referring to fig3 a and 3c , there is shown an illustrative embodiment of an axial - type , conical swirler 10 with aerodynamic turning slots 18 in accordance with a first embodiment of the present invention . although the following description describes a conical or cone - shaped swirler , the invention is not to be limited thereto as the principles taught work also for disk - shaped and dome - shaped swirler blanks ( not shown ). the manufactured conical swirler 10 begins as a swirler blank 11 on which a specific slot pattern is formed . the slot pattern consists of a plurality of turning vanes 22 and a corresponding plurality of turning slots 18 that separates each pair of adjacent turning vanes 22 . although fig3 a and 3c show eight turning vanes 22 and eight corresponding turning slots 18 , the invention is not to be so limited as the swirler 10 can include fewer or more than eight slots 18 and vanes 22 . fig3 a and 3c also show that the dimensions of the slots 18 and the vanes 22 are generally of the same magnitude . the invention , however , is not to be so limited as , for example , the width of the turning vanes 22 could be two , three or more times as wide as the width of the turning slots 18 without deviating from the scope and spirit of this disclosure . the dimensions of the swirler 10 must be compatible with the dimensions of the corresponding fuel injector or dome combustor for which they are manufactured . typically , the length or thickness of a manufactured swirler 10 can range from about 0 . 200 inch to about 0 . 400 inch , the outer diameter of the swirler 10 can range from about 0 . 500 inch to about 1 . 500 inch , and the inner diameter radius of the swirler 10 can range from about 0 . 100 inch to about 0 . 800 inch . generally , when used with a fuel injector or dome combustor , the swirler 10 is disposed between an air cap and a heat shield . the swirler 10 should fit tightly between the air cap and the heat shield so that the walls of the turning vanes 22 and the inner surfaces of the air cap and the heat shield define the boundaries of an airflow channel through which compressed gas can travel and be subject to swirl . the axial , conical swirler 10 shown in fig3 a and 3c includes turning vanes 22 and turning slots that provide inner slot angles φ i and outer slot angles φ o that are acute angles , or less than 90 degrees . this configuration provides greater swirl strength and , moreover , directs the compressed gas radially inward towards the central axis of the conical swirler 10 . when the radially - inward spiraling compressed gas reaches the downstream end of the swirler 10 , the high turbulence gas wants to expand radially outward as it is encountering a fuel spray . the shear force breaks apart the liquid film into fine droplets and the outward expansion disperses the atomized droplets of fuel over a wider area . as a result , when the atomized droplets of fuel enter the combustion chamber ( not shown ) the resulting combustion can be quicker , more powerful and cleaner . this embodiment of the subject invention provides uniform fuel distribution , lower pressure drop across the nozzle and improved efficiency . referring now to fig5 a to 5 c , there is shown an alternate illustrative embodiment of an axial conical swirler 10 with straight - edged , aerodynamic turning slots 22 in accordance with the present invention . the conical swirler 10 in fig5 a to 5 c is substantially identical to the conical swirler 10 in fig3 a and 3c except that the turning slots 22 are linear or substantially linear , rather than curved . this orientation is likely to produce less swirl strength than is the case with non - linear or curved turning slots 22 . because of the linear or straight slots , this embodiment of the swirler provides lower machining time , and more efficient design and manufacture , as compared to those with curved turning slots . referring to fig7 a and 7b , there is shown an illustrative embodiment of a radial - type conical swirler 24 in accordance with the present invention . preferably , the configuration of the embodied radial swirler 24 can be used with a combustor dome to provide a significant reduction in manufacturing costs without compromising swirl performance . the embodied radial - type conical swirler 24 includes a plurality of intake openings 25 that are disposed on the outer perimeter of the swirler 24 rather than at the base of the axial conical swirlers 10 as previously described . although fig7 a and 7b show eight intake openings 25 and eight corresponding turning vanes , the invention is not to be so limited as the swirler 24 can include fewer or more than eight intake openings 25 and turning vanes . the intake openings 25 shown illustratively provide a non - linear , or curved , airflow path through a corresponding plurality of turning passages 26 . the invention , however , is not to be so limited as the intake openings 25 can also be linear without deviating from the scope and spirit of this disclosure . as the incoming airflow enters the intake openings 25 of the conical swirler 24 from a substantially radial direction , the airflow follows the orientation of the intake opening radially inward through the aerodynamic