U.S. patent number 3,899,884 [Application Number 05/094,289] was granted by the patent office on 1975-08-19 for combustor systems.
This patent grant is currently assigned to General Electric Company. Invention is credited to Edward E. Ekstedt.
United States Patent |
3,899,884 |
Ekstedt |
August 19, 1975 |
Combustor systems
Abstract
The disclosure shows two versions of providing a venturi around
a fuel spray cone in a mixing chamber having an axial, vortical
flow of pressurized air therethrough. This mixture is discharged
into a combustion chamber. The venturi maintains desirable low
smoke formation while spacing the flame front of the ignited
mixture from the spray nozzle to reduce its temperature and thus
prevent undesired carbon formation thereon.
Inventors: |
Ekstedt; Edward E. (Cincinnati,
OH) |
Assignee: |
General Electric Company
(Cincinnati, OH)
|
Family
ID: |
22244287 |
Appl.
No.: |
05/094,289 |
Filed: |
December 2, 1970 |
Current U.S.
Class: |
60/737; 60/748;
431/183; 60/751 |
Current CPC
Class: |
F23R
3/04 (20130101); F23R 3/14 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F23R
3/14 (20060101); F23R 3/04 (20060101); F02c
007/22 () |
Field of
Search: |
;60/39.65,39.74
;431/183 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Hart; Douglas
Attorney, Agent or Firm: Sachs; Lee H. Lawrence; Derek
P.
Government Interests
The invention herein described was made in the course of or under a
contract, or a subcontract thereunder, with the U.S. Department of
the Air Force.
Claims
Having thus described the invention, what is claimed as novel and
desired to be secured by Letters Patent of the United States
is:
1. A combustor system comprising:
a combustion chamber,
a mixing chamber opening into the upstream end of the combustion
chamber,
a spray nozzle for discharging fuel as an atomized cone into said
mixing chamber, the axis of said spray cone extending lengthwise of
said mixing chamber toward said combustion chamber,
means for introducing pressurized air into the upstream end of said
mixing chamber and producing an axial flow field for dispersing the
fuel in fine droplets,
venturi means surrounding said spray cone and through which at
least a portion of the axially flowing air passes, and wherein
the air introducing means additionally provide a vortical component
to the air flow field,
the venturi means comprise a venturi tube mounted within said
mixing chamber,
a cylindrical conduit and an axial swirler at the upstream end of
the conduit define said mixing chamber,
said air introducing means includes an annular row of generally
radially oriented passageways angled through said swirler,
said axial swirler has a central opening through which the
discharge end of the spray nozzle projects, and
the inlet end of the venturi tube has a diameter intermediate the
minimum and maximum diameters of the annular row of swirler
passageways and is bonded to said swirler.
2. A combustion chamber as in claim 1 wherein the divergent
discharge end of the venturi tube terminates generally as a tangent
to the spray cone discharge from the nozzle.
3. A combustor as in claim 2 wherein:
a pressurized plenum is provided, in combination with the upstream
face of said axial swirler, and
the swirler passageways meter air into the mixing chamber at a rate
insufficient to produce a combustible mixture with the fuel
introduced by said spray nozzle, and
means are provided for introducing further pressurized air into
said combustion chamber sufficient to produce a combustible mixture
therein.
Description
The present invention relates to improvements in combustor systems,
particularly in the generation of a hot gas stream as in gas
turbine engines.
Combustor systems, as employed in gas turbine engines, comprise a
spray nozzle which injects fuel into a combustion zone. Once
ignited, a continuous flame front is maintained in the combustion
chamber as fuel and pressurized air flow therein and a high energy,
hot gas stream is discharged therefrom.
Recent emphasis had been placed on the problem of minimizing smoke
generated in the combustion process and discharged to the
atmosphere from gas turbine engines. One highly successful approach
to this problem has been to discharge the fuel into a conduit or
mixing chamber which opens into the combustion chamber. Pressurized
air is introduced axially and swirled vortically about the
discharge axis of the spray nozzle. In so doing, the turbulent flow
field created produces a highly dispersed, over-stoichiometric
mixture of fuel and air in the conduit. This mixture is discharged
in a generally conical fashion into the combustion chamber where it
is further dispersed by additional air entering other openings in
the combustion chamber. This additional air is sufficient to
sustain combustion and a flame front is produced in this mixing
zone at the mixing chamber discharge. Because of the high degree of
dispersion obtained, over-rich fuel zones are essentially
eliminated and smoke is minimized to the point of being virtually
undetectable.
