U.S. patent number 3,912,164 [Application Number 05/483,517] was granted by the patent office on 1975-10-14 for method of liquid fuel injection, and to air blast atomizers.
This patent grant is currently assigned to Parker-Hannifin Corporation. Invention is credited to Arthur Henry Lefebvre, Eric Roy Norster.
United States Patent |
3,912,164 |
Lefebvre , et al. |
October 14, 1975 |
Method of liquid fuel injection, and to air blast atomizers
Abstract
An airblast atomozier which spreads liquid fuel into a
continuous thin sheet, and exposes both sides of the sheet to the
atomizing action of high velocity non-swirling air. The atomizer
then injects the atomized fuel into a region of high turbulence and
high shear formed by the meeting of two contra-rotating swirling
air flows and in which region combustion occurs. This region is
spaced from the atomizer a sufficient distance to permit full
atomization of the fuel before it reaches such region. Also, the
downstream end of the atomizer has no large transverse surfaces so
exposed to the combustion process that significant deposits of
combustion products can accumulate thereon.
Inventors: |
Lefebvre; Arthur Henry
(Bedford, EN), Norster; Eric Roy (Bedford,
EN) |
Assignee: |
Parker-Hannifin Corporation
(Cleveland, OH)
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Family
ID: |
27560863 |
Appl.
No.: |
05/483,517 |
Filed: |
June 27, 1974 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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295956 |
Oct 10, 1972 |
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216495 |
Jan 10, 1972 |
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Foreign Application Priority Data
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Jan 11, 1971 [GB] |
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1315/71 |
Jan 11, 1972 [CA] |
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132132 |
Jan 11, 1972 [DT] |
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2201033 |
Jan 11, 1972 [FR] |
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72.857 |
Jan 11, 1972 [JA] |
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47-4992 |
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Current U.S.
Class: |
239/5; 60/743;
60/748; 239/8; 239/400; 239/406 |
Current CPC
Class: |
F23R
3/14 (20130101); F23D 11/12 (20130101) |
Current International
Class: |
F23D
11/10 (20060101); F23D 11/12 (20060101); F23R
3/14 (20060101); F23R 3/04 (20060101); B05B
007/00 () |
Field of
Search: |
;239/8,400,5,404-406,419.3 ;60/39.74R ;261/DIG.25 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Love; John J.
Attorney, Agent or Firm: Brisebois & Kruger
Parent Case Text
This is a continuation of application Ser. No. 295,956, filed Oct.
10, 1972, now abandoned which application was itself a
continuation-in-part of application Ser. No. 216,495, filed Jan.
10, 1972, now abandoned the priority of which applications is
hereby claimed.
Claims
The embodiments of the invention in which an exclusive property or
privilege is claimed are defined as follows:
1. A method of liquid fuel injection which comprises the steps
of:
spreading said fuel into a continuous thin sheet,
exposing both sides of said sheet to substantially non-rotating
high velocity air flows which atomize said sheet into a layer of
atomized fuel in a first region, and
injecting said layer of atomized fuel into a second region of high
turbulence and high shear formed by the meeting of two
contra-rotating swirling air flows emanating from opposite sides of
said fuel layer downstream of said first region.
2. The method claimed in claim 1 in which the sheet of fuel is
symmetrical about a longitudinal axis and annular in section.
3. The method claimed in claim 2 in which one of said high velocity
air flows is projected inside said sheet and the other outside,
while one of said swirling air flows is projected inside the
innermost high velocity air flow the outermost high velocity air
flow, said high velocity air flows being projected to converge on
said sheet in a first zone and said swirling air flows being
projected to converge on said atomized fuel in a second zone
downstream of said first zone.
4. The method claimed in claim 3 in which said swirling and high
velocity air flows are kept separate from each other during a
portion of their path of travel.
5. An air blast atomizer for carrying out the method of claim 1
which comprises:
means for projecting a thin sheet of fuel encircling a longitudinal
axis extending in the direction in which said fuel is
projected,
means for providing high velocity substantially non-rotating air
flows to both surfaces of said sheet to atomize said sheet into a
layer of atomized fuel in a first region of said atomizer, and
means for providing swirling air flows having components of
movement in opposite directions about said axis, one of which air
flows impinges on one side and the other of which air flows
impinges on the other side of said atomized sheet in a second
region of said atomizer downstream of said first region.
6. An air blast atomizer as claimed in claim 5 comprising a fuel
feed arm provided with a central support, in which said means for
providing high velocity air comprises concentric air ducts carried
by said arm, the means for providing swirling air comprises swirler
means for imparting a swirling motion to the innermost air in the
innermost of said air ducts and to the outermost air in the
outermost of said air ducts, and said means for projecting fuel
comprises fuel duct means around said innermost air duct but inside
said outermost air duct which is connected to supply fuel to the
outermost part of said innermost air duct.
