U.S. patent number 3,668,869 [Application Number 05/110,424] was granted by the patent office on 1972-06-13 for fuel spray ignition atomizer nozzle.
This patent grant is currently assigned to Westinghouse Electric Corporation. Invention is credited to Serafino M. De Corso, Chester A. Jersey.
United States Patent |
3,668,869 |
De Corso , et al. |
June 13, 1972 |
FUEL SPRAY IGNITION ATOMIZER NOZZLE
Abstract
A liquid fuel spray atomizer nozzle for use with a gas turbine
during combustion chamber fuel ignition, comprising a member having
a high pressure air blast passageway for directing a stream of air,
angularly in relation to the direction of fuel spray from a nozzle
into the combustion chamber, so as to atomize and forcibly blow at
least a part of the fuel toward an ignition device into ignition
proximity therewith. The air blast can be blown directly across the
fuel spray pattern or may be directed toward a side of the spray
pattern. In all cases, the air must be under sufficient pressure to
deflect and atomize the fuel spray sufficiently to provide for its
ignition by the spark gap or other igniter.
Inventors: |
De Corso; Serafino M. (Media,
PA), Jersey; Chester A. (Wallingford, PA) |
Assignee: |
Westinghouse Electric
Corporation (Pittsburgh, PA)
|
Family
ID: |
22332933 |
Appl.
No.: |
05/110,424 |
Filed: |
January 28, 1971 |
Current U.S.
Class: |
60/740; 60/200.1;
239/418; 60/776; 239/295; 239/433 |
Current CPC
Class: |
F23R
3/28 (20130101) |
Current International
Class: |
F23Q
1/06 (20060101); F23Q 1/00 (20060101); F02g
001/00 () |
Field of
Search: |
;239/290,292,295,300,418,433,102 ;60/39.74,39.82S |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Wood, Jr.; M. Henson
Assistant Examiner: Grant; Edwin D.
Claims
The invention claimed is:
1. Combustion apparatus for a gas turbine, comprising
a combustion chamber,
a liquid fuel spray atomizer nozzle for atomizing liquid fuel
sprayed into said combustion chamber,
said spray nozzle having a body defining a spraying orifice,
said body having fuel passage means for directing the liquid fuel
through said orifice in a substantially hollow conical spray
pattern at atmospheric pressure,
a fuel ignition device, and
means for providing an air blast directed at said fuel spray
pattern from only one side thereof for atomizing at least a part of
the liquid fuel forming said spray pattern and directing at least a
part thereof into igniting proximity with said ignition device.
2. Combustion apparatus as defined in claim 1 wherein said air
blast means includes means for controlling the operation
thereof.
3. Combustion apparatus as defined in claim 2 wherein said
controlling means is operative to render said air blast means
operative during starting ignition of fuel in the combustion
chamber and for rendering it otherwise inoperative.
4. Combustion apparatus as defined in claim 1 wherein said air
blast means comprises a member having therein an air passageway
with a blast orifice and constructed and arranged to direct an air
blast to engage at least a part of said fuel spray pattern and to
atomize the same and deflect at least a part of the atomized spray
toward said ignition device into igniting proximity therewith.
5. Combustion apparatus as defined in claim 4 wherein said air
blast passageway is constructed and arranged to direct an air blast
directly at and across the conical fuel spray pattern toward said
ignition device.
6. Combustion apparatus as defined in claim 4 wherein said air
blast passageway orifice is closely adjacent to said spray nozzle
orifice and said passageway is arranged to direct the air blast
angularly in the general fuel spray direction and across the
same.
7. Combustion apparatus as defined in claim 4 wherein said air
blast passageway is constructed and arranged to direct an air blast
angularly in the general fuel spray direction and so as to engage a
side of said conical spray pattern and atomize and deflect at least
part of the atomized fuel spray toward said ignition device.
8. Combustion apparatus as defined in claim 4 wherein the air blast
passageway has an input throat and a diverging mouth of larger
cross-sectional flow area than said throat forming said blast
orifice and providing for rapid expansion of air at the orifice and
a spreading of the air blast.
9. Combustion apparatus as defined in claim 4 including means for
supplying air to said air blast means at a pressure to provide
substantially sonic air velocity at the input to said air blast
passageway.
10. Combustion apparatus as defined in claim 9 wherein the air
blast passageway has an input throat and a diverging mouth forming
said air blast orifice,
said diverging mouth being formed to provide a critical air
pressure drop therethrough with a change in air pressure to about
0.53 of the air pressure in the input throat and a resultant
supersonic air velocity at the air blast orifice.
Description
BACKGROUND OF THE INVENTION
This invention relates to gas turbine combustion chamber liquid
fuel supply atomization and ignition during a starting
operation.
In the past, it has been found that air atomization of a liquid
fuel spray assists in assuring reliable starting of gas turbine
combustion chambers. This has been done by directing a plurality of
air blasts with the conventional conical liquid fuel spray pattern.
The use of this type prior system requires a costly air compressor
to supply the required air.