While smoke is thus effectively reduced, the frequency of
maintenance of the fuel nozzles has increased. This is due to the
coking of fuel on the nozzles which adversley affects the pattern
of the fuel spray cone discharged therefrom. Various forms of spray
nozzles and air shrouds therefor have had limited degrees of
success in overcoming this problem and still maintaining minimized
smoke levels. This lack of success is attributed to the fine
dispersion of fuel which recirculates, in localized regions, and
contacts the discharge end of the nozzle. The fuel then cokes or
carbonizes when it contacts the nozzle due to the high temperature
thereof.
Accordingly, the object of the invention is to reduce the
temperature levels of fuel nozzles and, in so doing, minimize the
build-up of carbon thereon and further, to maintain minimal smoke
generation in the combustion process.
These ends are broadly attained by providing a venturi means into
which the fuel spray is discharged. The acceleration provided by
the initial portion of the venturi tube accelerates mixing air
introduced around the nozzle to an extent sufficient to prevent
combustion for a predetermined distance from the nozzle. By thus
displacing the flame front from the nozzle, its temperature may be
reduced sufficiently to prevent undesirable carbon buildup thereon.
The divergent portion of the venturi tube re-expands the mixing air
to discharge it into the combustion chamber at a relatively wide
angle consistent with the smoke minimizing dispersion process
referenced above.
Other features are found in the relationship of the venturi tube to
the means for introducing mixing air as well as in the amount of
mixing air introduced.
The above and other related objects and features of the invention
will be apparent from a reading of the following description of the
disclosure found in the accompanying drawings and the novelty
thereof pointed out in the appended claims.
In the drawings:
FIG. 1 is a schematic representation of a gas turbine engine
employing a combustor of the type herein referenced;
FIG. 2 is an enlarged longitudinal section illustrating the details
of the combustor referenced in FIG. 1 as they embody the present
invention;
FIG. 3 is a section taken on line III--III in FIG. 2; and
FIG. 4 is a longitudinal section, similar to FIG. 2, illustrating
another embodiment of the invention.
Referencing FIG. 1, the illustrated engine comprises an axial flow
compressor 10 which pressurizes air. This pressurized air flows
through an annular passageway 12 to an annular combustor 14 where
fuel is introduced. The pressurized air supports combustion of fuel
within the combustor to generate a high energy level, hot gas
stream. This hot gas stream drives a turbine 16 which in turn
powers the rotor of the compressor 10. The hot gas stream is then
converted to a useful output as by being discharged from a nozzle
17 to provide propulsive. thrust for an aircraft.
The combustor 14, as illustrated in FIG. 2, comprises outer and
inner liners 18 and 20 which define an annular combustion chamber
21. These liners are joined by compositely formed dome portion 22
at their upstream ends. Cylindrical conduits or mixing chambers 24
which open into the dome portion 22 and the combustion chamber 21.
Transition segments 26 blend the conduit openings into the dome
portion. An axial flow swirler 28 is mounted at the upstream end of
each conduit 24.
The swirler has a central opening which receives the discharge end
29 of a fuel spray nozzle 30. The nozzle 30 may take many forms but
is preferably characterized by at least one orifice outlet which
produces a conical spray discharge having a relatively large
included angle relative to an axis a which extends lengthwise of
the mixing chamber. The swirler 28 includes a row of passageways 32
annularly surrounding the axis of the nozzle discharge end 29. The
passageways 32 are angled relative to the nozzle axis to produce a
vortical flow field.
The swirler 28 may be mounted on the upstream end of the conduit 24
in the manner taught in copending U.S. application Ser. No.
796,391, filed Feb. 4, 1969 and of common assignment. The
referenced application also describes in further detail, the
relationship of the swirler passageways 32 in obtaining a high
degree of fuel dispersion for low smoke combustion.
Introduction of pressurized air from the annular compressor
discharge passageway 12 into the combustion chamber 21 will now be
described. The passageway 12 is defined by outer and inner,
generally cylindrical casings 34 and 36 which extend along the
lengths of the liners 18 and 20 are respectively spaced therefrom
to define annular passageways 38 and 40. An annular snout assembly
42 is secured to and projects upstream from the liners 18 and 20.