turning passages 26 . subsequently , the radial - inward moving airflow is turned , or deflected , towards an axial or substantially axial direction by a deflector wall 27 . having described several embodiments of axial - and radial - type conical swirlers , preferred methods of manufacturing a plurality of conical air swirlers will now be described . although throughout this discussion , the blanks will be referred to as “ cone - shaped ”, the invention is not to be so limited as the air swirler blanks can also be disk - shaped or dome - shaped . the first step in the manufacturing process is to provide a plurality of cone shape blanks 11 for further machining . a side elevation view of an illustrative embodiment of a cone shape swirler blank 11 is shown in fig3 b . the swirler blank 11 includes an interior surface 12 and an exterior surface 14 . the interior and exterior surfaces 12 and 14 of the swirler blank 11 are not necessarily parallel to each other , but , preferably , provide a generally conical shape . a flat surface 16 on the swirler blank 11 is prepared for the upstream openings of the turning slots 18 . flat surface 16 generally is structured and oriented in a direction normal or substantially normal to the incoming fluid flows . however , in another aspect of the present invention , the flat surface could be structured and oriented with a slight inclination angle . the second manufacturing step is to determine the two - dimensional slot pattern that is to be provided on the swirler blank 11 . fig3 a and 3c , respectively , provide frontal plan and perspective views of a slot pattern 18 that will be constructed on the swirler blank 11 to form the desired flow passages . the illustrative slot pattern 18 contains eight aerodynamic turning contours that closely resemble a pinwheel . although , the illustrative slot pattern 18 includes eight slots and eight corresponding turning vanes , the number of slots 18 and turning vanes 22 can be more than or less than eight and the pattern can be varied . the slot pattern 18 determines the performance of the conical swirler 10 . therefore , it is important that some of the key parameters be identified for design consideration . referring to fig4 , important slot parameters include inner offset distance r i , outer offset distance r o , inner radius r i , outer radius r o , inner slot angle φ i , outer slot angle φ o , and throttle gap ab . depending on the slot 18 contours and shapes , these parameters are interrelated and influence swirler performance to a different extent . for example , offset distance appears to have a strong effect on swirl strength of the fluid flow . specifically , the higher the offset distance , the higher is the swirl strength . however , a smaller inner radius r i tends to reduce swirl strength and , moreover , provides a narrower spray angle . contrary to what one would expect , a smaller throttling gap ab does not necessarily translate into smaller effective flow area for the swirler 10 because the contour shape and the swirl strength associated with the slots 18 also contribute to flow area . generally , an aerodynamically shaped slot pattern 18 provides higher turning efficiency than a straight slot pattern 18 . using the above guidelines and parameters , one skilled in the art can configure the two - dimensional cutting pattern in many different ways to meet a wide range of swirler and flow field requirements . for example , fig5 a to 5 c provide views of a second illustrative embodiment of a simple slot pattern 18 that employs turning vanes 22 with straight cutting edges . this straight - edged configuration is easy to manufacture and swirler performance is not compromised . in a third step , once the slot pattern 18 is determined , material within the contoured slots 18 of the swirler blank 11 can be removed . the new conical swirlers 10 could be manufactured by a number of different machining techniques , including conventional cnc milling , casting , laser milling , photochemical etching , and any combination of these techniques . preferably , material is removed from the swirler blank 11 using an edm machine and edm processing , which machines and processing techniques are well known to those skilled in the art . briefly , wire edm processing utilizes sparks between an electrically conductive work piece , i . e ., the swirler blank 11 , and an electrode ( not shown ). a dielectric liquid , e . g ., deionized water and oil , separates the work piece and the electrode and serves to flush away the resulting debris . the sparks occur at a very high temperature , which melts and evaporates a tiny amount of the work piece . using thin wire electrodes , the edm process can provide high quality , high precision parts without the restrictions inherent to the other machining processes . in this manner , material can be remove to form inlet openings 20 and the curved turning vanes 22 . wire edm processing offers many distinct advantages for making the new conical swirlers 10 . it is ideal to produce complex curved shapes , allowing the designers to configure the slot geometry in many different ways for various applications . furthermore , it is capable of handling exotic materials , including heat - treated , hardened , and tough to machine stainless steels and alloys . the wire edm process can easily hold down to ± 0 . 