7. An air blast atomizer as claimed in claim 6 in which said air
ducts converge and an atomizing lip is formed at the point of
convergence of said ducts.
8. An air blast atomizer for carrying out the method of claim 1
which comprises:
an inner air swirler for swirling air in one direction,
a fuel atomizer member concentric therewith for forming fuel into a
continuous thin sheet,
means for providing high velocity substantially non-rotating air
flows to both sides of said sheet to atomize said sheet into a
layer of atomized fuel, and
an outer air swirler concentric with said inner air swirler and
oriented to swirl air in a direction contra to said one direction,
said inner and outer air swirlers being positioned to provide air
flows on opposite sides of said atomized fuel layer.
9. An atomizer according to claim 8, wherein said swirlers and said
atomizer member are formed as a structural assembly carried by a
fuel feed arm having a bore for supplying fuel to the atomizer
member.
10. An atomizer according to claim 9, wherein a plurality of axial
passageways convey fuel from the bore to an annular gallery formed
between an extension piece of a main body and a prefilmer
concentric therewith and wherein air is conveyed to a lip of said
atomizer member through two annular passages, one formed between
the prefilmer and the inner swirler, and the other formed between
the prefilmer and the outer swirler.
11. An atomizer according to claim 10, wherein a nut retains the
prefilmer on the main body.
12. An atomizer according to claim 10, wherein the main body has an
air passage and a center member is mounted in the air passage to
form an annular inner air passage to convey air to the inner
swirler and to the atomizing lip.
13. An atomizer according to claim 10, wherein the main body and a
center member are mounted on vane means to form an inner air
passage to convey air to the inner swirler and to the atomizing
lip.
14. An atomizer according to claim 10, wherein the main body has an
additional bore passing through its center and leading to a pilot
spray nozzle whereby fuel can be fed axially through the main body
to the pilot spray nozzle.
15. An atomizer according to claim 14, wherein the spray nozzle
comprises a number of components that are retained in position by a
nut that retains the inner air swirler on the main body, and
wherein a small portion of the air flowing through the inner air
passage passes through an anti-carbon air gallery to the face of
the spray nozzle.
Description
The present invention relates to methods and apparatus of fuel
injection for liquid fuelled combustion systems, whereby fuel can
be atomized and premixed with air before entering the combustion
zone, and in particular is applicable to airblast atomizers in gas
turbine engines.
In most gas turbine engines fuel is injected into the combustion
chamber by means of a pressure atomizer in which fuel is forced
under pressure through a small orifice from which it emerges as a
multitude of high velocity, atomized fuel droplets. Another method
of fuel injection is by means of an airblast atomizer, which is a
device in which liquid fuel is shattered into droplets by the
action of high velocity air. This air then enters the combustion
zone carrying the atomized fuel along with it.
Airblast atomizers have advantages over pressure atomizers in that,
because the fuel droplets are completely airborne, their
distribution throughout the combustion zone is dictated by an air
flow pattern which remains fairly constant under all operating
conditions. In consequence, the distribution of temperature in the
chamber exhaust gases also tends to remain constant, thereby
extending the life of the turbine blades. Other advantages include
the avoidance of high fuel pump pressures and, because the fuel
enters the combustion zone atomized and premixed with air, the
ensuing combustion is characterized by a blue flame of
low-luminosity, resulting in fairly cool flame-tube walls and a
minimum of exhaust smoke.
Many designs of gas turbine combustion chambers incorporate a
device known as an air swirler which is located at the upstream end
of the flame tube. The primary function of this swirler, referred
to hereinafter as the outer swirler, is to admit air to the flame
tube in a manner and direction calculated to promote a stable flow
recirculation of the air and combustion products in the primary
combustion zone.
Now it is well established that very high burning rates are
achieved when atomized fuel is injected into regions of high
turbulence and high shear. One object of the invention is to create
such a region of high turbulence and high shear through the use of
an additional or inner air swirler. This swirler produces a
swirling airstream which lies initially inside of, and concentric
with, the airstream issuing from the outer swirler, but whose swirl
component is in the opposite direction to that of the outer
swirler. The atomizer is so designed that the contra-rotating inner
and outer airstreams meet to form such region of high turbulence
and high shear at a region spaced from the downstream end of the
nozzle. Means are provided for forming the fuel into a thin
continuous sheet which is then atomized by the action of high
velocity non-swirling air acting on both sides of the sheet. The
fuel so atomized is then injected into the region of high
turbulence where it is burned in a very efficient manner.
Non-swirling air for achieving atomization of the fuel sheet is
directed to both sides of the fuel sheet through annular passages
separated from the inner and outer swirl passages.
