U.S. patent number 3,859,786 [Application Number 05/256,883] was granted by the patent office on 1975-01-14 for combustor.
This patent grant is currently assigned to Ford Motor Company. Invention is credited to Nicolas Alan Azelborn, Joseph Errante, Antoni Paluszny.
United States Patent |
3,859,786 |
Azelborn , et al. |
January 14, 1975 |
COMBUSTOR
Abstract
A three-chamber assembly is used for the control of combustion
in a gas turbine engine having a conventional supply of fuel and
compressed air. Uniform, homogeneous mixing, preferably on a
molecular level, takes place in a first chamber, combustion in the
second with restriction of the combustion flame thereto, and
quenching in the third chamber. Vortex flow is utilized in one or
more of the chambers. The combustion temperature is lowered without
sacrifice of combustion efficiency to provide control of
undesirable exhaust emissions.
Inventors: |
Azelborn; Nicolas Alan
(Ypsilanti, MI), Errante; Joseph (Dearborn, MI),
Paluszny; Antoni (Ann Arbor, MI) |
Assignee: |
Ford Motor Company (Dearborn,
MI)
|
Family
ID: |
22973991 |
Appl.
No.: |
05/256,883 |
Filed: |
May 25, 1972 |
Current U.S.
Class: |
60/737; 60/39.23;
60/753; 431/173; 60/748; 60/755; 431/353 |
Current CPC
Class: |
F23R
3/12 (20130101); F23R 3/007 (20130101); F23R
3/26 (20130101) |
Current International
Class: |
F23R
3/02 (20060101); F23R 3/00 (20060101); F23R
3/04 (20060101); F23R 3/26 (20060101); F23R
3/12 (20060101); F02c 007/22 (); F23d 011/44 ();
F23c 005/18 () |
Field of
Search: |
;60/39.65,39.71,39.74R,39.69,39.11 ;431/173,353 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Croyle; Carlton R.
Assistant Examiner: Garrett; Robert E.
Attorney, Agent or Firm: Malleck; Joseph W. Zerschling;
Keith L.
Claims
We claim as our invention:
1. A chamber assembly for use in a continuous combustion process
effective to provide low NO.sub.x emissions, comprising:
a mixing chamber having an inlet, an outlet and means interposed
between said inlet and outlet for directing a non-laminar
controlled turbulent flow of compressed air therethrough,
fuel supply means for continuously adding fuel to said flow in said
mixing chamber at a location adjacent to said inlet and at a rate
to provide for a substantially homogeneous gaseous air/fuel mixture
passing through said outlet,
a combustor chamber in communication with the outlet of said mixing
chamber for continuously passing said air/fuel mixture therethrough
and having a path for said mixture which is significantly longer
than the path of said mixture through said mixing chamber,
ignition means effective to ignite said mixture for sustained
flaming combustion in said combustor chamber,
means for tangentially introducing a flow of compressed air into
said combustion chamber for inducing vortical flow therein,
said induced vortical flow being effective to define an aerodynamic
orifice for effecting accelerated release of combustion products
from said combustor chamber, and
means for introducing a vortical flow of quenching medium into said
exhaust gases from said combustor chamber.
Description
BACKGROUND OF THE INVENTION
Continuing studies have indicated that nitrogen oxide emissions
from gas turbine engines remains relatively high if the temperature
of combustion is allowed to remain relatively high. However, the
same studies have shown that the expedient of reducing the
combustion temperature by limiting the fuel input rate undesirably
lowers overall combustion efficiency. Other efforts have been
solely directed at quickly reducing the temperature of generated
combustion products to inhibit nitrogen oxide, but have met with
only a limited degree of success. Accordingly, there is a need for
an improved chamber assembly which can maintain combustion
efficiency at a high level while at the same time reducing the
emission of nitrogen oxides to a negligible level.
Vortex combustor designs have been given serious consideration
because of the promise of increased combustion efficiency over a
wide range of operating conditions experienced in production
vehicles. Although the vortex combustor design is known, its
operating characteristics will be briefly reviewed to provide for a
full understanding of the improvements taught by the invention
herein. A typical vortex combustor has compressed air supplied in a
direction tangentially to a typical cylindrical chamber closed at
one end, the pressure energy being converted into a tangential
velocity as the body of gas swirls about the interior thereof
gradually decreasing its swirling radius. The gases finally flow
out through the open end near the axis of the swirling vortex. The
moving gases within the vortex chamber can be discriminated: a
natural vortex is generally disposed near the peripheral interior
area of the chamber where the components of the gaseous mixture,
such as fuel and air, experience a relative motion therebetween;
another vortex body, commonly referred to as "forced," occurs at
the axial region of the chamber and rotates like a solid gaseous
cylinder having no relative motion between the fuel and air. It is
known that the mixture within the forced vortex can be easily
ignited and produces a very stable rotating columnar flame.