001 inch tolerances and tighter . usually the accuracy and consistency can be maintained on each swirler part , regardless of quantity . further , unlike conventional milling methods , parts produced by wire edm processing are burr free and can save a tremendous amount of labor cost . because the process does not introduce any stress to the materials , the swirler parts do not warp , bow or curl after machining . the most important feature of wire edm processing , however , is that the conical swirlers blanks 11 can be stacked , or nested together , to allow the fabrication of many precision parts simultaneously . the combined use of stacked swirlers 10 and automated computer control makes wire edm processing the most efficient and economical choice for making the conical swirlers 10 described in this invention . preferably , prior to machining , a plurality of swirler blanks 11 can be nested in a stack 60 as shown in fig6 . the swirler blanks 11 are piled up on top of each other and are held together by a fixture ( not shown ) during wire edm processing . the number of swirler blanks 11 that can be fabricated simultaneously depends on the length of the individual swirler blanks 11 . in a preferred embodiment , for efficient , high - speed wire edm processing , the total length of the stacked swirler blanks 11 should not exceed about two ( 2 ) inches . the length of a typical swirler blank 11 can range from about 0 . 200 inch to about 0 . 400 inch . accordingly , for swirler blanks 11 having a length of about 0 . 200 inch , each wire edm manufacturing operation can produce at a minimum , at least ten ( 10 ) finished conical swirlers 10 simultaneously in one stack 60 . those skilled in the art will readily appreciate that the number of swirler blanks that can be machined at one time will depend largely upon the capacity of the edm machine . in addition , the number of conical swirlers that can be stacked together and machined at one time will depend upon the conical pitch of the blanks , which will define the extent to which the stacked conical swirlers overlap one another . most importantly , due to wire edm processing , each of the finished conical swirlers 10 from the stack 60 will have precisely the same dimensions with consistent performance . precise and consistent dimensions are extremely important in cost reduction because they eliminate many subsequent operations such as de - burring , rework , inspection , and calibration . although the wire edm manufacturing method is ideal for manufacturing conical style swirlers 10 , it is also suited to manufacture disk - shaped , radial swirlers 24 . use of a conical swirler 10 in a fuel injector will now be described . one of the main purposes in developing conical swirlers 10 is to integrate them into the fuel injectors for cost reduction . cone - shaped swirlers 10 not only allow use of wire edm processing to reduce manufacturing costs , but also fit well into most existing injector configurations that contain conical surfaces . in operation , when a conical swirler 10 is used as an air swirler for a fuel injector , compressed air enters the turning slots at the openings 20 . the airflow under pressure is forced into the turning passages defined by the sidewall of the turning vanes 22 and the retaining wall on the interior surface 12 and the exterior surface 14 . the swirl strength of the airflow is largely determined by the offset distance and angle of the turning slots at the exit area . fig8 shows an illustrative embodiment of a conical air swirler 40 that is fitted into a dual - orifice airblast injector 28 . the embodied dual - orifice airblast injector 28 includes two fuel circuits : a primary fuel circuit 30 and a secondary fuel circuit 32 . fuel traveling through the primary fuel circuit 30 exits from orifice 36 and produces a primary spray . similarly , fuel traveling through the secondary fuel circuit 32 exits from an annular orifice 38 to form a concentric secondary spray . each of the fuel circuits can accommodate similar or different fluids . accommodation of different fluids enables spray characteristics of the fuel injector 28 to be altered for different engine applications and air - fuel mixtures . preferably , the conical air swirler 40 can be positioned between an air cap 42 and a heat shield 44 . the atomizing airflow enters into the air swirler 40 at opening 46 and travels through the turning passages defined by the turning vanes 48 toward the center axis . as the airflow emerges from the injector 28 , it expands radially outward to disperse the fuel droplets from the primary and secondary sprays into a circular or substantially circular pattern . through experimental tests , performance of the conical swirler 40 in the embodied airblast fuel injector 28 is strongly coupled with the geometry of the air cap 42 . more specifically , the contoured shape of the exit surface 50 and the dimension of the diameter of the necking point 52 play an important role in determining the spray characteristics , such as , droplet size , spray angle , swirl strength , flow velocity and spray