The invention is based on the results of tests that have shown:
a. Atomization is best when the fuel is spread into a thin
continuous sheet and exposed to high velocity non-swirling air on
both sides.
b. Premixing of atomized fuel and air prior to combustion produces
a clean, soot-free flame of low luninosity.
c. High rates of combustion are achieved when the atomized fuel is
injected into the region of high turbulence and high shear formed
at the interface of two-contra rotating swirling air flows.
This invention comprises both the method of injecting the fuel and
the apparatus for achieving such method.
In order that the inventions may be more readily understood,
reference will now be made to the accompanying drawings which show
the application of the invention to gas turbine engines, and in
which:
FIG. 1 shows an axial section through a first embodiment of fuel
injector,
FIG. 2 shows a cross-section through the injector of FIG. 1, along
the line II--II thereof, and
FIG. 3 shows an axial section through a second embodiment of fuel
injector.
Referring now to the drawings, one embodiment of fuel injector is
shown in FIGS. 1 and 2, and comprises as a structural assembly, an
inner air swirler and concentric with it, an airblast atomizer unit
and an outer air swirler. The assembly is carried by a fuel feed
arm 1 having a bore 2 for supplying fuel to the airblast atomizer.
A number of axial passageways 3 convey fuel from the bore 2 to an
annular gallery 4 formed between an extension piece 5 of a main
body 6 and a concentric prefilmer 7 located in a spigot 8 and
retained by a nut 9. Air is conveyed to an atomizing lip 10 through
a small annular passage 12 formed between the prefilmer 7 and the
outer swirler 11. The nut 9 also retains a fuel sealing washer 13
between the main body 6 and the prefilmer spigot face 14. At the
discharge end of the annular fuel gallery 4 tangential swirl ports
15 machined into the extension piece 5 contact a shoulder 16 on the
prefilmer, and in so doing form a discharge passage for the fuel.
An inner divergent wall 17 of the prefilmer conveys the discharged
swirling fuel uniformly in a thin continuous sheet to the air
atomizing lip 10. The inner wall 18 of the main body of the
atomizer and a centre member 19 are mounted on three equispaced
vanes 20 to form an inner air passage 21 which conveys air to the
inner swirler 22 and non-swirling air to the air atomizing lip 10.
The forward end face of extension piece 5 is recessed to form a
radially inwardly extending shoulder adjacent the bottoms of ports
15 to prevent flow of fuel axially along inner wall 18, as is known
in the art.
The inner air swirler body 23 is retained on a conical centre boss
24 by the action of retaining screw 25. The inner swirler shroud
piece 26 separates the swirling air passing through the inner air
swirler 22 and nonswirling air passing through passage 40 between
shroud 26 and wall 17 to lip 10. The swirling liquid fuel leaves
tip 10 as a sheet, as indicated by solid line 41, and is acted upon
on its outer surface by non-swirling air issuing through passage 12
and on its inside surface by non-swirling air passing through
passage 40. This non-swirling air atomizes the liquid fuel, as
indicated by broken lines 42, and such atomization is substantially
complete by the time the fuel reaches region 43 where the inner and
outer swirling airstream from swirlers 22 and 11 meet. Because
these latter airstreams are rotating in opposite directions there
is high turbulence and shear force at region 43 and highly
efficient combustion occurs thereat.
The downstream parts of the nozzle exposed to the flame, namely
shroud 26, lip 10 and swirlers 22, 11, have thin transverse
surfaces and thus there are no large transverse surfaces exposed to
the flame upon which soot deposits and carbon build up can occur.
Screw 25 is spaced a sufficient distance from combustion region 43
so that it is not subject to excessive carbon deposit thereon.
The airblast atomizing and air flow arrangement of FIG. 1 is
particularly advantageous when used in conjunction with a pilot
fuel injector, for example of the kind shown in British
Specification No. 1,031,184 and illustrated in FIG. 3. Like parts
of FIGS. 1 and 3 are referred to by like reference numerals. Thus,
the combined fuel injector is carried by a feed arm 1 having bores
2 and 27 for supplying fuel to the airblast atomizer and pilot
spray nozzle respectively. An extension of the bore 27 passes
through the main body 6 and support vanes 20 such that fuel can be
fed axially through the centre body 19 to a pilot spray nozzle 28.
The spray nozzle includes component pieces 28, 29 and 30 which are
retained in position by a retaining nut 31 which carries the inner
air swirler 22. In this case, swirler 22 includes an inner annular
shell 34 that has several radially inwardly extending struts 35
about its inner circumference to space shell 34 from nut 31. A
small portion of the air flowing through the inner air passage 21
passes through anti-carbon air passages 32 to the face of the spray
nozzle 28.
At low fuel flows all the fuel passes through the pilot spray
nozzle 28 and air for combustion is provided through the inner
swirler whose geometry is designed primarily for optimum combustion
of pilot fuel. At high fuel flows most of the fuel flows through
the airblast atomizing system as described earlier.
* * * * *