Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M67/00—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type
  • F02M67/02—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type the gas being compressed air, e.g. compressed in pumps
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B19/00—Engines characterised by precombustion chambers
  • F02B19/10—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder
  • F02B19/1004—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder details of combustion chamber, e.g. mounting arrangements
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/22—Fuel supply systems
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M15/00—Carburettors with heating, cooling or thermal insulating means for combustion-air, fuel, or fuel-air mixture
  • F02M15/02—Carburettors with heating, cooling or thermal insulating means for combustion-air, fuel, or fuel-air mixture with heating means, e.g. to combat ice-formation
  • F02M15/025—Fuel preheating
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M17/00—Carburettors having pertinent characteristics not provided for in, or of interest apart from, the apparatus of preceding main groups F02M1/00 - F02M15/00
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M19/00—Details, component parts, or accessories of carburettors, not provided for in, or of interest apart from, the apparatus of groups F02M1/00 - F02M17/00
  • F02M19/03—Fuel atomising nozzles; Arrangement of emulsifying air conduits
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M29/00—Apparatus for re-atomising condensed fuel or homogenising fuel-air mixture
  • F02M29/04—Apparatus for re-atomising condensed fuel or homogenising fuel-air mixture having screens, gratings, baffles or the like
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M31/00—Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture
  • F02M31/02—Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture for heating
  • F02M31/16—Other apparatus for heating fuel
  • F02M31/18—Other apparatus for heating fuel to vaporise fuel
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M43/00—Fuel-injection apparatus operating simultaneously on two or more fuels, or on a liquid fuel and another liquid, e.g. the other liquid being an anti-knock additive
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M51/00—Fuel-injection apparatus characterised by being operated electrically
  • F02M51/06—Injectors peculiar thereto with means directly operating the valve needle
  • F02M51/061—Injectors peculiar thereto with means directly operating the valve needle using electromagnetic operating means
  • F02M51/0625—Injectors peculiar thereto with means directly operating the valve needle using electromagnetic operating means characterised by arrangement of mobile armatures
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M51/00—Fuel-injection apparatus characterised by being operated electrically
  • F02M51/06—Injectors peculiar thereto with means directly operating the valve needle
  • F02M51/061—Injectors peculiar thereto with means directly operating the valve needle using electromagnetic operating means
  • F02M51/0625—Injectors peculiar thereto with means directly operating the valve needle using electromagnetic operating means characterised by arrangement of mobile armatures
  • F02M51/0664—Injectors peculiar thereto with means directly operating the valve needle using electromagnetic operating means characterised by arrangement of mobile armatures having a cylindrically or partly cylindrically shaped armature, e.g. entering the winding; having a plate-shaped or undulated armature entering the winding
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M53/00—Fuel-injection apparatus characterised by having heating, cooling or thermally-insulating means
  • F02M53/04—Injectors with heating, cooling, or thermally-insulating means
  • F02M53/06—Injectors with heating, cooling, or thermally-insulating means with fuel-heating means, e.g. for vaporising
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M57/00—Fuel-injectors combined or associated with other devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M61/00—Fuel-injectors not provided for in groups F02M39/00 - F02M57/00 or F02M67/00
  • F02M61/16—Details not provided for in, or of interest apart from, the apparatus of groups F02M61/02 - F02M61/14
  • F02M61/18—Injection nozzles, e.g. having valve seats; Details of valve member seated ends, not otherwise provided for
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M67/00—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type
  • F02M67/02—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type the gas being compressed air, e.g. compressed in pumps
  • F02M67/04—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type the gas being compressed air, e.g. compressed in pumps the air being extracted from working cylinders of the engine
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M67/00—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type
  • F02M67/06—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type the gas being other than air, e.g. steam, combustion gas
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M67/00—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type
  • F02M67/14—Apparatus in which fuel-injection is effected by means of high-pressure gas, the gas carrying the fuel into working cylinders of the engine, e.g. air-injection type characterised by provisions for injecting different fuels, e.g. main fuel and readily self-igniting starting fuel
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
  • F02M69/04—Injectors peculiar thereto
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
  • F02M69/04—Injectors peculiar thereto
  • F02M69/047—Injectors peculiar thereto injectors with air chambers, e.g. communicating with atmosphere for aerating the nozzles
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M2200/00—Details of fuel-injection apparatus, not otherwise provided for
  • F02M2200/60—Fuel-injection apparatus having means for facilitating the starting of engines, e.g. with valves or fuel passages for keeping residual pressure in common rails
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M61/00—Fuel-injectors not provided for in groups F02M39/00 - F02M57/00 or F02M67/00
  • F02M61/14—Arrangements of injectors with respect to engines; Mounting of injectors
  • F02M61/145—Arrangements of injectors with respect to engines; Mounting of injectors the injection nozzle opening into the air intake conduit
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
  • F02M69/04—Injectors peculiar thereto
  • F02M69/042—Positioning of injectors with respect to engine, e.g. in the air intake conduit
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
  • F02M69/30—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel characterised by means for facilitating the starting-up or idling of engines or by means for enriching fuel charge, e.g. below operational temperatures or upon high power demand of engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
  • F02M69/00—Low-pressure fuel-injection apparatus ; Apparatus with both continuous and intermittent injection; Apparatus injecting different types of fuel
  • F02M69/46—Details, component parts or accessories not provided for in, or of interest apart from, the apparatus covered by groups F02M69/02 - F02M69/44
  • F02M69/462—Arrangement of fuel conduits, e.g. with valves for maintaining pressure in the pipes after the engine being shut-down
  • F02M69/465—Arrangement of fuel conduits, e.g. with valves for maintaining pressure in the pipes after the engine being shut-down of fuel rails
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T10/00—Road transport of goods or passengers
  • Y02T10/10—Internal combustion engine [ICE] based vehicles
  • Y02T10/12—Improving ICE efficiencies

Definitions

• This invention relates generally to fuel delivery systems, and particularly to a fuel delivery system including a : fuel nozzle incorporating a closed STAR TUBETM, the system providing a fog of fuel dr plets : sized 50 microns and less, and predominantly in the 10 ⁇ - 30 micron range, while minimizing vapor formation.
