner 40 between the dome 44 and the 
housing 52 (not shown) with the fuel/air mixture thereby undergoing 
combustion which recirculates in the form of the main vortex 64 before 
being channeled downstream through the combustor 12 as the combustion 
gases 30 which are discharged from the outlet 48. 
As shown in FIG. 2, the dome 44 preferably includes an annular film-cooling 
nugget 66 disposed coaxially about the centerline axis 14. The nugget 66 
includes a radially outwardly facing circumferential outer slot 66a 
disposed in flow communication with a plurality of circumferentially 
spaced apart apertures 68 through the dome 44. The nugget 66 also includes 
a radially inwardly facing circumferential inner slot 66b disposed in flow 
communication with a plurality of circumferentially spaced apart apertures 
70. The apertures 68 and 70 receive a portion of the compressed air 24 as 
film-cooling air 24c which is channeled into the respective outer and 
inner slots 66a and 66b for discharging the film-cooling air 24c radially 
outwardly and inwardly, respectively, along the dome 44 for the cooling 
thereof. The outer and inner liners 40 and 42 and the dome 44 include 
additional conventional film-cooling nuggets, as is conventionally known, 
which may be suitably angled to augment the vortex recirculation both 
radially and circumferentially if desired. 
However, in accordance with the present invention, the double flow nugget 
66 is provided in the dome 44 radially between the outer liner 40 and the 
inner liner 42 in alignment with the fuel/air mixture 56 discharged from 
the splashplate trailing edge 50d so that the channel first and second 
outlets 58c and 62c face the nugget 66 for discharging the fuel/air 
mixture and the secondary air 24b toward the nugget 66. In this way, the 
main vortex 64 is formed in the primary zone 46a radially below the nugget 
66, and a toroidal, pilot recirculation vortex 72 may be formed radially 
above the nugget 66 from a portion of the fuel/air mixture 56. As shown in 
FIG. 2, the pilot vortex 72 rotates in a clockwise direction for the upper 
half of the combustor 12 illustrated. The film-cooling air 24c discharged 
radially outwardly from the nugget outer slot 66a enhances the clockwise 
circulation of the pilot vortex 72, while the film-cooling air 24c 
discharged radially inwardly from the nugget inner slot 66b enhances the 
counterclockwise recirculation of the main vortex 64. In this way, the 
flame stability of the burning fuel/air mixture 56 may be improved by the 
pilot vortex 72 which may be selected for providing a relatively rich 
fuel/air mixture 56 at low power operation of the combustor 12. At low 
power operation, the velocity of the compressed air 24 is relatively low 
so that the fuel 26 discharged against the splashplate 50 will enter the 
primary zone 46a with relatively low momentum which will therefore foom a 
relatively rich pilot vortex 72. As power of the combustor 12 increases 
during operation, the velocity of the compressed air 24 increases with a 
corresponding increase in momentum of the fuel/air mixture 56 discharged 
from the splashplate trailing edge 50d with a majority of the fuel 26 
therein then being carried into the main vortex 64. 
In order to further enhance the main vortex 64, the inner liner 42 as 
illustrated in FIG. 2 includes a row of unopposed (in the outer liner 40) 
circumferentially spaced apart dilution holes 74 disposed generally 
radially below the fuel injectors 54 and generally aligned axially with 
the first and second outlets 58c and 62c (see FIG. 4) and spaced aft of 
the dome 44 an axial distance L.sub.2 for channeling radially outwardly 
into the combustion zone 46 another portion of the compressed air 24 as 
dilution air 24d for enhancing axial recirculation of the main vortex 64 
of the fuel/air mixture 56 and the secondary air 24b. 
