Patent Grant
7513489
This invention relates generally to fuel delivery systems, and particularly to a fuel delivery system including a fuel nozzle incorporating a closed STAR TUBE™, the system providing a fog of fuel droplets sized 50 microns and less, and predominantly in the 10-30 micron range, while minimizing vapor formation.
A large number of methods for producing fuel-air mixtures for reciprocating internal combustion engines, such as Otto cycle engines, Diesel engines, 2-stroke engines, Wankel-type engines and any other compression-type engine are well known, and many are patented. However, as far as Applicant is aware, many previously disclosed methods, except Diesel and jet engines, attempt to produce a fuel vapor mixed thoroughly with air. In many of these methods, fuel is heated, in some instances to near a boiling point of the fuel, in order to convert the fuel to a gas prior to its induction into a combustion chamber. Virtually all attempt to minimize fuel droplet production and maximize fuel vapor production based on the belief that fuel droplets in the fuel/air mixture cause inefficient combustion, and generate more pollutants in the exhaust. In most engines, fuel spray from a carburator or fuel injector is simply sprayed into an intake manifold of the engine.
In gasoline engines, one major drawback to providing a stochiemetric fuel/air mixture wherein the fuel is in a vapor form is that the vapor provides a readily explosive mixture. This becomes a problem when loading on an engine causes pressures in the combustion chambers sufficient to raise a temperature of the fuel/air mixture to or beyond its flash point. This in turn causes the fuel/air mixture to explode all at once (rather than burning evenly in an outward direction from the spark plug), a condition commonly known as “ping”, or in older, worn engines “knock”, due to the knocking noise created as bearings of the piston connecting rods are slammed against the crankshaft under the force of the explosion. As might be imagined, such a condition is deleterious to bearings and other parts of the engine, and can greatly shorten engine life. For purposes of this application, both ping and knock are used to refer to a detonation of the fuel vapor/air mixture in a manner similar to an explosion rather than a controlled burn.
Where gasoline is simply sprayed into an engine manifold, as from a carburetor or fuel injector, droplets of all sizes enter the combustion chamber. Here, Applicant has discovered that fuel droplets larger than about 50 microns or so do not burn completely, creating unburned hydrocarbon pollutants. With respect to Diesel and jet fuel, incomplete burning also produces carbon particulate pollution in addition to gaseous hydrocarbon pollution.
In accordance with the present invention wherein a fog of size-limited fuel droplets of about 50 microns and less predominantly make up the fuel component of the fuel/air mixture, apparatus is provided that processes metered quantities of fuel delivered by a fuel injector, fuel valve (or other nozzle) or any other fuel metering device into an aerosol fog having droplets less than 50 microns in diameter and with a minimum of vapor. As stated, the object of this invention is to cause internal combustion engines such as Otto-cycle engines, Diesel engines, two-stroke engines, Wankel-type engines and other, such engines that compress an air/fuel mixture to operate more efficiently, with less pollution and without knock than has heretofore been possible. It has been discovered that fuel droplets of about 50 microns and less in diameter burn at a slower rate than a fuel vapor/air mixture that explodes, but significantly faster than the larger liquid fuel droplets delivered by conventional fuel delivery systems currently in use. In addition, it has been found that these smaller fuel droplets, when thoroughly mixed with air, burn more stoichiometrically than larger fuel droplets. It is believed a larger fuel droplet depletes the surrounding microenvironment of oxygen before burning completely, thus creating the unburned hydrocarbon pollutants found in exhaust gases. In contrast, fuel droplets smaller than about 50 microns in diameter consume surrounding oxygen in a stoichiometric relation when burned because of their extremely small size, thus the net fuel/air charge in a combustion chamber is burned completely, rapidly and with little to no hydrocarbon pollutants. It is also believed that since, in one embodiment of the instant invention, fuel is initially sprayed into a generally confined tube (designated as a STAR TUBE™ for purposes of this application) containing turbulence-inducing devices, vapor saturation of air within the tube prevents further evaporation of the fuel droplets, causing the fuel droplets to be reduced in size mechanically rather than by evaporation as the fuel droplets travel through the tube. Here, as the fuel, and particularly with respect to gasoline and other volatile fuels, is released from pressure of the fuel rail and exposed to the partial vacuum created by the downward travel of a nearby piston via the open intake valve, lighter, more volatile components of the fuel instantly evaporate and increase hydrocarbon vapor pressure within the tube, suppressing further evaporation of the fuel droplets. In addition, cooling due to rapid expansion of the evaporating lighter components of the fuel cools and stabilizes the fuel droplets within the closed environment within the STAR TUBE™. The fuel is then processed mechanically by turbulence-inducing devices in the STAR TUBE™ until the droplets reach a size sufficiently small so as to travel with a localized region of fuel-saturated air to the combustion chamber. The fuel/air mixture is thoroughly mixed as it passes the intake valve and compressed in the combustion chamber, causing a rapid, even burning of the fuel.
