U.S. patent number 3,886,728 [Application Number 05/465,754] was granted by the patent office on 1975-06-03 for combustor prechamber.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Ronald E. Quinn.
United States Patent |
3,886,728 |
Quinn |
June 3, 1975 |
Combustor prechamber
Abstract
A combustion liner for a gas turbine combustion apparatus has a
prechamber for mixing of fuel and combustion air. Air enters the
prechamber with a radially outward and tangential flow through a
cylindrical swirler. The swirler is movable axially to reduce its
axial length and thus the effective area of the swirler to control
the primary air flow into the prechamber and on into the reaction
zone of the combustion liner. Fuel is scoured off the outer wall of
the prechamber and preferably vaporized by the air flowing with
swirling movement from the air inlet to the reaction zone.
Inventors: |
Quinn; Ronald E. (Indianapolis,
IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
23849034 |
Appl.
No.: |
05/465,754 |
Filed: |
May 1, 1974 |
Current U.S.
Class: |
60/39.23; 60/737;
60/743; 60/748 |
Current CPC
Class: |
F23R
3/30 (20130101); F23R 3/26 (20130101); F23R
3/14 (20130101); F05B 2250/41 (20130101) |
Current International
Class: |
F23R
3/14 (20060101); F23R 3/02 (20060101); F23R
3/30 (20060101); F23R 3/04 (20060101); F23R
3/26 (20060101); F02c 003/00 (); F02c 007/22 () |
Field of
Search: |
;60/39.23,39.65,39.71,39.74R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Husar; C. J.
Assistant Examiner: Garrett; Robert E.
Attorney, Agent or Firm: Fitzpatrick; Paul
Claims
I claim:
1. A combustion liner for a gas turbine combustion apparatus or the
like comprising a wall extending from an upstream end to a
downstream end of the liner defining, in flow sequence, a
prechamber, a reaction zone, a dilution zone, and an outlet for
combustion products, the prechamber wall having a substantially
circular cross section; means for delivering fuel to the inner
surface of the prechamber wall; means defining an annular radial
outflow air inlet at the upstream end of the prechamber, the air
inlet extending circumferentially and axially of the prechamber
upstream of the fuel delivering means; an air swirling and
throttling cylinder disposed across the said air inlet movable
axially of the prechamber, the cylinder bearing a set of swirl
vanes adapted to direct the air outwardly and circumferentially
from the inlet into the prechamber, the area of the set of swirl
vanes being variable by axial movement of the cylinder to vary
primary air flow into the liner.
2. A combustion liner for a gas turbine combustion apparatus or the
like comprising a wall extending from an upstream end to a
downstream end of the liner defining, in flow sequence, a
prechamber, a reaction zone, a dilution zone, and an outlet for
combustion products, the prechamber wall having a substantially
circular cross section; means for delivering fuel to the inner
surface of the prechamber wall; means defining an annular radial
outflow air inlet at the upstream end of the prechamber; a
centerbody defining with the prechamber wall an annular flow path
leading from the inlet to the reaction zone; the air inlet
extending circumferentially and axially of the prechamber upstream
of the fuel delivering means and centerbody; an air swirling and
throttling cylinder disposed across the said air inlet movable
axially of the prechamber, the cylinder bearing a set of swirl
vanes adapted to direct the air outwardly and circumferentially
from the inlet into the prechamber, the area of the set of swirl
vanes being variable by axial movement of the cylinder to vary
primary air flow into the liner.
3. A combustion liner for a gas turbine combustion apparatus or the
like comprising a wall extending from an upstream end to a
downstream end of the liner defining, in flow sequence, a
prechamber, a reaction zone, a dilution zone, and an outlet for
combustion products, the prechamber wall having a substantially
circular cross section; means for delivering fuel to the inner
surface of the prechamber wall; means defining an annular radial
outflow air inlet at the upstream end of the prechamber; the
prechamber wall being divergent at the air inlet and convergent
through the downstream portion of the flow path; the air inlet
extending circumferentially and axially of the prechamber upstream
of the fuel delivering means; an air swirling and throttling
cylinder disposed across the said air inlet movable axially of the
prechamber, the cylinder bearing a set of swirl vanes adapted to
direct the air outwardly and circumferentially from the inlet into
the prechamber, the area of the set of swirl vanes being variable
by axial movement of the cylinder to vary primary air flow into the
liner.