The relative motion between the gaseous elements of the natural
vortex is both advantageous and disadvantageous. One of the more
important advantages is the inducement of greater mixing between
fuel and air promoting increased efficiency of combustion for which
the vortex combustor design is generally known. The mode of mixing
occurs because the tangential velocity distribution along the
radial direction takes a hyperbolic form. Thus any hypothetical
lump of gaseous fuel is subject to different shear forces at the
different radii of the lump and deforms into a stretched ligament
which ultimately atomizes into finer particles. This mode of mixing
is not present in the forced vortex because the tangential velocity
distribution is to the contrary and is linear. In a single vortex
chamber, the natural vortex begins to promote uniform homogeneity,
but cannot do so to satisfactory levels because of the momentary
time dwell of the mixture therethrough before being combusted.
One of the disadvantages of the vortex combustor is the inability
for the combustion flame to proceed smoothly from the forced vortex
into the natural vortex while remaining stable and totally within
the combustion chamber. This disadvantage can be overcome to some
degree by critically maintaining the air/fuel input ratio within a
very narrow range. This limitation prevents the vortex combustor
from achieving practical utility under its promise of higher
combustion efficiency. Accordingly, there is a need for overcoming
the deficiencies of a vortex combustor in such characteristics as
limited operating efficiency and need for further reduction of
nitrogen oxides without hindering its relatively trouble-free
construction.
As to mechanisms utilized by the art to lower per se the emission
content of combustion products, independent downstream quenching
has been used in the hopes that this alone would serve to prevent
the formation of undesirable nitrogen oxides. Although this has
helped to some limited degree, it has not totally solved the
fundamental problem of the initial formation of the nitrogen oxide
compounds.
SUMMARY OF THE INVENTION
To accommodate the problem of this invention, the invention has a
three-fold aspect wherein there is first a discovery that a more
homogeneous intimate mixture must be provided between the vaporized
fuel and air thereby preventing nonuniform combustion temperatures
from occurring within the combustion chamber, and particularly
pockets of combustion at elevated temperatures above 3,000.degree.F
which lead to immediate formation of nitrogen oxides. The
temperature of combustion is related to the air/fuel ratio within
the combustable mixture, and therefore, if the mixture is
nonuniform, the uncontrolled and undesirable portions of the
mixture will produce a high content of nitrogen oxide.
The second aspect or discovery is that the mixing capability of the
natural vortex within the combustion chamber is not sufficient by
itself to provide for the homogeneous uniform mixture required for
appropriate combustion, but that it can be used to augment and
complement this function while additionally serving to stabilize
the combustion flame and act as insurance that combustion will not
take place outside the preferred combustion zone.
Relatively restrictive exit orifices have been used with vortex
combustor chambers for the purpose of cooperating with the vortex
flow to provide stability. As a third aspect or discovery of this
invention, the size of the orifice has been found to be expandable
by controlling the strength of the natural vortex for promoting
combustor gas recirculation to sustain combustion and controlling
the downstream quenching medium in the form of a circulating vortex
which restricts the propagation of flaming combustion.
Construction features which implement the above inventive aspects
comprise the novel use of a three-chamber assembly for the
combustor unit, the first chamber providing for controlled
turbulence to intimately and homogeneously vaporize and mix fuel
and air, a second chamber for actual combustion utilizing the
vortex principle for additional controlled turbulence to insure
final atomization of the mixture, and a third chamber for quenching
also using controlled turbulence. The mixing chamber is constructed
with consideration not only to the dynamics of the flow therein but
also to the time dwell therein. Communicating means is constructed
between chambers so that flame propagation back into the mixing
chamber is prevented, as well as prevention of propagation into the
quenching chamber.
SUMMARY OF THE DRAWINGS
FIG. 1 is a central sectional view of a chamber assembly of this
invention showing also the fuel and air supply as well as the
ignition system.
FIG. 2 is a partial sectional view taken along line 2--2 of FIG. 1;
and
FIG. 3 is substantially a schematic illustration of an alternative
embodiment.
DETAILED DESCRIPTION
Referring to the drawings, the preferred embodiment of the chamber
assembly of this invention is illustrated in FIGS. 1 and 2 having a
plurality of chambers A, B, C interconnected, the most forward or
upstream chamber A providing for mixing of the charge elements, the
middle chamber B providing for combustion and lastly the exit
chamber C (which is ultimately connected to the turbine of the
engine) provides for cooling and general quenching of the
combustion products.