In addition to the foregoing, it is also well known that when a cold engine is started, only about ⅕ of the fuel is burned. Only after the engine warms does it become possible to burn the fuel stoichiometrically. During the warm-up period, the quantity of unburned hydrocarbon pollutants produced by the engine are much greater than in a warm engine. Applicant's system for fuel processing also greatly reduces such pollutants developed by a cold engine by providing an air/fuel mixture that burns readily and completely.
Engines such as Diesel or other direct injection engines may also benefit from fuel processed into droplets sized 50 microns and less. Here, an aerosol fog of Diesel fuel having droplets of 50 microns and less will burn faster and ignite easier than a fuel spray of larger droplets, this fuel fog increasing efficiency and reducing unburned hydrocarbon pollutants and particulates in the exhaust of Diesel-type engines. Also, such combustion properties allow a more stoichiometric proportion of Diesel fuel/air to be used. Similarly, turbine and other jet engines, which typically are sources of unburned hydrocarbon pollution and particulates because of poor fuel management, particularly in afterburner modes of operation, may also benefit by fuel provided as a fog of droplets sized 50 microns and less. These droplets burn faster and/are ignited easier than would otherwise be the case. This allows more of a stoichiometric combustion of the jet fuel, reduces particulates and hydrocarbon pollutants in the exhaust gas, increases the efficiency the engine and may even prolong life of a jet engine.
In accordance with the foregoing, it is one object of the invention to provide a fuel delivery system that processes fuel into a fuel fog having fuel droplets of a maximum predetermined size. It is another object of the invention to provide apparatus for generating a fuel/air mixture wherein the fuel is incorporated into a fog of droplets sized 50 microns and less to as great an extent as possible, with as little vapor as possible. It is yet another object of the invention to provide a closed STAR TUBE™ and fuel injector or other fuel nozzle as a single integral unit or assembly sized so as to be as direct a replacement as possible for a conventional fuel injector. Other objects of the invention will become apparent upon a reading of the following appended specification.
a is a diagrammatic view showing particulars of construction related to a different embodiment of the present invention.
b is a diagrammatic view showing particulars of construction related to another embodiment of the present invention.
a is a view of an end of a STAR TUBE™ that receives a fuel injector.
b is a cut-away view showing particulars of another embodiment of the invention.
a is another embodiment of the invention integrating a STAR TUBE™, a smaller air reservoir and a fuel metering system into a single integral unit.
b is yet another embodiment of the invention integrating a STAR TUBE™ and a fuel metering valve into a single integral unit without a discrete air reservoir, with carrier gas supplied from the volume of air and gas within the STAR TUBE™.
a is a diagrammatic illustration of another way a STAR TUBE™ may be fitted to a jet engine.
The basic principle of operation of the present invention involves providing a fuel fog having fuel droplets of a maximum predetermined size of from about 50 microns or so in diameter down to just larger than sub-micron clumps of fuel generally considered to be vapor. While in some fuels, such as gasoline, formation of some vapor cannot be avoided due to high volatility of the lighter components of the fuel, it is believed one feature of Applicant's system minimizes fuel vapor formation and keeps the fuel in droplet form to as great an extent as possible by creating a cooled fuel vapor-saturated region within which the fuel fog is transported, the cooling and saturation of the region stabilizing the fuel fog and preventing further evaporation of the fuel droplets. In this form, droplets of a fog are known to be particularly stable, with diffusion being the primary way droplets dissipate. Here, surface tension of the fuel droplets in such a fuel fog is believed to also contribute to prevent evaporation and dissipation of the fuel droplets until the droplets are burned.
In a most basic embodiment of the invention, and as shown in
Pursuant to Applicant's system, devices other than Applicant's specific apparatus may be used to generate a fuel fog, such as piezoelectric atomizers, ceramics sieves receiving pressurized fuel, specialized nozzles such as SIMPLEX™ nozzles and LASKIN nozzles, air pressure atomizers, rotary cup atomizers, ink jet-like devices that operate using ink jet or bubble jet technologies, insecticide spray nozzles and other nozzles such as nozzles from CHARGED INJECTION CORP. of New Jersey. These alternate devices may be incorporated into a throttle body or intake manifold, either with or without a STAR TUBE™ of Applicant's design. In addition, devices such as the NEBUROTOR™ available from IGEBA GERAETEBAU CORP. of Germany may also be used. This device uses a motor-driven rotating blade to break the liquid fuel into droplets of the desired predetermined size. However, it is probably desirable to generate the fuel fog in a closed environment so as to take advantage of vapor saturation and cooling of the environment within which the fuel fog is created. As such, these devices may be mounted within some form of tube or housing communicating with the induction air flow. Further, other applications of Applicant's STAR TUBE™ include spray painting, spraying insecticides, herbicides or fertilizer, powder coating applications and other applications wherein it is desired to break a liquid into droplets of a relatively uniform, predetermined size. Furthermore, such creation of a fog of droplets may be advantageously accomplished in combination with a gas used as a carrier or vehicle to transport and process the droplets through a STAR TUBE™. One example of such a process is wherein a product is formed from binary compounds, with one of the compounds being a liquid and the other being a gas or vapor. Here, using Applicant's STAR TUBE™, mixing of the two compounds occurs almost instantly and in an extremely uniform manner. Such an application may be useful in drug manufacture where a liquid precursor for a drug is treated with a gas, such as hydrogen or oxygen. In this application the gas and liquid precursor may be applied through a STAR TUBE™ in a stoichiometric proportion, as contrasted to currently used methods where the gas is simply bubbled up through a solution containing the liquid precursor.