4. A combustion liner for a gas turbine combustion apparatus or the
like comprising a wall extending from an upstream end to a
downstream end of the liner defining, in flow sequence, a
prechamber, a reaction zone, a dilution zone, and an outlet for
combustion products, the prechamber wall having a substantially
circular cross section; means for delivering fuel to the inner
surface of the prechamber wall; means defining an annular radial
outflow air inlet at the upstream end of the prechamber; a
centerbody defining with the prechamber wall an annular flow path
leading from the inlet to the reaction zone, the prechamber wall
being divergent at the air inlet and convergent through the
downstream portion of the flow path; the air inlet extending
circumferentially and axially of the prechamber upstream of the
fuel delivering means and centerbody; an air swirling and
throttling cylinder movable axially of the prechamber guided on the
prechamber wall and the centerbody, the cylinder bearing a set of
swirl vanes adapted to direct the air outwardly and
circumferentially from the inlet into the prechamber, the area of
the set of swirl vanes being variable by axial movement of the
cylinder to vary primary air flow into the liner.
Description
My invention is directed to combustion apparatus for liquid fuel,
particularly those used at relatively high pressures and rates of
flow as compared to ordinary fuel burners supplied with air at
substantially atmospheric pressure. Examples of such pressurized
combustion apparatuses are found in gas turbine engines. In such
engines, it is desirable in many cases to improve combustion so as
to minimize the discharge of carbon, unburned hydrocarbons, carbon
monoxide, and nitrogen oxides. One helpful technique in reducing
emissions is thorough mixing of the fuel with air and evaporation
of the liquid fuel prior to its entry into the reaction zone of the
apparatus where combustion takes place.
Particularly where the energy rate output of the combustor varies
over a considerable range, it may be necessary to control the air
flow so as to maintain a desired fuel-air ratio in the reaction
zone. This fuel-air ratio is commonly referred to as the
equivalence ratio, which is the quotient of the actual fuel-air
ratio divided by the stoichiometric fuel-air ratio. Prevaporization
of fuel facilitates clean and complete burning with relatively low
equivalence ratios which are conducive to low formation of nitrogen
oxides.
My invention is directed to a prechamber type of combustor, and
particularly to the prechamber itself. To summarize the principles
of my invention briefly, air is admitted to an annular prechamber
through a swirler which delivers the air outwardly and
circumferentially so that the air swirls along and scours the inner
surface of the outer wall of the prechamber. This wall converges
toward the outlet of the prechamber. At a point near its greatest
diameter and downstream of the swirler, fuel is put on the wall to
be picked off by the air flow and evaporated as it flows into the
combustion chamber. The swirler is of a type having a constant
cross section but of variable length so that the area for entrance
of primary air may be varied in accordance with operating
conditions which determine the required amount of fuel. In this
way, the equivalence ratio in the reaction zone of the combustor
may be varied as desired.
The principal objects of my invention are to improve combustion of
liquid fuels, to provide an improved prechamber for combustion
apparatus, and to provide a prechamber having variable air flow but
substantially constant flow characteristics as flow is varied. A
further object is to provide a prechamber having an annular air
entrance with a variable-area radial outflow air swirler disposed
in the entrance.
The nature of my invention and its advantages will be apparent to
those skilled in the art from the succeeding detailed description
of the preferred embodiment of the invention.
FIG. 1 is an axial sectional view, with parts broken away, of a
combustion liner including a prechamber embodying the
invention.
FIG. 2 is an enlarged cross sectional view of the prechamber taken
on the broken surface indicated by the line 2--2 in FIG. 1.
Referring to FIG. 1, a combustion liner 2 may be installed in an
engine housing or combustion chamber outer case (not illustrated)
to which air is supplied under pressure for combustion of fuel. Air
may be supplied in the usual manner by a compressor and may be
heated in a regenerator. Such an installation may be similar to
that described in Collman, et al., U.S. Pat. No. 3,267,674, Aug.
23, 1966.
Fuel fed to the combustion chamber is burned in the air thus
supplied and the resulting combustion products are directed to a
user, such as the turbine of a gas turbine engine. Preferably, and
as illustrated, the combustion liner is of circular cross section.
A liner wall 3 defines in flow sequence from the upstream end of
the liner a prechamber 4, a reaction or combustion zone 6, a
dilution zone 7, and an outlet 8 for combustion products. All
except the prechamber may be of known structure. The liner is shown
broken away, and in practice the length will be greater than
illustrated. Air enters the dilution zone 7 for mixing with and
cooling of the combustion products through dilution or secondary
air ports 10 in wall 3.
The prechamber wall 11 is of a divergent-convergent configuration,
beginning at the extreme upstream end with a guiding flange 12 from
which extends a flaring wall portion 14, followed by a converging
wall portion 15 which terminates at a radial wall portion 16
defining the upstream end of the reaction zone. The entrance to the
reaction zone is through a circular opening 18 in the radial wall
portion 16. Opening 18 is preferably of slightly smaller diameter
than the downstream end of the prechamber to provide an annular
baffle.
