CA2440597A1

CA2440597A1 - Discrete jet atomizer

Info

Publication number: CA2440597A1
Application number: CA002440597A
Authority: CA
Inventors: Chien-Pei Mao; John Earl Short
Original assignee: Delavan Inc
Current assignee: Collins Engine Nozzles Inc
Priority date: 2002-09-30
Filing date: 2003-09-11
Publication date: 2004-03-30
Also published as: JP4307942B2; US20040061001A1; AU2003243993B2; EP1402956A2; JP2004122124A; AU2003243993C1; EP1402956B1; EP1402956A3; DE60318287D1; AU2003243993A1; US6863228B2; DE60318287T2

Abstract

An atomizer including a fuel output portion shaped to provide a fuel output and an air swirler portion shaped to direct streams of air at the fuel. The air swirler portion includes an outer opening and an inner opening located radially inwardly relative to the outer opening. The inner and outer openings are arranged such that an air stream passed through the inner opening does not intersect a conical section defined by an air stream passed through the outer opening unless bout of said air streams are moving at least partially radially outwardly.

Description

Sent by: Thompson Hine 937 4438910; 08/27/03 2:57PM;JetFrx #19B;Page 4/27 Attorney Docket No. 015559-277 The present invention is directed to an atomizer, and more particularly, to an atomixer for creating a liquidlgas spray.
BACKGROUND
Liquid atomizers arc widely used in industrial, agricultural, propulsion and ether systems.
Such liquid atomizers are typically used to produce a spray (i.e., a Iiquidlgas mixture including fine droplets of the liquid) for various purposes, such as creating a spectrum of droplets, control or metering of liquid throughput, dispersion of liquid droplets for mixing with surrounding air, and generation of droplet velocity or penetration. In one embodiment, the transformation of bulk liquids to sprays can be achieved, far example, by directing various forms of energy, such as hydraulic, pneumatic, electrical, acoustical, or mechanical energy, to the bulk liquid to cause the liquid to break up into droplets.
Pneumatic atomizers are often used in gas turbine engine applications. Most pneumatic atomizers used in gas turbine engine applications include an atomizer tip which includes two components: a fuel swirler and an air swirler. The fuel swirler may receive a liquid in one end and eject or feed the liquid through an exit orifice, typically in a spiral motion, to generate a film or spray of liquid. The air swirler (such as a discrete jet air swirler) may direct pressurized air towards the outputted liquid such that the pressurized air impinges upon the liquid, breaks the liquid into a spectrum of droplets, and disperses the droplets.
In such pneumatic atomizers, the air streams are typically either high volume, low-pressure drop air streams, ar low volume, high-pressure drop air streams that are directed toward the bulk liquid to impinge upon, or shear against, the liquid film or spray.
The air streams directed toward or over the bulk liquid often includes a rotational component or a "swirl" motion a5 to enhance mixing and interaction with the liquid surface, as well as to improve dispersion of the liquid droplets. Thus, the air streams may be arranged and controlled to produce the desired distribution and uniformity of foal droplets, as well as the desired angle of the fluid droplets spray. In particular, in gas turbine applications, the atontezer preferably provides a fuel spray that allows the gas turbine to operate over a wide range of combustion limits over extended 3a periods of time with low acoustic noise and low emission pollutants.

Sent b : Them son Hine 937 4436910' 08!27/03 2:58PM
Y P , ;IetFsx #198;Page 5127 Attaraey pocket No. U15559-277 Air swirlers are often still designed by trial-and-error techniques, which involves much development effort and time to fine tune the design geometry or to achieve the desired spray characteristics. Furthermore, the air streams emerging from the air swirler may overlap and emss each other in the vicinity of the air sv~zrler, which results in energy loss, decreased spray control and narrow spray angles. 'When used in a gas turbine engine, such atomixers with crossing air streams may result in a relatively narrow range of combustion stability limits, excessive acoustic noise, and high levels of smalte at low power conditions.
Such atomizers may also exgerience carbon fornnation on the atomizer face and difficulty in high altitude re-light. Tn some prior art designs, the air streams are designed to cross to collapse the spray in an attempt to I U reduce smoke and alleviate the presence of hot spots on the liner walls.
Accordingly, there is a need for air swirlers and atomizers which are more efficient and effective, as well as a methodology for designing air swirlers and atomizers.
SL)MMARY
'The present invention may he an atomizer or air swirler which can provide favorable air streams, fuel sprays and fuellair mixtures. In use, such as in gas turbine engine applications, the air swirIers and atomizers may be energy efficient, and provide noise reduction, carbon alleviation, and improved ignition and combustion stability. The present invention may also include a methodology for designing air swirlers and atomizers.