SUMMARY OF THE INVENTION
The present invention provides a simplified efficient liquid fuel
spray atomizer nozzle for use in a gas turbine combustion chamber
during starting by providing a single air blast stream which is
directed at a part of the fuel spray so as to deflect it toward the
igniter into igniting proximity therewith and concurrently
atomizing it to assist the ready ignition thereof. The air blast
may be blown directly across the fuel spray pattern or may be aimed
to deflect a part from a side of the spray. This is conveniently
done by providing a member with an air blast passageway having an
orifice adjacent to the fuel spray nozzle orifice and extending
angularly so as to direct the air blast in the desired direction.
The air blast passageway also preferably is made with an initial
throat which flares outwardly to the blast orifice in the form of a
diverging mouth to provide for rapid expansion of the high pressure
air at the orifice and a spreading of the air blast. Further, the
air preferably is supplied at a pressure high enough to provide
substantially sonic air velocity at the input throat, and the mouth
flare is such as to reduce the orifice pressure to about 0.53 of
the input pressure and result in a supersonic air velocity at the
orifice.
The limited amount of air required for this air blast can readily
be supplied from a suitable storage tank of relatively small size
which can be pumped up to the needed pressure between starts by the
existing conventional air compressor. It has been found that even
if a separate air compressor is provided, it can be reduced in size
to about an eighth that required by the prior art.
The foregoing and other advantages and features of novelty of this
invention will be apparent from the following description referring
to the accompany drawing.
BRIEF DESCRIPTION OF THE FIGURES OF THE DRAWING
In the drawing:
FIG. 1 is an axial sectional view of part of a gas turbine
combustion chamber provided with one embodiment of a liquid fuel
spray atomizer nozzle according to this invention;
FIG. 2 is an elevational end view of another embodiment of the
spray atomizer member according to this invention;
FIG. 3 is a fragmentary sectional view along line 3-3 of the
atomizing member shown in FIG. 2; and
FIG. 4 is a fragmentary sectional view through the air blast
passageway in an atomizing member, on a fuel nozzle, showing
details of the passage geometry to provide the maximum atomizing
effect.
DETAILED DESCRIPTION OF THE INVENTION
Referring to the drawing, FIG. 1 illustrates the upstream end of a
gas turbine combustion chamber 10 provided with a liquid fuel spray
nozzle 11 incorporating the present invention. The combustion
chamber is only partially shown as it may comprise any suitable
type for generating hot pressurized products of combustion for
operating a gas turbine (not shown).
The illustrated combustion chamber 10 is of the cannister type and
includes a tubular body 12 with an upstream end wall 13 to which a
suitable nozzle-mounting wall 14 is secured by suitable detachable
means, such as bolts 15. The chamber body 12 is formed with a
plurality of axially and circumferentially spaced apertures 16 for
the passage of compressed air into the combustion chamber from the
surrounding space in a suitable conventional plenum chamber, not
shown. The liquid fuel spray nozzle 11 is supplied with fuel under
pressure from a suitable source, not shown, through a conduit 17
connected to a fuel inlet passage 18 in a nozzle body 19. The
pressurized liquid fuel is adapted to be sprayed by the nozzle 11
into the combustion chamber in a pattern which is a substantially
hollow conical fuel spray pattern 20 at atmospheric pressure;
however, since the combustion chamber is under pressure, both when
starting up, due to the compressed air therein, and during normal
operation, due to the additional pressure of the combustion gases
formed therein, the full wide angle conical spray pattern 20 tends
to contract to a narrower conical spray angle. Any suitable fuel
directing structure can be used to provide the desired conical
spray pattern, and, in FIG. 1, includes a small throat 21 connected
to and forming the inner end portion of the fuel passage 18 and
terminates in an outwardly flaring mouth 22 which defines the
spraying orifice of the nozzle.
It has been found that if the liquid fuel spray is finely atomized,
it will ignite much more readily in intiating combustion in the
combustion chamber. In addition, the normal spray angle pattern 20
does not spray fuel near enough to an igniter, such as a spark plug
23, to allow ignition of the fuel. According to this invention, a
simplified and efficient atomizing of some of the fuel during
starting and deflecting of at least a portion thereof into igniting
proximity with the igniter 23 is provided by directing a single air
blast at very high, preferably supersonic, velocity at a part of
the fuel spray pattern 20 so as to atomize and blow it in the
desired direction. In the FIG. 1 embodiment, this is conveniently
done by providing a jet of high velocity air through an atomizing
orifice 24 in a face plate 25 having an air-tight seat on the inner
end of the nozzle body 19.