The snout assembly has a central passageway 43 having an entrance
facing the discharge passageway 12 and discharging into an annular
chamber 44 surrounding the entrances to the mixing chambers, i.e.,
swirler passageways 32. The pressurized discharge from the
compressor then is split into three annular flow-paths along
passageways 38, 40 and 43.
Air from the passageways 38 and 40 may enter the combustion chamber
21 to serve three functions. First, it may pass through relatively
small holes 46 which are oriented to cool the liners 18 and 20.
Second, it may enter relatively large holes 48 to penetrate the
combustion chamber and supply requisite, primary air for the
combustion process. Third, it may enter holes (not shown) further
downstream as dilution air to reduce the temperature of the hot gas
stream to a temperature compatible with the capabilities of the
materials forming the turbine. The air entering holes 48 may also
serve a dilution function.
Air entering the snout passageway 43 and chamber 44 is then metered
by and injected into the mixing chamber as discrete jets by the
swirler passageways 32. The vortical flow of mixing air is highly
effective in dispersing or mixing the fuel from the spray cone into
fine droplets which support a combustion process at a flame front
generally identified by the broken line in FIG. 2.
The flame front is primarily controlled by two factors, once
ignition is had. These are the presence and degree of a combustible
mixture and the velocity of that mixture. In accordance with the
present invention, these factors are taken into account in
maintaining a desired distance between the flame front and the
discharge end 29 of the fuel nozzle to minimize the temperature of
the latter.
To this end, a venturi tube 50 is disposed concentrically of the
nozzle axis a in a surrounding relationship with the spray cone
discharged by the nozzle. The inlet diameter of the venturi tube
approximates the mean diameter of the annular row of swirler
passageways 32. Thus approximately one-third of the swirler mixing
air is captured by and axially accelerated through the convergent
portion of the venturi tube 50. This creates a condition of where
the mixture, at the throat of the venturi, is sufficiently
over-stoichiometric as not to support combustion and the mixture
velocity is increased to further deter combustion. The divergent
portion of the venturi tube then re-expands the mixture to
approximately the original cone shape of the nozzle discharge. In
this connection, it will be noted that the divergent portion of the
venturi terminates at a generally tangent relationship with the
spray cone.
While maintaining the desired low smoke characteristics, the
venturi tube 50 is highly effective in maintaining the flame front
at a desired downstream distance. This distance can be controlled
as desired by the length of venturi tube and its contraction ratio
as well as the amount of mixing air flow therethrough, all of these
factors being balanced so that the spray cone angle is relatively
divergent as it discharges from the venturi tube into the
combustion chamber.
The effect of the venturi tube may be expressed in another fashion
in that it increases the total pressure in the core of the vortical
flow field created by the axial flow swirler. Without the venturi,
the low pressure of the vortical core would enable recirculating
primary air to flow forwardly, as indicated by the broken arrows,
and create a combustible mixture and flame front closely adjacent
the nozzle discharge. With the venturi such recirculation occurs,
as indicated by the solid arrows, but is more limited in the
magnitude of its upstream movement.
It will be noted that the venturi tube 50 is welded or otherwise
bonded to the swirler 28 intermediate the lengths of the
passageways 32. In so doing, added strength and rigidity is
obtained for the swirler.
FIG. 4 illustrates an embodiment of the invention wherein all of
the mixing air flows through a venturi tube 52 which also serves as
a mixing chamber for introducing the dispersed fuel mixture into
the combustion zone. The action of this venturi in obtaining a
desired downstream displacement of the flame front and a consequent
reduction in nozzle temperature is essentially the same as
previously described except that the velocity factor of the venturi
is more predominant in displacing the flame front since a greater
amount of air enters the venturi. In fact, the benefits of the
broader aspects of the present invention can be attained where the
amount of mixing air flow is sufficient to produce a combustible
mixture in the mixing chamber.
It has been demonstrated that the described use of a venturi is
highly effective in preventing carbon buildup on fuel nozzles and,
thus, assuring long maintenance-free operation. At the same time,
low smoke levels continue to be maintained.
While the invention has been described with reference to an annular
combustion system, it is equally applicable to a cannular system.
Further, in the broader aspects of the invention, the mixing air
could flow through the mixing chamber with little or no vortical
component. These and other variations in the described embodiments
will occur to those skilled in the art within the spirit and scope
of the present inventive concepts which are to be derived solely
from the appended claims.
* * * * *