Patent Application
20220397267
The present invention relates generally to atomizers, and more particularly to a swirling flow-blurring atomizer.
Conventional gas turbine engines are currently being developed that will allow greater range, flight duration, and available power for electronic payloads, but their operability can be compromised by the available fuel quality in regions since they are designed for single-fuel operation. Fuels laced with impurities, poor distillation quality control, higher-cut, or high viscosity fuels such as plant-derived fuels may be more readily available than jet fuel, kerosene, or diesel in remote regions of the world. Power systems with engines capable of operating on lower quality fuels can remain operational while utilizing the local fuel supply. Designers typically optimize gas turbine fuel injectors to operate with kerosene-based jet fuels, such as Jet A, JP-5, or JP-8. These engines use conventional fuel injectors, such as pressure, air-assisted, or air-blast atomizers, in conjunction with swirl-stabilized or similar recirculation zone-stabilized burners. Pressure atomizers require heavy, high-pressure pumps and small exit diameters. Air-assisted atomizers require a portion of compressor air while air-blast atomizers require a secondary, high-pressure source of air to atomize fuel. Both utilize narrow, circuitous fuel injection routes to distribute liquid fuel to locations where high local shear stress between the air and fuel atomizes the fuel. Narrow flow passageways are incapable of accommodating highly viscous residual fuels and fuel-born particles found in low quality fuel without clogging.
Conventional flow-blurring atomizers are capable of atomizing a wide range of both high and low viscosity fuels while delivering a consistently fine droplet distribution. Though similar to a flow-focusing or air-blast atomizer, the fuel delivery is placed close to the exit to produce a high-shear region where the atomizing air flows radially inward and then must turn sharply to exit. In the process, local shear forms and stretches thin ligaments as air travels out of the nozzle. Surface tension breaks apart the ligaments into droplets to produce primary atomization. A key advantage of the flow-blurring atomizer is the low pressure requirement for both fuel and air.
Though the multi-fuel capability of the flow-blurring atomizer makes it a design candidate for multi-fuel engines, it produces a narrow, solid spray plume that is suited more to diesel engines than gas turbine engines. In the swirl-stabilized burners used in aircraft, industrial, and marine gas turbines, solid, conical spray plumes are shown to produce lifted flames that are susceptible to acoustic coupling because their anchoring behavior is coupled to the pressure drop across the swirler. To avoid lifted swirl flames, gas turbine combustors typically use hollow spray plumes in the center of a jet of swirling air.
Therefore, described herein is a device for producing a wider spray plume than can be produced by a conventional flow-blurring atomizer (FBA) with the same supply pressures and flow rates of the atomizing gas and liquid. The tangential momentum imposed by the swirl also increases the turbulent mixing between the plume and the surrounding air. This change assists in broadening the spray plume droplets to a wider region and in the formation and anchoring of stable combustion.
According to one aspect of the invention, an atomizer configured to atomize liquids passed therethrough includes an endcap having a nozzle situated therein; an annular sidewall extending axially outward from a surface of the endcap and situated radially outward from the nozzle; and a plurality of vanes extending radially inward from any location along the sidewall as well as axially outward from the endcap, the vanes being set at a non-zero angle of incidence to the sidewall. The annular sidewall and endcap define an inner fluid chamber between a fluid inlet and the nozzle, and wherein flow from the inlet to the nozzle is at least partially directed through passageways between the plurality of vanes, and wherein the flow is imparted with swirling motion from the plurality of vanes.
Optionally, the nozzle is centered with respect to the annular sidewall.
Optionally, the vanes are connected to an inner surface of the annular sidewall.
Optionally, the vanes are connected to the surface of the endcap.
Optionally, the angle of incidence is 32 degrees.
The foregoing and other features of the invention are hereinafter described in greater detail with reference to the accompanying drawings.
To produce a wider, hollower plume than conventional atomizers, swirl vanes can be added to impart tangential momentum to the atomizing air at any location upstream of the liquid injection to increase rotation as it approaches the exit orifice, which propels droplets outward from the plume center to form a broader, more hollow, conical spray plume that will prevent flame lifting and the associated combustion dynamics. Preliminary demonstrations with 30° swirl vanes have shown to produce broader plumes with better mixing behavior than the strait atomizer.
Referring first to
Nozzle tests have been performed with water and air to determine the spray behavior of exemplary atomizer tips, as shown in
Plume tests reveal that a conventional nozzle produces a plume spreading angle of 22°, while an exemplary nozzle with 30° radial swirl vanes produces a plume with a spread of 32°, resulting in a 31% increase.
The tangential momentum imposed by the swirl vanes produces a substantial increase in the plume angle that allow exemplary atomizers to be utilized for any application that requires a broader spray cone, such as, for example, spray burners, coating applications, fire suppression, and water-efficient spray washing.
The tangential momentum imposed by the swirl also increases the turbulent mixing between the plume and the surrounding air. This change assists in broadening the spray plume droplets to a wider region and in the formation and anchoring of stable combustion.
Although the invention has been shown and described with respect to a certain embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described elements (components, assemblies, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.
The United States Government has ownership rights in this invention. Licensing inquiries may be directed to Office of Technology Transfer, US Naval Research Laboratory, Code 1004, Washington, D.C. 20375, USA; +1.202.767.7230; techtran@nrl.navy.mil, referencing NC 107170.