Droplet sizes produced by Applicant's STAR TUBE™ were measured by a test rig wherein a STAR TUBE™ as disclosed herein and an associated fuel injector was set up in a simulated throttle body constructed of a transparent material. A suction device was used to draw air through the simulated throttle body at a rate representative of induction air flow. Conventional laser interferometry equipment, such as that used to measure size of pesticide droplets, was used to measure size of the fuel droplets as they exited the STAR TUBE™. As stated, a maximum fuel droplet size was found to be approximately 50 microns, with most of the droplets being in the 10-30 micron range.
In one particular embodiment of the instant invention, and by way of example, part of the induction air flow through an intake manifold of an engine may be diverted and utilized to process fuel sprayed by one or more fuel injectors into droplets sized 50 microns and less to provide the fuel fog. This embodiment uses two or more discs, with five discs for each STAR TUBE™ performing best to develop a fog having droplet sizes predominately in the range of 10 to 30 microns or so, with 50 microns being the maximum size. Each disk has a central opening, with a series of slits or vanes radially extending away from the central opening and each vane angularly positioned to spin the diverted induction air flow and fuel droplets. Slits between the vanes converge with distance from the central opening, forcing the air and fuel droplets in a flow path through the central opening and slits between the vanes. For purposes of this application, these plates are variously enumerated as Star Spin and Shear plates, or simply Star plates. Also, while some retrofit embodiments disclosed herein utilize conventional fuel injectors or similar devices, it should be apparent that a fuel injector is simply a metering valve for liquid fuel, and any fuel metering device for providing selected quantities of fuel may be substituted for a fuel injector and used in conjunction with Applicant's STAR TUBE™.
Here, a fuel injector may be replaced by any other fuel-management device, such as a cam activated piston, a solenoid activated piston, or a variable speed fuel pump. Such a fuel pump may be particularly applicable to a turbine or other type jet engine. Also, any of the aforementioned devices may be used alone to develop a fuel fog for mixing with intake air flow for combustion in an internal combustion engine, and advantageously should be mounted in an enclosure communicating with the induction air flow so as to saturate and cool the environment within which the fuel fog is created.
The vanes of Star plates create turbulence in the flow path, causing mechanical breakup of the fuel into smaller droplets. Within these combined actions, the spinning or spiral path creates centrifugal force on the fuel droplets, forcing them radially outward in the STAR TUBE™ where they pass through narrower portions of the slits between the vanes were turbulence is greater, tearing the larger droplets into smaller droplets. As the droplets become successively smaller as they pass through and by each Star plate, it is believed that the centrifugal and shearing forces overcomes surface tension in the liquid fuel droplets until an equilibrium point between the centrifugal and shearing forces and surface tension of the droplets is reached. Thus, the mixture may have an induced spin about the axis of the STAR TUBE™, as well as turbulent spin from passing through the vanes. After exiting the STAR TUBE™, the resulting aerosol fog is provided to the rest of the induction air stream and the fuel-air mixture is drawn into a combustion chamber.
In addition, and with respect to gasoline-fed engines, the gasoline used in an engine utilizing fuel injectors is provided to the fuel injectors under a significant amount of pressure, typically in the 30 PSI range. Within the STAR TUBE™, some of the lighter components of gasoline, such as pentane and hexane, and to some extent heptane, flash into a vapor when released from the pressure of the fuel rail and become exposed to the manifold vacuum. This provides cooling to the environment within the STAR TUBE™ during operation. Such cooling retards further evaporation of the fuel droplets, and stabilizes the fuel fog as it passes through the STAR TUBE™. Such cooling is believed to be greater than would otherwise be obtainable with a conventional fuel injector by itself, because such a conventional fuel injector provides a spray of fuel with much larger droplets that evaporate less, and in an open environment, as contrasted to the generally closed environment of a STAR TUBE™. While some cooling of the fuel fog is believed to be beneficial at normal operating temperatures, in cold weather the fuel, particularly heavier fuels such as Diesel fuel, may need to be heated in order to flow properly or provide a carrier gas, as will be further explained. Also, the fuel may be heated until an engine reaches its normal operating temperature, which assists in reducing pollutants developed by cold engines.