patterns . the preferred contoured shape of the exit surface 50 of the air cap 42 is a smooth , convergent - divergent geometry with a necking point 52 located a short distance from the fuel exit orifice 36 . “ convergent - divergent geometry ” refers to a geometry that , upstream of the necking point 52 , converges radially inwardly in the direction of the conical swirler 40 and , downstream of the necking point 52 , diverges radially outwardly towards the combustion chamber ( not shown ). swirling air from the conical swirler 40 after it exits the airflow passages first enters the converging , radially inward portion of the air cap 42 . as a result , the exiting airflow is directed towards the orifice 36 and annular orifice 38 , which promotes greater swirl and better atomization . then , when the atomized fuel passes through the necking point 52 into the diverging , radially outward portion of the air cap 42 , the atomized fuel is dispersed radially outward as it enters the combustion chamber . preferably , the diameter of the necking point 52 must provide a large enough exit area so that it does not impose additional constriction to the airflow entering into the swirler passages . generally , the preferred flow area at the necking point 52 should be at least two times that of the available swirler inlet opening area 46 . fig9 shows an illustrative embodiment of plural conical swirlers 62 and 64 that are fitted into a single - circuit simplex airblast injector 60 . in this illustrative embodiment , the fuel injector 60 includes a conical swirler 64 for an air flow circuit and a conical swirler 62 for a fuel flow circuit . the single - circuit , simplex airblast injector 60 utilizes a conical fuel swirler 62 and a conical air swirler 64 to induce swirl motion for fuel atomization and droplet dispersion . liquid fuel under pressure is forced through the fuel circuit 66 into the opening 68 of the fuel swirler 62 . the liquid fuel emerges from the turning passages of the fuel swirler 62 , generating a whirling flow of fuel in the swirl chamber 70 . the whirling liquid fuel exits the orifice 72 of the swirl chamber 70 as a hollow spray that contains a multitude of fine fuel droplets . on the airflow side , compressed air enters the openings 74 of the air swirler 64 . the turning vanes direct the airflow radially inward . as the airflow exits the airflow passages of the air swirler 64 , the airflow first enters the converging , radially inward portion of the air cap . as a result , the exiting airflow is directed towards the fuel spray exiting the orifice 72 , which promotes greater swirl and better atomization . rapid mixing and atomization of the fuel spray and swirling air take place in the vicinity of the necking area 76 before the atomized spray diverges radially outward into the combustion zone . fig1 shows yet another illustrative embodiment of plural conical air swirlers 82 and 88 that are fitted in a pre - filming airblast injector 80 . in this particular configuration , an inner air swirler 82 is located in the central passage 84 of the fuel injector 80 at some distance upstream of an annular fuel orifice 86 . an outer air swirler 88 is disposed between the air cap and the outside of a heat shield body 90 . preferably , the inner and outer air swirlers 82 and 88 are coaxial . the fuel swirler 92 is connected to a fuel delivery line 94 . fuel passes through the fuel delivery line 94 to the fuel swirler 92 where it travels through a winding , spiral passage 96 to a plurality of spin slots 98 . fuel passes through the spin slots 98 into an annular fuel gallery 100 . from the annular fuel gallery 100 , the fuel enters a pre - filming area 102 , where , at first , it attaches to the wall surface of the pre - filming area 102 before it is released into the converging , radially - inward portion of the air cap in the form of a hollow sheet . a compressed gas enters the openings of the outer air swirler 88 and , further , passes through a central passage 84 before entering the openings of the inner air swirler 82 . each of the outer and inner air swirlers 88 and 82 include turning vanes that direct the airflow radially inward towards a center axis about which the air swirlers 82 and 88 are coaxially structured and arranged . the inner air swirler 82 produces an inner air stream 104 that enters the converging , radially inward portion of the air cap inside the hollow sheet of fuel . the outer air swirler 88 produces an outer air stream 106 that enters the converging , radially inward portion of the air cap outside the hollow sheet of fuel . the combined airflow of the inner air stream 104 and the outer air stream 106 attacks the hollow sheet of fuel to cause sheet breakup , which disperse the droplets into the desired spray pattern . the atomized spray passes into the diverging , radially outward portion of the air cap , causing the atomized spray to diverge radially outward into the combustion zone . although preferred embodiments of the invention have been described using specific terms , such description is for illustrative purposes only , and it is to be understood that changes and variations may be made without departing from the spirit or scope of the following claims .