A support 19, which also serves as a pilot fuel tube, is fixedly
connected to the liner wall 3 by suitable structure of the
combustion apparatus, not illustrated. It is coaxial with the
prechamber. Struts 20, at least three in number, fixed to tube 19
extend outwardly to support a centerbody 22 which defines the inner
boundary of an annular flow path through the prechamber. The
downstream end of the centerbody converges to an opening 23. A
pilot fuel nozzle 24 suitably mounted on the end of tubular support
19 contains suitable spray mechanism of known type to discharge a
small quantity of fuel in a conical spray through the opening 18
into the reaction zone 6. This fuel is for maintenance of flame
under low power conditions, or for starting the engine.
The forward portion of centerbody 22 constitutes a cylindrical
guide 26. Guiding flange 12 and guide 26 provide support for an air
swirling cylinder 27. This cylinder comprises a downstream ring 28
slidable on the exterior of guide 26 and an upstream ring 30
slidable on the inner surface of guiding flange 12. An annular row
or set of radial outflow swirl vanes 31 extends between the rings
28 and 30. These vanes may be brazed or otherwise fixed to the
rings, the mode of construction of the swirler being immaterial to
the present invention. As is clear from FIG. 2, these vanes are of
such shape as to deliver air radially outwardly and with a
considerable circumferential component of motion into the
prechamber. The ring 30 may be integral with a spider 32 including
arms 34 and a hub 35. Hub 35 is slidably guided on the support 19.
As illustrated in FIG. 2, support 19 defines a conduit 36 for
carrying fuel to the pilot nozzle 24. Support 19, which is fixed to
centerbody 22, may be considered to be part of the centerbody.
The air swirling cylinder 27 is illustrated in the extreme
position, to provide maximum opening of the swirler and airflow. It
may be moved to the left as illustrated in FIG. 1, with ring 30
sliding in flange 12 and ring 28 sliding on guide 26, whereupon the
space between ring 28 and the chamber wall portion 14 lessens to
reduce air flow. Means for reciprocating the swirler is indicated
by a rod 38 fixed to the spider 32.
The main fuel supply is conducted to the prechamber by a fuel line
39 which enters a ring manifold 40 of semi-circular cross section
brazed or otherwise fixed sealingly to the outer surface of the
prechamber wall 11. Fuel supplied to the manifold, ordinarily at a
pressure only slightly higher than that of the air in the
prechamber, is delivered to the interior surface of the prechamber
walls through a ring of small ports 42, which may be directed
somewhat tangentially and somewhat downstream relative to the axis
of the prechamber.
In operation of the combustion apparatus, the air under pressure
surrounding the liner 2 flows through spider 32 and swirl vanes 31
into the prechamber 4, where it picks up the fuel supplied through
ports 42. The air swirls downstream with the fuel through the
annular flow path 44 defined between wall 15 and centerbody 22. The
air, which is heated by compression and ordinarily by regeneration
from the engine exhaust, evaporates the fuel and delivers it
through the opening 18 into the reaction zone. Combustion may take
place as is customary in prechamber combustors, the mixture of air
and evaporating fuel burning readily without local hot spots such
as would be due to combustion around fuel droplets in a fuel spray.
The structure of the combustion and dilution zones of the liner is
not explained in detail, since it may be conventional. The hot
combustion products from the reaction zone 6 are mixed with
additional air delivered from the same source as the combustion
air, this dilution air being supplied through ports 10 and mixing
as it flows from the liner through outlet 8 to a user. For starting
the engine or maintaining the flame, a small amount of fuel may be
delivered by the pilot nozzle 24.
With a fixed area for entrance of primary combustion air, the
equivalence ratio varies undesirably with changes in the operating
level of a combustor which accompany changes in power level of the
engine in which it is used. To reduce the amount of primary
combustion air, the swirling cylinder 27 may be moved leftward as
illustrated in FIG. 1 from the position shown to throttle the air
flow as desired.
It will be clear that this provides a means for throttling the air
flow without changing the effective direction of flow or disturbing
its natural tendency to scour the outer wall of the prechamber. The
radially outward swirling flow enhances this scouring tendency, and
also tends to centrifuge any unevaporated oil droplets toward the
outer wall 14, 15.
The detailed description of the preferred embodiment of the
invention for the purpose of explaining the principles thereof is
not to be considered as limiting or restricting the invention,
since many modifications may be made by the exercise of skill in
the art.
* * * * *