As stated, the method and apparatus described herein creates a stable fuel fog that allows a gasoline fuel with a lower octane rating to unexpectedly be used without knock in a high compression engine that otherwise would require a higher octane fuel. In the instant invention, and with respect to gasoline, it is believed the extent to which knocking of an engine is reduced or eliminated is dependent largely on the extent to which fuel droplet size is controlled. Also as stated, fuel droplets larger than about 50 microns or so burn in an oxygen-starved microenvironment, causing loss of power along with production of hydrocarbon byproducts characteristic of a “rich” fuel condition. On the other hand, if too much vapor is developed, the vapor may spontaneously detonate (knock) due to increased engine compression as the engine is loaded or if the compression ratio of the engine is higher than specified for the octane rating of the fuel. As stated, empirically derived results have demonstrated that an acceptable fuel droplet size for a sparked ignition engine is 50 microns and less in diameter down to just greater than the submicron clumps of fuel generally considered to be vapor. Within this range, a droplet size of between about 10-30 microns or so appears to be optimal.
In an engine equipped with Applicant's STAR TUBEs™” and where exhaust gases are closely monitored by a conventional engine controller, the more complete, faster and efficient burning caused by the STAR TUBEs™ causes the engine controller to provide close stoichiometric fuel/air charges. In contrast, conventional fuel injectors or carburetor-type devices that provide a fuel spray containing droplets of larger sizes results in unburned hydrocarbons in the exhaust gases that in turn causes the engine controller to reduce fuel in the fuel air charges, creating a lean, less than stoichiometric mixture that causes the engine to not produce rated power.
In these modern engines that have a computer and sensor system to monitor exhaust gas products to determine quantity of fuel to be provided to the induction air, addition of any of the aforementioned gases or vapors via the STAR TUBE™ to induction air is compensated for by the engine controller in order to keep the fuel/air mixture at a close stoichiometric proportion. Further, in the instance where there is a fuel injector for each combustion chamber, an aftermarket or OEM manifold may be provided with provisions to house the fuel injectors and a respective STAR TUBE™ in a position proximate a respective intake port of a combustion chamber, with possibly an air scoop or independent induction air channel cast or mounted in the interior of the intake manifold to direct an appropriate proportion of induction air through the STAR TUBE™. Alternately, an amount of gas or vapor serving as a carrier gas may be controlled, as by a computer such as an engine controller, to maintain or assist in maintaining a close stoichiometric fuel/air mixture or to increase or decrease a flow of motive gas through the STAR TUBE™ to compensate for changes in induction air flow, as when the accelerator pedal is depressed to a greater or lesser degree. Also, mechanical linkages coupled to valving apparatus may be employed for such increases and decreases in the motive flow through the STAR TUBE™.
In gasoline engines specifically designed as “lean burn” engines, excess air is mixed in the fuel/air charge. In these engines, the fuel fog consisting of droplets 50 microns and less burns more rapidly and more completely than would otherwise be the case. Thus, with STAR TUBES(™), these engines operate more efficiently and produce less pollution, and with little or no detonation.
As described herein,
As shown in the embodiment of
By using STAR TUBEs™ in a jet engine to convert fuel into a fog, it should be apparent that the fuel may be controlled so as to produce more efficient and stoichiometric burning, in turn increasing efficiency, reducing pollutants and conserving fuel.
In yet other embodiments, such as in gasoline engines, it has been found that external carrier gas is unnecessary, with a motive flow of gas through the STAR TUBE™ provided by ambient gas or air within the STAR TUBE™, and by lighter components of the liquid fuel flashing into vapor. In these embodiments wherein no external carrier gases are provided, it has been found that lighter components of gasoline fuel flashing into vapor cools the environment within the STAR TUBE™ to between about 35-45 degrees Fahrenheit. As stated, this stabilizes the fuel fog. Also, vacuum developed by the engine assists in flashing the lighter components of the fuel into vapor. Here, as the spray of fuel is provided by the fuel injector, the associated piston begins its downward travel on the intake stroke, creating a partial vacuum in the intake manifold that is felt by the volume of air in the STAR TUBE™. As the partial vacuum increases due to the piston continuing its downward travel, air and fuel vapor, along with fuel droplets from the fuel injector, are drawn outward, pulling and processing the fuel droplets through the STAR TUBE™. After the intake valve closes, the partial vacuum dissipates, allowing air in the intake manifold to re-enter the STAR TUBE™. Of course, this action is in addition to any fuel vapor developed as described, and which contributes to carrier gas flow. This embodiment is useful in retrofit applications as only a closed STAR TUBE™ need be mounted between each fuel injector and its respective port. In all instances, the STAR TUBE™ and fuel injectors assemblies are mounted and supported by brackets or other similar structure (dashed lines in
With reference again to
In the example of
One STAR TUBE™ that has been found to work well for the aforementioned 350 cubic inch engine is shown in
The region of the tube portion 42 immediately adjacent cap 40, which may be about 0.250 inches thick, may be tapered on an interior side over about a 0.5 inch length of the tube portion as shown in order to provide a clearance for openings O, and to provide a feeder region for fuel spray from the injector. Additionally, this taper somewhat compresses air flowing through openings O, thus advantageously speeding up velocity of air flowing through the STAR TUBE™. Alternately, the STAR TUBE™ may be constructed of thinner material. As such, the spray of fuel from the fuel injector is initially introduced into the STAR TUBE™ along with a flow of air. The flow of air and fuel droplet spray then encounters a plurality (5 shown) of turbulence-inducing devices, namely serially arranged Star Spin and Shear Plates 46 spaced about 0.75 inch from one another, with the closest star plate to the injector being spaced about 0.75 inch from the interior transition of the taper. As described, this volume, and to some extent the volumes between the Star Spin and Shear plates, forms a reservoir (in the absence of openings O) wherein air and fuel vapor in the STAR TUBE™ constitute carrier gas.