2(1 1n one embodiment the invention is an atomizer including a fuel output portion shaped to provide an output of fuel and an air swirler portion shaped to direct streams of air at the output fuel. The air swirler portion includes at least one outer opening and at least one inner opening located radially iawardly relative to the outer opening. The inner and outer openings are arranged such that an air stream passed through the inner opening does not intersect a conical 2S section defined by an air stream passed through the outer opening unless both of said air streams are moving at leas! partially radially outwardly.
Other objects and advantages of the present invention will be apparent from the accompanying drawings and descriptions.

Sent by: Thompson Hine 937 4438910; OB/27i03 2:58PM;JerFax #198; Page B/27 Attorney Docket No. 015559-277 BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a side cross section of an air swirler illustrating the various geametries and coordinates of an air swirler with a single set of holes;
Fig. 2 is a side cross section of an air swirler with two sets of holes illustrating aix streams that do not cross;
Fig. 2a is a schematic three-dimensional representation of air flaw passed through the air swirler of Fig. 2;
Fig. 2b is a fi-ont view of the schematic representation of Fig. 2a;
Fig. 2c is a side cross section of the scherbatic representation of Fig. 2b, taken along lines 2c-2c;
Fig. 3 is a side cross section of an air swirler with two sets of halts illustrating air streams which merge downstream;
Fig. 4 is a side cross section of an air swirler with two sets of holes illustrating air streams which cross;
Fig. 5 is a side cross section of an atomizer system including a fool swirler and the air swirler of Big. 2;
Fig. 6 is a front view of the atomizer of Fig. 5;
Fig. 7 is a side cross section and front view of an atomizer including an alternate air swirIer;
Fig. 8 is a side cross section and front view of an atomi2er including another alternate air swirler; and Fig. 9 is a side cross section of an atomizer including two air swixlers and a pre-filming type fuel swirler device.
DETATLED D>;SC~T10N
Fig. 1 illustrates an air swirler 10 and a coordinate system and design parameters for determining the patterns of the air streams passing therethrough. The air swirler 10 of Fig. l includes a central axis 12 (the x axis of Fig. l ) and an axially-extending opening 14 centered about the central axis 12. The air swirler 10 includes a front face 1G and a set of radially spaced openings 18 extending from a back surface 20 of the air swirler 10 to the front face 16 thereof.
Each of the openings 18 may have a generally circular cross section and a central axis 19.

Sent by: Thompson Hine 937 4438910; 08/27/03 2:58PM;~ tFax ~198;Page 7/27 Attorney l7ocket No. 015559-277 However, the openings 18 may have different shapes besides circular, such as an "airfoil" or quadrilateral shape.
Each of the openings 18 is spaced apart from the central axis 12 of the sir swirler 10 at the front face 16 by a radial offset distance a. The central axis 19 of each of the openings 18 may form an angle with the central axis 12 of the sir swirltr 10 by an angle designated the angular offset 8, which may be an acute angle. Each of the openings 18 may be preferably aligned such that each of the openings 18 has an essentially identical value for a and 8. Each of the openings 18 may have an angle of inclination (not shown) such that air passed through each of the openings 18 has a velocity component that extends into and out of the page of Fig. 1 (see Fig.2a).
Whui compressed air is passed through the openings 18, illustrated as projected six streams 22, the air streams 22 follow a generally hyperbolic path. Figs. 1-2 and 3-9 illustrate the path of air streams (such as air streams 22 of Fig. 1 ) that are passed through the openings.
I-iowever, because each of the air streams may include velocity components in three dimensions, the air streams illustrated in each of Figs. 1-2 and 3-9 represent projections of the air stream. >~or example, as shown in Fig. 1, each of the sir streams 22 arc projected onto the x-y plane, and Fig.
6 illustrates the air streams 46 and 4$ projected onto the y-z plane.
As sbawn in Fig. 1, the projection of each ofthe air streams 22 on the x-y plane may have a predominantly axial velocity component, but also have a radial velocity component which is initially a radially inward velocity component when the air streams first exit the air swirler 10, and eventually transitions to a radially outward velocity component at a location termed the pinch point 24. Thus, the air streams 22 first converge inwardly towards the pinch point 24 that is typically located a short distance within the nozzle face 16 (i.e., about t3a or about ~ 10a.).
The air streams 22 then begin to diverge radially outwardly fmm the pinch point 24 to disperse 2S the droplets into a circular cross sxtional area. The exist distance from the front face 16 of the air swirler 10 to the pinch point 24 is designated by the dimension 1e.
rt should be understood that the pinch point 24 may be located inside the air swirler 10 (that is, the pinch point may be located to the left of the outer edgy of the front face 15 of Fig. I).
Yn this case, the dimension h may be designated to have a negative value.
However, the distance from the $ont face 16 is generally measured as a positive number; that is, h may represent the absolute value of the distance from the front face 16.