The desired supply of air for the atomizing air jet and a rigid
air-tight assembly of the nozzle structure may readily be provided
by forming the face plate 25 with a central frusto-conical seat 26
snugly fitted over a complementary frusto-conical face 27 on the
inner end of the nozzle body 19 around the spraying orifice 22, and
providing an enclosing air supply means for rigidly securing these
in air-tight relationship. In the FIG. 1 structure, this is
obtained by press fitting or otherwise suitably mounting a sleeve
28 around the nozzle body 19 and providing an air-tight seat of
this sleeve 28 with a flange 29 on the nozzle body 19. This sleeve
28 is mounted in a central aperture in the mounting wall 14 and is
secured in position in any suitable manner, as by bolts 30
extending through a sleeve flange 31 and the wall 14. The face
plate is drawn onto its air-tight seat with the nozzle body by an
enclosing cap 32. In this embodiment, the cap is formed with an
inwardly extending lip 33 which engages a complementary
circumferentially extending flange 34 on the outer edge of the face
plate 25, and has a threaded engagement 35 with the adjacent end of
the sleeve 28. The sleeve 28 is made shorter than the length of the
nozzle body from the flange 29 to the conical face 27, thereby
providing a space 36 between the end of the sleeve 28 and the
adjacent side of the face plate 25, whereby tightening of the cap
32 threaded engagement 35 on the sleeve 28 draws the complete
nozzle assembly into a rigid air-tight unit.
Air is supplied to the atomizing orifice 24 from a suitable source,
such as a small tank 37, through a conduit 38-39 and a control
valve 40. The conduit is connected to a passageway 41 in the sleeve
28, which passageway 41 opens into the space 36 between the end of
the sleeve and the face plate 25.
In order to provide the desired air blast deflection of part of the
liquid fuel from the conical fuel spray pattern 20 toward the
igniter 23, the face plate 25 is formed with a passageway 42
extending substantially radially therethrough and at an angle
between the faces thereof so as to direct an air blast from the
orifice 24 angularly in the general fuel spray direction directly
at and across the conical fuel spray pattern 20 toward the igniter
23. This air blast operation is controlled by the valve 40, and is
made operative by opening the valve during the starting ignition of
fuel in the combustion chamber, whereby part of the fuel pattern is
atomized and at least a part 43 thereof is deflected to igniting
proximity with the igniter 23. After the fuel has ignited, the
valve 40 is closed, rendering the air blast atomizer inoperative.
Thus, only a relatively small amount of air is required for a short
time to provide this efficient ignition atomization and deflection
of the fuel, and the small air storage pressure tank 37 can be
pumped up between starts by the conventional air compressor or, if
need be, by a relatively small auxiliary compressor. If desired,
the valve 40 may be a suitable conventional electromagnetic type
valve, which may be energized to open position when the igniter 23
is energized and deenergized to closed position at other times to
thereby provide the desired air blast control.
FIGS. 2 and 3 illustrate another embodiment of the present
invention in a modified air blast nozzle atomizer structure.
Similar parts are indicated by the same reference numbers as in
FIG. 1. In this embodiment, the general nozzle structure may be the
same as in FIG. 1, wherein the nozzle body 19 terminates in a
frusto-conical face 27 around an outwardly flared mouth 22 forming
the fuel spray orifice connected to the fuel supply passage throat
21. The face plate 25 is mounted on the nozzle in the same manner
as in FIG. 1 and is provided with an air blast passageway 50
between the faces thereof so as to direct an air blast angularly in
the general fuel spray direction, but instead of being directed
across the fuel spray pattern, it has an orifice 51 directed to
engage a side of the conical spray pattern, whereby the air blast
will deflect a part of the fuel spray toward the igniter 23 and
concurrently atomize this deflected spray. In some cases, this
almost tangential spray deflection blast may be advantageous
because of the pressures involved or because of the relative
placements of certain parts, such as the igniter 23.
FIG. 4 illustrates another embodiment of the nozzle atomizer
structure which may be incorporated in either the FIG. 1 or the
FIGS. 2 and 3 type atomizer face plates. Similar parts are
identified by the same reference numbers as in the other figures.
The additional feature in this embodiment over the previously
described nozzles is the geometry of the atomizing passageway 59 in
the face plate 25, the remainder of the structure being the same as
that previously described.
In all embodiments, it is desirable that the pressure of the air at
the intake to the face plate atomizing passageway be sufficient to
give the air entering the passageway about sonic velocity in order
for it to produce the desired results. The FIG. 4 passageway 59 is
formed with an intake throat 60 of relatively small cross-sectional
area into which the air passes at about sonic velocity under the
correct pressure. This passageway throat opens abruptly into a
diverging mouth 61 of much larger cross-sectional area to the
atomizing air blast orifice 62, so proportioned that the rapid
expansion of the air therethrough provides for a drop of the
orifice air pressure to about 0.53 of the air pressure in the input
throat 60. This provides a critical pressure drop which produces a
supersonic air velocity at the air blast orifice 62, which has been
found to improve greatly the fuel atomizing effect of the blast and
also provides a broadening of the air jet with a consequent
improvement in the efficiency of the starting ignition of the
fuel.
While particular embodiments of this invention have been
illustrated and described, many modifications thereof will occur to
those skilled in the art. It is to be understood, therefore, that
the invention is not to be limited to the exact details disclosed
but only as required by the prior art.
* * * * *