The Star plates may be mounted in the tube as by an interference fit between edges of each plate and an interior of a tube, by lips or supports constructed along an interior surface of the tube that the plates rest on, by bonding the plates within the tube, securing by fasteners, or any other obvious means for securing the plates within the tube, as represented by blocks 48 in
The Star Spin and Shear plates 46 each have a plurality of types of openings (
As a feature of the invention,
In addition, it has been found that the vanes may be angled either upward or downward, with approximately equal performance with respect to breaking up larger droplets into smaller droplets. Here, while the rotation imparted by downwardly extending vanes causes axial spin of fuel/air mixture through the STAR TUBE™, upwardly extending vanes also creates spin through the STAR TUBE™, in addition to the aforementioned shearing action around edges of openings 52.
While a Star Spin and Shear plate is disclosed, other configurations of plates with openings therein have been tested and have been found to work, albeit to a lesser extent but to an extent which may be practical. For instance, in one test the Star Spin and Shear plates were replaced with conventional flat washers having only a central opening. In this example, spin of the airflow was eliminated while providing relatively sharp or abrupt edges around central openings in the washers, these edges developing turbulence in the airflow. This embodiment worked about 40% as well as the Star Spin and Shear plates having vanes and radially extending slits. In another test, the Star Spin and Shear plates were replaced with TENON-type quick-connect nuts, which are configured similarly to the Star plates. These worked about 70-80 percent as well as the Star Spin and Shear plates. From this, it should be apparent that openings of any configuration in the plates may be used. This would include star-shaped openings, rectangular openings, square openings, or any other opening configuration. In addition, these openings may be alternated between successive plates so that a first plate may have one particularly configured opening and the next plate may have a differently configured opening, and so forth. In addition, it has been found that other types of washers and washer-like devices, such as star-type lock washers, which also have a similar configuration to a Star plate, work well. Another device that has been found to work to some extent is a disk or plate similar to a star-type lock washer except lacking a central opening. In this latter embodiment, fuel restriction was found to be a problem, but wider, outwardly extending radial slots or openings that terminate at a periphery of the plate may improve performance.
While 6 spoke-like slits 52 are shown in a Star Spin and Shear plate, more or fewer of these slits may be employed, such as about three or more. Likewise, while 5 star plates are shown and have been found to be optimal, fewer or more of these plates may be used, such as from about 1 or 2 to 7 or so. Also, the STAR TUBEs™ and Star plates may be scaled as necessary depending on displacement of the engine and number of fuel injector/STAR TUBE™ assemblies per cylinder. As stated, more plates and smaller openings and slits produce smaller droplets, with fewer plates and larger openings and slits producing larger droplets. Also, a greater rate of flow produces smaller droplets, while a slower rate of flow produces larger droplets.
As a primary function of a fuel injector is to provide a selected amount of fuel as determined by an engine controller, the fuel injector simply serves as a variable fuel metering valve responsive to the engine controller. As such, it may be possible to replace the fuel injector with a simple metering valve that provides the required amount of fuel, and generally as a spray or stream, to a STAR TUBE™ responsive to a signal from the engine controller, with the STAR TUBE™ breaking up the fuel into droplets of the predetermined size of about 50 microns and less.
It has been found that in the instance where a carrier gas is used, the carrier gas passing through all the STAR TUBEs™ of an engine may be up to a maximum of about five percent or so of the total induction airflow through the throttle body and intake manifold. In any Star Tube system, the process of breaking up the larger droplets may further be assisted or regulated by additives in the fuel to limit droplet breakup beyond a selected smallest size, such as 1-10 microns or so. Here, the additive may be selected so as to increase surface tension in the fuel droplets so that the smallest droplets of the fuel fog do not break up into yet smaller droplets. For instance, the addition of a small amount of heavier oil or fuel oil to gasoline, or addition of a small amount of glycerin or castor oil to alcohol, may increase surface tension or reduce volatility of the fuel so as to facilitate small droplet formation and minimize vapor formation.