Sent by: Thompson Hine 937 4436910; 08/27103 2:59PM;JetFsx #198; Page 8/27 Attorney Docket No. 015559-277 The projection of the hyperbolic path of the air streams 22 includes a pair of asymptotes 26, each of which extends generally parallel to the central axis 19 of the openings 18 and intersect at the distance !t. A pair of lines 28 extend generally axially and are tangential to the hyperbolic air streams 22 at the pinch point 24. The dawnstream offset b is the axial distance S from the point of intersection of the asymptotes 26 (or from the pinch point 24) to the point where the asymptotes 26 intersect the line 28.
The path of the projection of the airstrearns 22 shown in Fig. 1 can be defined by the following hyperbolic equation:
Yz (x b)z =1 az - bz With reference to Fig. 1, it can be based upon simple trigonomotry that tats A
= a .
b Accordingly, with this equation in nuud, the paths or the projections of the paths ofthe air streams 22 can be platted and determined in advance by knowing the radial offset distance a, pinch point distance h and angular offset 0. The radial offset a may be desired to be set at a maximum distance allowed by the geometry of the swirler 10.
As shown in Figs. 2 a.nd 6, an air swirler 40 may include at least two sets of holes or openings 42, 44. As shown in Fig. 6, the air swirler 40 may include a set of outer openings 42 arranged in a generally circular configuration and a set of inner openings 44 arranged ixt a gerttrally circular configuration. The set of inner openings 44 may be generally concentric with the set of outer openings 42, with each set of openings 42, 44 being arranged around the central axis 12. The sat of inner openings 44 may be generally smaller than the set of outer opea~ings 42.
As shown in Fig. 5, the inner openings 44 cad projection of the inner flow paths 4$ may have the parameters a~, 81 and h1, and the outer openings 42 and projection of the outer flow paths 46 may have the parameters aZ, 8Z and hZ.
fig. 2a illustrates a three dimensional plot of the air swirler 40 of Fig. 2, arid the air streams 46, 48 passed therethrough, As can be seen, the air streams 46 are located in the profile of a tstree dimensional hyperbola 47, and the air streams 48 are located in the profile of a three dimensional hyperbola 49. In other words, hyperbola 47 (or 49) may be visualizod as a body of rotation defined by the projection of an air stream 46 (or 48) as rotated about the central axis 12.