Accordingly, the combustor 12 is effective for eliminating the injection of 
a plurality of fuel/air mixtures at discrete circumferentially spaced 
apart locations as found in conventional combustors, while providing the 
annular splashplate 50 which allows the fuel injectors 54 to provide a 
more uniform annular sheet of atomized fuel as the fuel/air mixture 56 
discharged from along the splashplate trailing edge 50d. The improved 
circumferential uniformity of the fuel/air mixture 56 will improve the 
pattern factor, or circumferential uniformity of the temperature of the 
combustion gases 30 discharged from the combustor outlet 48. Furthermore, 
a single toroidal main vortex 64 and a single toroidal pilot vortex 72 are 
provided instead of the plurality of vortices associated with the 
respective plurality of circumferentially spaced apart carburetors in a 
conventional combustor, while providing flame stability at low power. The 
pilot vortex 72 is preferably rich at low power for good flame stability, 
while the main vortex 64 may be lean at higher power operation of reducing 
exhaust emissions. Yet further, by locating the injectors 54 and the 
housing 52 in the outer liner 40 downstream of the dome 44, a more compact 
and shorter combustor 12 having reduced weight by be obtained. 
Yet further, a relatively simple fuel atomizer in the form of the fuel 
injectors 54 injecting fuel against the single splashplate 50 by be 
obtained. The fuel injectors 54 be relatively simple in construction being 
a low pressure fuel design discharging a plain jet of the fuel 26 from the 
outlet 54a. In other embodiments of the invention, conventional high 
pressure fuel injectors 54 could be also be utilized. And, as shown in 
more particularity in FIG. 4, the fuel injector 54 may include a coaxial 
annular passage 76 therein surrounding the outlet 54a for channeling 
another portion of the compressed air 24 as injector air 24e around the 
fuel 26 for atomizing and directing the fuel 26 as well as for providing 
additional mixing of the fuel 26 with the injector air 24e prior to 
impinging against the splashplate 50. 
The velocity of the primary and secondary air 24a and 24b channeled through 
the first and second channels 58 and 62, respectively, and the inclination 
angles B and of the inlet apertures 58a and 62a may be selected as desired 
for controlling the amount of circumferential spreading of the fuel/air 
mixture 56 as well as for controlling the main vortex 64 and the pilot 
vortex 72 during operation of the combustor 12. 
Although it is generally desirable in accordance with the present invention 
to increase the circumferential spreading of the fuel/air mixture by the 
splashplate 50, the longer the fuel/air mixture 56 flows along the 
splashplate first surface 50a the more likely that the fuel 26 may form 
undesirable carbon deposits on the splashplate 50. Accordingly, in 
accordance with additional embodiments of the invention as illustrated in 
FIG. 7, a plurality of circumferentially spaced apart partitions 78 
extending radially outwardly from the splashplate 50 are provided to 
prevent circumferential flow past the partitions 78 in the first channel 
58. In this way, the circumferential travel of the fuel/air mixture 56 
within the bifurcated first channel 58 is limited by impingement against 
the partition 78. 
FIG. 7 also discloses an alternate embodiment of the splashplate 50 which 
may be in the form of a plurality of circumferentially spaced apart 
arcuate segments, designated 50A which are disposed coaxially about the 
centerline axis 16 at a common radius R therefrom. The spacing between the 
circumferentially adjacent segments 50A may be selected to ensure that the 
fuel/air mixture flows circumferentially along each segment 50A for a 
relatively short time to avoid undesirable buildup of carbon thereon. 
In the embodiment illustrated in FIG. 4, the fuel 26 is injected radially 
inwardly against the splashplate first surface 50a, with the flameside of 
the splashplate 50, i.e. splashplate second surface 50b, being cooled by 
the secondary air 24b. In the alternate embodiment of the invention 
illustrated in FIG. 8, the splashplate first surface 50a is instead 
disposed radially inwardly from the splashplate second surface 50b and is 
concave about the centerline axis 14. A suitable fuel injector 54A may be 
conventionally provided in the housing 52 for discharging the fuel 26 
radially upwardly toward the splashplate first surface 50a. 
Correspondingly, the first channel 58 is disposed radially inwardly of the 
splashplate 50 with the second channel 62 being disposed radially 
outwardly thereof. Since the splashplate first surface 50a is concave, and 
the fuel 26 and the primary air 24a flow therealong, the centrifugal 
forces acting thereon will improve the circumferential spreading thereof. 
Illustrated schematically in FIGS. 9 and 10 is another embodiment of the 
combustor designated 12A wherein the splashplate designated 50B is joined 
to an inner liner 42A at its forward end and extends radially outwardly. 