As stated, when lighter fuels, such as gasoline, are initially sprayed into a STAR TUBE™ from a fuel injector or similar nozzle, more volatile components of the fuel are vaporized instantly due to being released from pressure in the fuel rail or fuel system, which may be about 30 PSI or so, and exposed to the vacuum pulse in the intake manifold adjacent an intake valve. This flashing into vapor saturates and cools the environment in the STAR TUBE™ so that further evaporation of the remaining heavier-component fuel droplets is prevented. Further, when drawn into the induction airflow, the volume of lighter-component fuel vapor containing the heavier-component fuel droplets forms a gas and vapor bolus of cool, hydrocarbon fuel-saturated air that stabilizes the heavier-component fuel droplets and prevents them from evaporating as they are drawn into a combustion chamber. Thus, in embodiments closed to an external source of carrier gas, a fuel charge for each intake stroke is made up of fuel droplets (50 microns and less) of the heavier-component fuel suspended in air partially saturated with cooled lighter-component fuel vapor. Such separation of the fuel into lighter-component vapor and heavier-component, size limited droplets may contribute to more efficient and faster burning of the fuel by causing faster propagation of the flame front through the fuel vapor/droplet/air mixture.
Several test engines have been adapted with Applicant's invention in order to test feasibility, practicality and workability of the STAR TUBEs™. For instance, one such engine was adapted as described above, and performed on a dynamometer as follows:
Engine:
A Chevrolet 350 CID engine bored out 0.030 to provide about 355 CID and a Compression Ratio of about 10.6:1.
Total runs done: more than 160.
4 STAR TUBEs™: (Step Diffuser plates enhanced by Star spin) mounted in a throttle body,
Six Star spoked openings, base to base: ¾ in.
Peak anti-detonation effect in this engine was found with 5 to 7 Star plates. With more than 7 plates, power began to drop, probably because of fuel restriction. With 3 plates, the effect was still about 80% of what it was with 5 plates. In this engine;
Star plate OD: 15/16 in.
Tube ID: 13/16 in.
Tube OD: 1¼ in.
Tube length about four inches Smaller sized Star plates and tubes still produced an effect but with a proportional reduction in engine power. Sizing of the Star plates may therefore be a function of air-flow (almost akin to engine size) through the engine. Considerable latitude appears to exist, but larger area Star plates work better with larger displacement engines, and vice versa. As a general rule, the STAR TUBEs™ work well when they receive about 5% of the total induction airflow through the throttle body. The opening or openings in cap 12 around the fuel injector tip are generally sized to allow little restriction of carrier gas flow through the tube. Typically, engine runs were from 5000 rpm down to 2500 rpm, with data readings taken by conventional engine monitoring equipment.
Engine measurements were taken at every 250 rpm from between 1500 rpm up to about 4500 rpm. Critical detonation data typically comes in between 3000 and 3500 rpm. Peak torque typically comes in between 3000 and 4000 rpm. Spark advance was set for best torque (without detonation, if any). With C-12 (108 octane racing fuel used to establish a baseline), there was never any detonation regardless of the amount of spark advance (this did not exceed 36 degrees). Using a gasoline with an octane rating of about 80, peak torque with the STAR TUBEs™ was typically at about 30 degrees spark advance with no knock. Peak torque was always equal to or better with STAR TUBES™ and 80 octane gasoline than peak torque with C-12 and conventional fuel injectors. The lesser spark advance used to obtain peak torque with the STAR TUBES™ is indicative that the 80 octane fuel fog burns faster than the C-12. Further, it has been found that utilizing STAR TUBEs™ and 80 octane gasoline, with the spark advance set for peak torque at 28-30 degrees spark advance, exhaust gases are cooler, indicating that more available power is converted to mechanical energy, and not wasted as heat.
In an aviation context, a ROTORWAY™ helicopter engine in a helicopter was modified with STAR TUBEs™ and extensively tested. In this embodiment of the STAR TUBEs™, the tubes were similar to the ones used in the Chevrolet™ engine as described, except were closed to any external carrier gas. The gasoline feed region of the STAR TUBE™ serves as a gas/vapor reservoir. The ROTORWAY™ engine is a fuel-injected aviation engine rated at 145 horsepower, with a fuel injector for each cylinder of the engine, each fuel injector injection tip mounted in a fuel injector port located just upstream a respective intake valve. The fuel injectors were removed, and a STAR TUBE™ mounted in each fuel injector port. The fuel injector was then mounted at the other end of the STAR TUBE™, and as stated, closed to any external source of carrier gas so that there was a small air reservoir approximately ¾″-1″ or so between the fuel injector tip and the first Star plate. In full power dynamometer tests, the ROTORWAY engine equipped with STAR TUBEs™ produced over 200 horsepower, as opposed to 145 horsepower for a full power test of the conventional version of the engine. In a 30 minute hover test, the ROTORWAY helicopter equipped with STAR TUBEs™ used slightly under three gallons of gasoline at a ⅓ power throttle setting, as compared to the same helicopter without STAR TUBEs™ which used four gallons of gasoline at a ⅔ power throttle setting in the same 30 minute hover test. Clearly, the embodiment of STAR TUBEs™ closed to any external carrier gas, at least with respect to the ROTORWAY engine, provides about 25 percent increase in power and efficiency.