More particularly the mixing chamber A has a skirt portion 1 which
envelopes the combustion chamber B and a forward portion 2 which is
reduced in section or necked to define a central entry zone to the
mixing chamber. As best viewed in FIG. 2, the skirt portion is
defined by an outer sheet metal wall 3 spaced a radial distance 4
from a cylindrical sheet metal stamping 5 provided with flanges 6
extending from the edges 7 defining circumferentially spaced
openings 8 therein. The openings 8 constitute an outlet for the
mixing chamber and further cooperate as a specialized communicating
means to the combustion chamber as later described. As best viewed
in FIG. 1, a dish-shaped wall 9 extends across and is commensurate
with the left-hand opening of the sheet metal stamping 5; the
convex surface 10 of the wall serves as a diverter in regulating
the flow within the mixing chamber. The upstream end of the sheet
metal cylindrical wall 3 is reduced in diameter to define portion 2
and has an interior contour 11 effective to stimulate turbulence in
cooperation with other interior walls of the mixing chamber. The
necked portion is closed by member 12 having a central axial sleeve
13 (taken relative to the axis 14 of flow of the entire assembly)
through which a fuel injection nozzle 15 extends for introduction
of liquid fuel in droplet form or the equivalent. The nozzle is
supported by biased ring assembly 15a movable against a seat 13a of
the sleeve 13. An air inlet 16 is provided in said member 12 and is
defined by annular vaned assembly 16a surrounding the fuel
injection nozzle 15.
Turning now in particularity to the combustion chamber B, it is
comprised of a ceramic cylinder 17 having a smooth interior
cylindrical wall 18 with an axis aligned with the general axis 14
of the assembly; the upstream or left hand portion of the ceramic
cylinder is closed by dome wall 19 having a convex surface 19a
effective to cooperate with the vortical flow therein. A plurality
of openings or slots 20 are defined in the cylindrical wall 18 at
spaced circumferential positions and are generally aligned with the
axis of the chamber. Each opening 20 constitutes an inlet for the
combustor chamber and each has sidewalls 20a aligned with a chord
21 of the interior diameter of the chamber (best viewed in FIG. 2).
The interior surface 6a of flanges 6 carried by the previously
noted stamping 5 constitute extensions of the slot walls 20a
defining a communicating means d so D the gaseous mixture, being
introduced therethrough, is given a tangential velocity or guidance
within the combustor chamber promoting a swirling or vortex flow
pattern. The distance between walls of a single slot may occupy an
arc of approximately 10.degree. to 12.degree. and each slot is
preferably aligned at an angle of about 65.degree. relative to a
radius 22 of the chamber. Slots 20 have a longitudinal extent
substantially commensurate with the length of the combustor
chamber. The combustor chamber has a single outlet 23 defined by an
annular wall 23a projecting inwardly from the interior wall 18 in a
general direction perpendicular to the axis 14. The central
circular opening 24 in the wall 23a defined by edge 23b a control
orifice whereby gaseous elements can be compressed and then rapidly
expanded upon passage through the orifice, such flow control
accelerating the particles of the gaseous mixtures so that there is
a release from the combustor chamber at a velocity above that which
would allow the flame to follow.
Although the interior configuration of the quenching chamber C can
take a variety of forms, including a generally flared
configuration, the preferred embodiment utilizes a cylindrical wall
25 formed integrally as a ceramic extension of cylinder 17 and has
a diameter somewhat larger than the interior diameter of the
combustion chamber. Wall 25 is smoothly connected with the annular
wall 23a (defining said orifice) by an interior shoulder 26. The
entire ceramic unit constituting the combustor and exhaust chambers
is supported in an outer housing 28 which also serves to define a
flow passage 29 for secondary air received from a common compressor
source 30 which enters the housing at locations in the upstream
portion of the housing to provide also for primary air. The
incoming air is divided between the inlet 16 to the mixing chamber
and the passage 29. In passage 29, air passes along between the
sheet metal cylindrical wall 3 and housing 28 to enter through
inlet 31 having a plurality of openings 31a circumferentially
arranged about and in the wall 25 of the exhaust chamber and
thereby defining a communicating means E in conjunction with outlet
23. To vary the division of compressed air flowing between the
inlet 16 to the mixing chamber and inlet 31 to the exhaust chamber,
a variable control mechanism 33 may be employed which varies the
size of the openings 31a. A suitable mechanism here comprises a
slidable sleeve 34 actuated by elements 35 for movement along the
axis 14 of the unit.
In operation, air (compressed to approximately four atmospheres and
having a temperature of approximately 1,000.degree.F) is conveyed
to the housing 28 of the combustor unit. Such compressed air
divides preferentially between inlet 16 and passage 29, that
entering inlet 16 is immediately guided into a toroidal swirl
resulting from conversion of the pressure energy into a tangential
velocity component creating a controlled turbulent flow pattern
with flow impinging against the interior surfaces 10 and 11 of the
mixing chamber. The secondary division of the air supply moves
along the interior of housing 28 and enters the exhaust chamber by
way of circumferentially arranged inlet openings 31a.