Sent by: Thompson Hine 937 4438910; 08/27103 2:59PM;]etFaz #198; Page 9/27 Attorrtey pocket No. 015559-277 As shown in Figs. 2b and 2c, the individual streams of air 46, 48 cut through a vertical plane passing through the eGntral axis 12 (i.e., the plane defined by tine 2c-2c), As noted above, Fig. 2 includes a projection of the flow paths 46, 48 on the x-y place.
Thus, only openings 42', 44' (see Fig. 6), which are spaced apart from the central axis 12 by a distance of a2 and ai respectively, will truly have a angle of gland 9i projected upon the x-y plane.
The remaining openings 42, 44 will have lesser values of the angles B1 and 8i projected upon the x-y plax<e. Thus, the angular offset 9 may be defined as the maximum angle any one opening of a set of openings forms with a plane that passes through the central axis 12.
As shown in Fig. 5, the air swirler 40 of Fig. 2 may be used with a fuel swirler 50, such as a simplex injection tip, to create a discrete jet atomizer S2. The simplex injection tip 50 is a wall-known component which includes a fuel swirler cone 54 connected to a fuel delivery line 56, and a sealing ball 58 may be disposed in the fuel swirler cone 54. The simplex injection tip SO and fuel delivery line ~6 are received inside the opening 14 of the air swirler 40. In operation, liquid fuel in the fuel delivery line 56 is forced under pressure through a set of offset spin holes 1S 60 on the fuel cane 54 and into a h411ow swirl chamber b2 inside the fuel none 54. The spiral motion of the liquid fuel in the swirl chamber 62 induces the formation of an sir core inside the swirl chamber b2 toward the exit orifice 64 of the swixl chamber 62. Thus, as liquid fuel emerges from the orifice b4, liquid fuel spreads radially outwardly to form a conical film 66 in a well-known manner. The air streams passing through the air swirler 44 impinge upon the fuel spray cone 66 fa atomize the fuel spray b6 into droplets and disperse the droplets in the desired manner.
The air swirler 10 and atomizer 52 preferably are located and arranged such that there are no physical structures or components located in the vicinity of the air swirler such that the air streams 4b, 48 are free to follow their natural hyperbolic path. For example, in one embodiment, there are na physical structures or components located with a distance of at least about the radial offset distance a or about duee times or ten times the radial offset x in the downstream diroction.
Although the velocity of air flowing through the inner 44 and outer 42 set ofopenings tray be about the same, the lower volume air streams 48 passing through the inner set of holes 44 can provide initial atomization of the fuel and the atrongcr impact air streams 46 passing through ~0 the outer set of openings 42 may disperse and deliver the droplets to the desired areas. Thus, the atomized fuel droplets tend to follow the air streams 46, 48 along their flow paths, which deliver Sent by: Thompson Hine 937 4436910; 08127/03 2:59PM;J2t~x #198; Page 10!27 Attorney Dxket Na. 015559-277 the atomized fuel to the desired areas for mixing and combustion and the outer air streams 46 help to increase atomization and provide a more desired spray angle. Thus, in the embodiment shown in Fig. 2, the outer 46 and inner 48 air streams assist each other to provide an efficient atomization and droplet dispersion.
When air streams 46, 48 are passed through each of the openings 42, 44 (i.e., by passing compressed air through each of the openings 42, 44), it may be desired that the projectians of the air streams 46, 48 remain generally parallel or, at a minimum, do not intersect while in the vicinity of the front face 16. Fig, 4 illustrates a configuration in which the projections of the sir streams 46, 48 cross or intersect. In the configuration of Fig. 4, the prajectian of the air streams 48 of the inner sei of holes 44 intersects the projection of the air stxeam 4b of the outer sets of bolos 42 upstream of the pinch point of the air stream 46. The inner air streams 48 may have a wider angle than the outer air streams 46 and thus the air stream 46 may end up located inside the air stream 48.
When the air streams 46, 48 (ar their projections) cross over each other, as sbowu in Fig.
1 S 4, the energy and directed velocity of the intersecting streams 46, 48 is lost due to interference between the air streams 46, 48. Thus, in the configuration of Fig. 4, the flow path of the projected inner air streams 48 tends to cut through the projected outer sir streams 46 which results in a random and disturbed spray pattern. Furthermore, the crossing air streams 46, 48 may not be properly directed at the fuel spray 66 which redacts the air streams' effect upon the fuel spray 56, thereby reducing atomization of the bulk liquid. When used in gas turbine engine applications, sir swirlecs which have crossing air streams can lead to problems of altitude re-Iight, may provide a relatively narrow range of combustion stability limits, high levels of smoke at low power conditions, and increased acoustic noise.
Accordingly, it may be desired to provide an air swirler in which the air streams 46, 48 (or their proj ections) do not cross each othex. For example, the projections of the air streams 46, 48 in the embodiment of Fig. 2 remain somewhat parallel (or diverge slightly in the downstream direction) and do not cross. However, in some cases the flow configuration of Fig. 2 (i.e., fully non-overlapping, non-intersecting air streams} cannot be achieved due to physical limitations in the air swirler 40 or other atomizer components. Thus, as shown in Fig. 3, the air streams 46, 48 (or their projections) may also be allowed to merge sufficiently downstream to minimize disruption of the stable flow regime, Tn this embodiment the projections of the air streams 46, 48 Sent by: Thompson Hine 937 4438910; 08127/03 3:OOPM;IfltFax #198; Page 11/27 Attorney Docket No. 015559-277 merge together into a single air stream at a sufficient distance in the downstream direction, but not cross or intersect.