The STAR TUBE™ of the instant invention may also work with certain Diesel or Diesel-type engines wherein the fuel is ignited by compression. In this instance, and referring to
Operation of the embodiment of
In yet other embodiments that may be particularly applicable to gasoline or other sparked ignition engines, and referring to
The assembly 200 is provided with an outer hollow housing 202 having a port 232, which as stated sealably communicates with fuel rail 230, with the combined fuel valve and STAR TUBE™ assembly 204 mounted in housing 202. Housing 202 may be constructed to internally and rigidly support assembly 204 at an interface region 206, although other internal mounting arrangements may be implemented, as should be apparent from Applicant's disclosure to one skilled in the art. An armature assembly 218 is provided between housing 202 and assembly 204, and is provided with a magnet portion 220 that reacts against a magnetic field developed by solenoid 222. Thus, armature assembly 218 is raised and lowered responsive to control current applied to solenoid 222. Also attached to an upper portion 223 of armature 218 is a needle portion 224 of a needle valve, which is mounted so as to release a flow of fuel through an entrance 226 of nozzle 212 when the armature is raised. A spring 228 biases armature 218 downward, pressing needle 224 against a needle valve seat 229 at entrance 226 until the armature is lifted by an energizing current pulse provided to solenoid 222. Vertical or other guides (not shown) may be incorporated on armature 218 and on interior surfaces of housing 202 so that needle 224 is maintained in a precise position with respect to seat 229 as the armature is actuated up and down. As stated, fuel rail 230 provides fuel to the interior of housing 202 via opening 232, from which pressurized fuel flows to opening 226. For reducing hydrostatic resistance as the armature is moved up and down, the armature may be provided with openings, or be constructed as a cage-like structure, as should be apparent from Applicant's disclosure to those skilled in the art. Further, the skirt of the armature may be shortened so as to extend barely over the reservoir, reducing its mass. In this instance, the coil 222 would be appropriately positioned. As should be apparent from Applicant's disclosure, the armature and fuel valve may take many forms, the primary feature being that of a fuel metering valve constructed in conjunction with a STAR TUBE™, with or without an air reservoir, and all as a single, integral, compact unit.
In operation, and as stated, pulses of appropriately poled current flow, which may be on the order of about 1-15 milliseconds or so, depending on the fuel demand to the engine, are applied to solenoid 222. Responsive to these pulses, armature 218 is lifted against the bias of spring 228, releasing fuel through opening 226 for a duration approximately equivalent to the duration of each pulse. Just before or concurrently with each pulse, an intake valve in the engine opens and an associated piston begins downward travel of the intake stroke, creating a temporary vacuum pulse in the intake manifold. This temporary vacuum pulse causes air in air reservoir 216 (when provided) to rush downward through the STAR TUBE™ and out port 238. In addition, such a temporary vacuum pulse in combination with pressure in the fuel rail assists in vaporizing lighter components of the fuel, which develops more carrier gas and vapor and cools and saturates air in the STAR TUBE™ as described above. Fuel droplets from nozzle 212 are carried along with the rush of air along with the lighter, vaporized components of the fuel from reservoir 126 and processed as described above by Star plates 210. After the intake valve closes, the partial vacuum pulse is eliminated and air fills the Star TUBE™. Thus, in this embodiment, an external supply of gas or air need not be provided to the STAR TUBE™, and the entire assembly 200 may be constructed in a more compact form, possibly a short as the length of a conventional fuel injector. In these embodiments that do not use an external carrier gas, it may be that after a short period of operation, and particularly at higher RPM's of the engine, reservoir 216 becomes filled with fuel vapor that may simply oscillate back and forth on each stroke of the engine, with all the fuel vapor never really clearing the reservoir. In this instance, the lighter-component, fuel saturated environment in the reservoir assists in preventing further evaporation of the heavier-component fuel droplets. Of course, as the lighter fuel components flash into vapor when released from pressure in the fuel rail, the newly formed fuel vapor displaces any fuel vapor remaining in the STAR TUBE™ along with the heavier-component droplets.
a and 7b each show an integral device similar to that of
Also shown in
While a heater is shown within the assembly 200 of
Other, more volatile fuels than gasoline may also be used in conjunction with a STAR TUBE™ system. For example, cryogenic fuels such as liquefied propane or liquefied natural gas, and possibly hydrogen, may be used. Here, a step down liquid-to-liquid regulator may be used so that the output pressure of the fuel may be regulated to about 40 psi or so, with the fuel lines carrying this lower pressure being thermally insulated so that the lower-pressure fuel is maintained in a chilled and liquid state. Any vapor developed in the fuel lines may be returned to the tank. In this instance, a standard fuel injector or similar metering valve may be used to dispense the chilled liquid fuel. Operation would be the same as with gasoline, with a portion of the liquid fuel flashing into vapor, saturating the environment of the STAR TUBE™ with hydrocarbon gas and further cooling the fog of droplets, stabilizing the droplets and retarding further evaporation of the droplets until they are burned.