The first and second channels designated 58A and 62A are disposed axially 
oppositely apart toward the splashplate first and second surfaces 50a and 
50b, with the first and second inlet apertures 58A and 62A being inclined 
circumferentially oppositely to each other. The fuel injector designated 
54B provides the fuel 26 through the first channel 58A in impingement 
against the splashplate first surface 50a. The first row of the dilution 
holes 74 is disposed in this embodiment in the outer liner 40A axially 
downstream from the splashplate 50B to similarly enhance the main toroidal 
vortex 64 which in this embodiment of the invention flows in a clockwise 
direction in the upper half of the combustor 12A. The splashplate trailing 
edge 50d preferably projects into the combustion zone 46 for cooperating 
with the dome 44A to provide the pilot vortex 72 and flame holding or 
stability. 
As illustrated in FIG. 11, the splashplate trailing edge 50d may be 
recessed away from the combustion zone 46 to allow the secondary air 24b 
to more fully mix with the fuel/air mixture 56 before discharge into the 
combustion zone 46, as well as for ensuring that the splashplate 50B 
remains relatively cool preventing carbon buildup thereon. 
As shown in FIG. 4, the splashplate trailing edge 50d may be aligned with 
the inner surface of the outer liner 40. 
As shown in FIG. 12, the inner liner 42A may include an annular recess 80 
into which the splashplate trailing edge 50d extends. In this way, the 
fuel/air mixture 56 discharged from the first channel 58A may form two 
toroidal pilot vortexes 72a and 72b on both sides of the splashplate 50B 
for enhanced flame stability during low power operation of the combustor. 
FIG. 13 illustrates yet another embodiment of the combustor designated 12B 
wherein the splashplate designated 50C is joined to a radially center 
region of a dome 44B and is inclined radially and axially toward the outer 
liner 40B. The first channel 58B and the fuel injectors 54C are disposed 
on the radially outer side of the splashplate 50C with the second channel 
62B being disposed on the radially inner side of the splashplate 50C. The 
first row of dilution holes 74 are disposed in the outer liner 40B 
downstream of the dome 44B to enhance the formation of the main toroidal 
vortex 64 which flows in a clockwise direction in the upper half of the 
combustor 12B as shown in FIG. 13. The dome 44B includes an axial 
projection 82 which defines a portion of the first channel 58B, which 
allows the pilot vortex 72 to form behind it. 
Illustrated in FIG. 14 is another embodiment of the fuel injectors 
designated 54D which includes an outlet body 84 having a tangentially 
inclined fuel outlet 86 for impinging the fuel 26 against the splashplate 
50. A majority portion of the fuel injector 54D may extend directly 
radially outwardly from the outer liner 40 with only the fuel outlet 86 
being inclined. The outlet body 84 includes a concentric channel 88 
surrounding the fuel outlet 86 for channeling a portion of the compressed 
air 24 around the fuel outlet 86. The channel 88 includes an annular 
outlet 90 which discharges the compressed air 24 around the fuel 26 
discharged from the fuel outlet 86 for mixing therewith for generating the 
fuel/air mixture 56. 
Accordingly, in view of the several embodiments of the invention disclosed 
above, it will be apparent to those skilled in the art that various forms 
of the arcuate splashplate 50 may be utilized in either the combustor 
outer liner 40, inner liner 42, or dome 44 for injecting the fuel/air 
mixture 56 along a common radius into the combustion zone 46 as an annular 
sheet of fuel and air for improving circumferential uniformity of the 
fuel/air mixture 56, and therefore, improving the pattern factor of the 
combustion gases discharged from the combustor outlet 48. 
While there have been described herein what are considered to be preferred 
embodiments of the present invention, other modifications of the invention 
shall be apparent to those skilled in the art from the teachings herein, 
and it is, therefore, desired to be secured in the appended claims all 
such modifications as fall within the true spirit and scope of the 
invention. 
Accordingly, what is desired to be secured by Letters Patent of the United 
States is the invention as defined and differentiated in the following 
claims.