Tn this manner, an inner air stream 48 preferably does not intersect an outer air stream 46 (or the hyperbola or conical section 47 defined by one or more of the air streams 46), but if they do inters~t they do not inters~t unH! or unless both of the intersecting air streams 46, 48 are moving at least partially radially outwardly relative to the central axis 12.
The inner 44 and outer 4z openings may be arranged such that an inner air stream 48 (or its projection) does not intersect an outer air stream 46 (or its projection) within a distance of, far example, at least about three times the radial offset distance of the outer openings 42, or at least about ten times the radial offset distance of the outer openings 42. lit other words, the sir streams 46, 48 {or their projections) do not intersect, or if they do intersect, the air streams 46, 48 (or their projections) may both be moving at least partially outwardly relative to the central axis 12 when the streams 45, 48 (or their projections} do intersoct.
The atomizer may include morn than two sets of openings 42, 44. In this case, each of 1 S the sets of openings may be arranged so that the projections of the streams of air passed through each of the openings do not intersect in the same or similar manner discussed above.
In order to arrange the openings 42, 44 of the air swirler 10 such that the sir streams 46, 48 do trot cross, plots of the air streams 46, 4S based upon a given radial offset distance a, pinch point distance b and angular offset B can be calculated. The resultant hyperbolic curves for the air streams 46, 48 passing through the openings 42, 44 can then be plotted, and the designer can review the graphical plots or data to determine whether the air streams X46, 48 (or the 2-13 projections of the nit' streams 46, 4$) cross. If the air streams 46, 4B do cross (as in Fig. 4), then the various dimensions (a, h and A) can be modified until the desired result is achieved.
When the air swirler 40 of Figs. 2 and 3 (i.e., having non-intersecting projected air 2S streams 46, 48) is used as part of an atomizer in gas turbine engine application, the resultant atomizer may provide increased combustion stability limits, reduced acoustic noise, uniform spray and well-atomized droplet sizes, all of which produce a well mixed fuellait mixture favorable for high combustion efficiency and low emissions.
In this manner, an air swirler can be designed and constructed using methodology that allows the preview of the air stream patterns so that the designer can ensure the air swirler provides an efficient aerodynamic pattern to control liquid atomization, droplet dispersion, spray Sent by: Thompson Hine 937 443(39f0; 08/27103 3:OOPM;~tFax #198; Page 12/27 Attorney )docket No. 015559-277 pattern and flow structure. After the desired pattern of air stxeams is established, the dimensions a, h and 9 can be provided to a manufacturer so that the air swirler body can be constructed in the desired manner.
The air atomizer 40 can be used in combination with any of a wide variety of fuel swirlers or injectors to crease any of a wide variety of atomizers. For example, the air swirler 40 of the present invention can be used with a wide variety of fuel swirlets beyond simplex injection tips, including but not limited to simplex, duplex, dual orifice and annular prefilmiug atomizer tips, ar combinations thereof (such as piloted tips). Furthermore, the discrete jet atomizer 52, which is shown in Fig. S, can be modified to accommodate extended flow rate requirements equipped with dual fuel circuits. This type of discrete jet atomizer could be constructed by replacing the simplex injection tip 50 with either a duplex or a dual orifice injection tip that allows an extended flow rate control with higher fuel turndown ratio.
Furthermore, although the air swirter is illustrated as including a series ofdiscrete openings and air streams, the air swirler needs only to include a single or a pair of openings, such as a pair of generally annular openings which may or may not include vanes.
As noted above, it may be desired to arrange the air swirlcr such that air streams passed therethrough do not intersect. However, it may also be desired to arrange the sir swirler and fuel swiricr such that the air streams passed through the air swirler do not intersect or cross through the furl spray cone 66. In general, it is desired that the air streams be arranged to approach and then extxnd away from the fuel spray cone, although in some cases the innermost air streams may be desired to intersect the fuel spray cone to collapse the spray to contml the spray angle.
In some prior art air swirlers, the internal wall or components of the air swirler interferes with the air streams. Thus, in the embodiment of Fig. 7, the air swirter 10 includes s curved interior wall 70 which conforms to the trajectory of the projected air streams 72. More particularly, the interior wall 70 is preferably convex with respect to the central axis 12 of the air swirler 10 to ensure the air streams 72 pass smoothly over the wall 70. This curvilinear design of the inner surface 70 enables the atomizing air streams 72 to fully argage with the liquid fuel film b6 inside the air swirler 10 to form a premixed fuehair mixture. Although the air swirler of Fig.
7 includes only a single set of openings 44, multiple arrays or set of openings can be included in the sir swirler 10 of Fig. 7.