As should be apparent from Applicant's disclosure, there are many ways in which an integral unit containing a STAR TUBE™ and fuel injector or fuel valve, or other droplet generator such as those earlier described, may be configured, either with or without a discrete air/gas reservoir. Also, the size of the reservoir and distance between the Star plates may be adjusted to a set size and distance so as to take advantage of a particular RPM range of an engine, or may be adjustable “on the fly” so as to be adjustable throughout an engine's RPM range in order to assist or facilitate broadening a power band of the engine. Such variations or adjustment of the reservoir size and/or distance between the Star plates may be in accordance with harmonics or resonance of the air column within the star tube, and possibly in conjunction with resonance of the reservoir, to make gas flow through the star tube more efficient, enhance fuel flow or to increase or decrease gas pressure spikes in the STAR TUBE™ and reservoir (where used). Such tuning would generally be similar to tuning of exhaust systems in order to make air flow through the engine more efficient.
Having thus described my invention and the manner of its use, it should be apparent to those skilled in the arts to which my invention pertains that incidental changes may be made thereto that fairly fall within the scope of the following appended claims, wherein I claim:
This application is a continuation-in-part of pending PCT application number PCT/US03/08635, filed 19 Mar. 2003, which claims priority from pending U.S. patent application Ser. No. 10/101,250, filed 19 Mar. 2002.
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/US2004/002186 | 1/27/2004 | WO | 00 | 9/19/2005 |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2004/094810 | 11/4/2004 | WO | A |
| Number | Name | Date | Kind |
|---|---|---|---|
| 1382285 | Harris | Jun 1921 | A |
| 1874002 | Fantz | Aug 1932 | A |
| 1885559 | Smith | Nov 1932 | A |
| 3326538 | Merritt | Jun 1967 | A |
| 3334657 | Smith et al. | Aug 1967 | A |
| 3336017 | Kopa | Aug 1967 | A |
| 3388868 | Watson et al. | Jun 1968 | A |
| 3393984 | Wisman | Jul 1968 | A |
| 3544290 | Larson, Sr. et al. | Dec 1970 | A |
| 3664818 | Kramer | May 1972 | A |
| 3981946 | Soya et al. | Sep 1976 | A |
| 4044077 | Gupta | Aug 1977 | A |
| 4080700 | Muller | Mar 1978 | A |
| 4092966 | Prosen | Jun 1978 | A |
| 4106459 | Asai et al. | Aug 1978 | A |
| 4123481 | Herold et al. | Oct 1978 | A |
| 4176634 | Martin | Dec 1979 | A |
| 4177780 | Pellerin | Dec 1979 | A |
| 4244821 | Molvar | Jan 1981 | A |
| 4307697 | Ong | Dec 1981 | A |
| 4359997 | Lyssy | Nov 1982 | A |
| 4370304 | Hendriks et al. | Jan 1983 | A |
| 4399794 | Gagnon | Aug 1983 | A |
| 4443335 | Gullace | Apr 1984 | A |
| 4487553 | Nagata | Dec 1984 | A |
| 4515734 | Rock et al. | May 1985 | A |
| 4568500 | Rock et al. | Feb 1986 | A |
| 5054688 | Grindley | Oct 1991 | A |
| 5113945 | Cable | May 1992 | A |
| 5431346 | Sinaisky | Jul 1995 | A |
| 5472645 | Rock et al. | Dec 1995 | A |
| 5480589 | Belser et al. | Jan 1996 | A |
| 5512216 | Rock et al. | Apr 1996 | A |
| 5672187 | Rock et al. | Sep 1997 | A |
| 6010083 | Roe et al. | Jan 2000 | A |
| 6113078 | Rock | Sep 2000 | A |
| 6283460 | Omarsson | Sep 2001 | B1 |
| 6540210 | Satterfield | Apr 2003 | B2 |
| 6736376 | DeLisle | May 2004 | B1 |
| 7093826 | DeLisle | Aug 2006 | B2 |
| 7111829 | DeLisle | Sep 2006 | B2 |
| 7111830 | DeLisle | Sep 2006 | B2 |
| Number | Date | Country |
|---|---|---|
| 1 143 728 | Feb 1997 | CN |
| 2083554 | Mar 1982 | GB |
| WO 9748897 | Dec 1997 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 20060175719 A1 | Aug 2006 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | PCT/US03/08635 | Mar 2003 | US |
| Child | 10549726 | US |