In the primary air flow of the mixing chamber, liquid fuel is
disbursed by the fuel nozzle 15 and is quickly vaporized and
stimulated to mix on a molecular level, being afforded a sufficient
time dwell to accomplish improved diffusion of the atomic elements
of air into the atomic elements of the vaporized fuel. The time
dwell is promoted by having the flow path between the inlet 16 and
outlet 8 of an irregular non-laminar character whereby flow is not
only turbulent but tortuous to promote homogeneity. Upon passing
through the communicating means D into the combustion chamber, the
intimate mixture of fuel and air achieves further homogeneity and
ultimately attains desired uniformity by supplementary making of
the natural vortex within the combustor chamber B.
In conventional gas turbine systems the air/fuel ratio, at the
point of combustion, is approximately 15:1 when supporting optimum
combustion efficiency. This invention contemplates maintaining
air/fuel ratios on the order of 40:1 (and in some practical
applications about 44:1) in a substantially uniform homogeneous
condition throughout the entire mixture ultimately combusted.
Experiments have shown that very peak combustion efficiency of a
vortex combustor is attained at air/fuel ratios between 25:1 and
30:1. However, this invention optimizes emission control of
nitrogen oxides by use of a higher but limited air/fuel ratio to
maintain the combustion temperature at a level at or below
2,800.degree.F and preferably about 2,000.degree.F. This is
accomplished with only a slight drop in efficiency from that
obtained at the peak ratios between 25:1 and 30:1.
With the intimate homogeneous mixture and improved air/fuel ratio,
the combustion flame will appear as a glow throughout the entire
combustor chamber when ignited by suitable ignition means, here
shown as an ignitor element F disposed near the interior periphery
of the combustor chamber. Propagation of the flame back through the
communicating means D is prevented by controlling the flow of
gaseous mixture so that it is at a higher rate than the back
propagation rate of the flame. Such flow can be varied to attain
this objective by regulating the division between primary and
secondary flow as mentioned earlier.
Similarily the orifice defined by the outlet 23 from the combustor
chamber functions to compress and expand the combustion products so
as to accelerate the particles thereof in a manner to release and
exit from the chamber at a velocity considerably higher than the
propagation rate of the flame within combustor chamber and such
constriction secondarily serves to guide and stimulate the
formation of the natural vortex, again supporting supplementary
mixing within the combustor chamber.
To illustrate the equivalence to which the inventive features
should be entitled, an alternative embodiment is illustrated in
FIG. 3 wherein the internal flow within the mixing chamber provides
an "aerodynamic" dome for the combustor chamber which lacks a
positive mechanical wall at the conventional end where a dome wall
normally occurs. The aerodynamic dome is created by the formation
of the very strong vortical flow within the mixing chamber. This
can be obtained by providing the necked portion 36 of the mixing
chamber A with a plurality of inlet ports 37 which provide a
tangential component to the entering primary air substantially
throughout a greater area than that obtained with the swirl vanes
of the preferred embodiment. This particular design increases the
degree of turbulence in chamber A and provides a more direct flow
path into the combustor chamber B thereby eliminating possibilities
of super heated sheet metal elements. Ignition can be accomplished
by an element 46 disposed centrally in chamber A, but combustion is
restricted to chamber B by controlling of primary air in excess of
the rate of back propagation of the flame.
Instead of using primary air for stimulating the vortex flow
pattern in the combustor chamber B, secondary air is employed
passing along the exterior of the ceramic unit 41 (defining all the
chambers) and housing 28. Secondary air is introduced by a
plurality of circular openings 38 in the outer wall 39 of the
combustor chamber B. The flow through openings 38 serves to
stimulate and maintain a vortex flow comparable in lesser degree to
that contained in the preferred embodiment, keeping in mind that
the primary flow enters at 42 with a previously imparted vortical
flow pattern.
In the embodiment of FIG. 3, the mechanical orifice controlling the
release of combustion products in the combustor chamber is
eliminated and the flow pattern of the combustor vortex is utilized
as a "aerodynamic" orifice 43 or control whereby gaseous products
of combustion are released only upon having entered the forced
vortex region 40 of the combustor chamber and are accelerated to
leave at a velocity in excess of that flame propagation. The
aerodynamic orifice 43 can be implemented by tangentially directing
a strong secondary air flow through slots 44 adjacent the orifice
43 location.
Although not shown, a third flow of secondary air can be utilized
for quenching purposes downstream from orifice 43 of the combustion
region B and can be introduced through slot openings 45 creating a
swirl therein.
* * * * *