Sent by: Thompson Hine 937 4438910; OBf27103 3:OOPM;JetFsx #19B;Page 13!27 Attorney Docket No. 015s59-277 Fig. 8 illustrates another discrete jet swirler which includes a stopped interior vs~all 80 and two sets of openings 42, 44. The inner set of openings 44 are located on the inner (rearward) tier 82 and the outer set of openings 42 are located on the outer (forward) ties 84. In this manner, the sets of opetlings 42, 44 and corresponding pinch point locations 46h, 48h can be axially and radially spaced to al low the desired spray pattern to be produced. For example, the stepped wall 80 of the air swirIer 40 of Fig. 8 provides for flexibility in the location of the openings 42, 44 such that the openings 42, 44 can be located at the proper angle and radial position to produce the desired a1r pattern. Although Fig. 8 illustrates only two tiers 82, 84 and two sets of openings 42, 44, a greater number of tiers andlor sets of openings can be used.
The prnjcction of the air streams 48 passed through the inner openings 44 may have a pinch point 48h located inside the sir swirler 10 (i.e., spaced axially inwardly from the outermost portico $8 of the front face 16), and the projection of the air streams 46 passed through the outer openings 42 may have a pinch point ~16h located outside the body of the air swirler 10. The trajectories of the projections of the two air streams 46, 48 may be generally parallel to each other along the center axis l2 to keep the spray angle constant st varying conditions.
Fig. 9 illustrates another embodiment of the present invention which includes two air swirler components 90, 92 used with a fuel swirler 95 in the form of an annular prefilming injection device. The inner air swirler component 92 includes one set of opGtlings 94 which produces air streams 98, and tho outer air swirler 90 includes two conccatric sets of openings 96, 101. With the aid of the air swirler components 90, 92, the fool swirler 95 ejects a fuel spray 97 that is located between the air streams 98 of the inner air swirler component 92 and the air streams 100, 102 of the outer air swirler component 90.
The fuel swirler 95 of Fig. 9 may be a well-known prefihning fuel ejection device. In particular, the fuel swirler 95 may be coupled to a fuel delivery line 104 which delivers tiael through a winding passage 106 to one of a plurality of spin slots 108 and into an annular fuel gallery 110. The Fuel, which may have a spiral or swirl velocity is imparted to the fuel by the spin slots 108, then the fltel reaches a prefilmer area I 12 which allows the liquid film to attach as a film and prepare for uniform release in the circumferential direction. The inner air streams 98 thon impinge upon and attack the inner surface ofthe liquid film, and the outer air streams 100, 102 impinge upon and attack the outer surface of the liquid film to create the fuel spray 97, and disperse the fuel spray in the desired manner. Tn the embodiment of Fig. 9, in the same manner Sent by: Thompson Hine 937 4436910; 08/27/03 3:01PM;J~tFex #198; Page 14/27 Attorney Docket No. 015559-277 as discussed above, it may be desired that each of the air streams 98, 100, 102 not intersect, or that the air streams 98, 100, 142 merge together at a sufficient distance in the do~cvnstream direction.
Laving described the invemion in detail and by reference to the preferred embodiments, it will be apparent that modifications and variations thereof are possible without departing from tho scope of the inventiozr.
What is claimed is:

Claims

1. An atomizer comprising:

a fuel output portion shaped to provide an output of fuel; and an air swirler portion shaped to direct streams of air at said fuel, said air swirler portion including an outer opening and an inner opening located radially inwardly relative to said outer opening, said inner and outer openings being arranged such that an air stream passed through said inner opening does not intersect a conical section defined by an air stream passed through said outer opening unless both of said air streams are moving at least partially radially outwardly.

2. The atomizer of claim 1 wherein said inner and outer openings are arranged such that the air streams passed therethrough are initially directed at least partially radially inwardly.

3. The atomizer of claim 1 wherein said atomizer has a central axis, and wherein a central axis of each opening forms an acute angle with a central axis of said air swirler portion.

4. The atomizer of claim 3 wherein said fuel output portion is shaped to create a spray of fuel which travels in a downstream axial direction.

5. The atomizer of claim 1 wherein said air swirls portion includes a plurality of outer openings arranged in a configuration and a set of inner openings arranged in a configuration that is generally concentric with said set of outer openings.

6. The atomizer of claim 5 wherein said atomizer has a central axis and each of said inner and outer openings are each arranged in a generally circular pattern about said central axis, and wherein each opening of said inner and outer set of openings is radially spaced apart from any adjacent openings.

7. The atomizer of claim 1 wherein said fuel output portion includes an orifice through which fuel can be passed to create said fuel spray when fuel is passed therethrough.

8. The atomizer of claim 7 wherein said fuel output portion is shaped to create a generally conical fuel spray when fuel is passed therethrough.

9. The atomizer of claim 1 wherein said fuel output portion includes an simplex, duplex, dual orifice or annular pre-filming atomizer tip.

10. The atomizer of claim 1 wherein said atomizer includes an outer wall portion located adjacent to said opening, said outer wall portion being generally curved and having a convex portion which generally conforms to the path of an air stream passed through said outer opening.

11. The atomizer of claim 1 wherein said air swirler portion includes a generally stepped inner surface having an inner tier and an outer tier, and wherein said inner opening is located on said inner tier and said outer opening is located on said outer tier.

12. The atomizer of claim 1 wherein said outer opening is larger than said inner opening.

13. The atomizer of claim 1 wherein said atomizer lacks any physical structure which interferes with or blocks the flow of any air streams that passed through said openings.

14. The atomizer of claim 1 wherein said air streams passed through said openings follow a generally hyperbolic path for a distance of at least the radial offset of said outer set of openings.

15. An atomizer comprising:

a fuel output portion shaped to provide an output of fuel; and an air swirler portion shaped to direct streams of air at said fuel, said air swirler portion including an outer opening and an inner opening radially spaced apart from said a radial center of said atomizer by a radial offset distance, said inner and outer openings being arranged such that an air stream passed through one of said inner opening does not intersect a conical section defined by an air stream passed through one of said outer openings within an axial distance of at least about three times the radial offset distance measured from a front face of said atomizer.

16. An air swirler comprising:

a swirler body;

at least one set of outer openings located in said swirler body and arranged in a configuration; and at least one set of inner openings located in said swirler body and arranged in a configuration that is generally concentric with said set of outer openings, said inner and outer openings being arranged such that an air stream passed through one of said inner openings does not intersect an air stream passed through one of said outer openings when at least one of said air streams is moving at least partially inwardly.

17. An atomizer comprising:

a fuel swirler portion shaped to create a film of fuel when fuel is introduced therein; and an air swirler portion shaped to direct streams of air at said fuel film, said air swirler portion including a set of outer opening arranged in a configuration and a set of inner opening arranged in a configuration that is generally concentric with said set of outer openings, said inner and outer openings being arranged such that an air stream passed through one of said inner openings does not intersect an air stream passed through one of said outer openings unless both of said air streams are moving at least partially radially outwardly.

18. An atomizer comprising:

a fuel output portion shaped to provide an output of fuel; and an air swirler portion shaped to direct streams of air at said fuel, said air swirler portion including an outer opening and an inner opening located radially inwardly relative to said outer opening, said inner and outer openings being arranged such that the projection on a plane of an air stream passed through said inner opening does not intersect the projection on said plane of an air stream passed through said outer opening unless both of said air streams are moving at least partially radially outwardly.

19. A method for designing an air swirler having a body with a central axis, a front face, an inner opening and an outer opening comprising the steps of:

selecting a radial offset of each opening relative to said central axis;

selecting a pinch point distance for an air stream passed through each of said openings, said pinch point distance being located along said central axis and spaced from said front face;

selecting an angular offset of each of said openings relative to said central axis;
and using said radial offset, said pinch point and said angular offset to determine the path of air streams passing through said openings.

20. The method of claim 19 wherein said determining step includes determining the projection of the path of an air stream through each of said openings based upon a hyperbola equation.

21. The method of claim 24 wherein said hyperbola equation is wherein a represents the radial offset of said openings, h represents the pinch point, .theta. represents the angular offset of the openings, and b is a/(tan .theta.).

22. The method of claim 20 further comprising the step of repeating said selecting and determining steps to determine the path of air streams for a plurality of different values for said radial offset, pinch point and angular offset, and selecting selected ones of said values which provide a desired path of said air streams.

23. The method of claim 22 said selecting step includes selecting values for said radial offset, said pinch point and said angular offset such that an air stream passed through said inner opening does not intersect an air stream passed said outer opening unless said both of said intersecting air streams are moving at least partially outwardly relative to said central axis.