• apparatus 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.
• 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.
• 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 TUBETM 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.
• a generally confined tube designated as a STAR TUBETM for purposes of this application
• 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.
• 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 TUBETM.
• the fuel is then processed mechanically by turbulence-inducing devices in the STAR TUBETM 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.
• Engines such as Diesel or other direct injection engines may also benefit from fuel processed into droplets sized 50 microns and less.
• 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.
• combustion properties allow a more stoichiometric proportion of Diesel fuel/air to be used.
• 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.
• Fig. 1 is a diagrammatic view of the fuel delivery system of the present invention in its operating environment.
• Fig. la is a diagrammatic view showing particulars of construction related to a different embodiment of the present invention.
• Fig. lb is a diagrammatic view showing particulars of construction related to another embodiment of the present invention.
• Fig. 2 is a cut-away view of one embodiment of a "STAR TUBETM" of the present invention.
• Fig. 2a is a view of an end of a STAR TUBETM that receives a fuel injector.
• Fig. 2b is a cut-away view showing particulars of another embodiment of the invention.
• Fig. 3 is a top view of a Star Spin and Shear plate of the present invention.
• Fig. 4 is a side view of the Star Spin and-Shear Plate as shown in Fig. 3.
• Fig. 5 is a cut-away view of a Star Spin and Shear plate illustrating particulars of operations.
• Fig. 6 is a cut-away, diagrammatic view of a cylinder and combustion chamber of a Diesel engine fitted with a STAR TUBETM of the instant invention.
• Fig. 7 is an embodiment of the invention integrating a STAR TUBETM, air reservoir and a fuel metering valve into a single, integral unit.
• Fig. 7a is another embodiment of the invention integrating a STAR TUBETM, a smaller air reservoir and a fuel metering system into a single integral unit.
• Fig. 7b is yet another embodiment of the invention integrating a STAR TUBETM 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 TUBETM.
• Fig. 8 is a diagrammatic illustration of how a STAR TUBETM may be fitted to a jet engine.
• Fig. 8a is a diagrammatic illustration of another way a STAR TUBETM 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.
• droplets of a fog are known to be particularly stable, with diffusion being the primary way droplets dissipate.
• 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.
• a throttle body or intake manifold 1 is provided with any device 2 capable of receiving liquid fuels from a fuel tank 3 and associated fuel pump 4 and processing the fuel into droplets about 50 microns and less in diameter.
• Droplets larger than about 50 microns or so may be returned to tank 3 via line 6. Such oversize droplets may be isolated by centrifugal force in a vortex or other controlled flow path, or screens having a mesh sized to pass the smaller droplets but trap the larger droplets may also be used.
• a fog of fuel droplets of 50 microns and less burns faster and cleaner than a spray as provided by a conventional fuel injector or carburetor, but yet in a controlled manner.
• a fuel fog unexpectedly prevents detonation of lower octane fuels in higher compression engines requiring higher octane fuels, as will be further described.
• 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 SIMPLEXTM 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 TUBETM of Applicant's design.
• devices such as the NEBUROTORTM 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.
• these devices may be mounted within some form of tube or housing communicating with the induction air flow.
• Applicant's STAR TUBETM 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.
• 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 TUBETM.
• a gas used as a carrier or vehicle to transport and process the droplets through a STAR TUBETM.
• a product is formed from binary compounds, with one of the compounds being a liquid and the other being a gas or vapor.
• STAR TUBETM 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.
• the gas and liquid precursor may be applied through a STAR TUBETM 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 TUBETM were measured by a test rig wherein a STAR TUBETM 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.
• 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 TUBETM 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.
• 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.
• a fuel pump may be particularly applicable to a turbine or other type jet engine.
• 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.
• the spinning or spiral path creates centrifugal force on the fuel droplets, forcing them radially outward in the STAR TUBETM where they pass through narrower portions of the slits between the vanes were turbulence is greater, tearing the larger droplets into smaller droplets.
• 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.
• the mixture may have an induced spin about the axis of the STAR TUBETM, as well as turbulent spin from passing through the vanes.
• 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.
• 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.
• 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 TUBETM during operation. Such cooling retards further evaporation of the fuel droplets, and stabilizes the fuel fog as it passes through the STAR TUBETM. 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 TUBETM. 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.
• 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.
• 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.
• 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.
• 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.
• an aftermarket or OEM manifold may be provided with provisions to house the fuel injectors and a respective STAR TUBETM 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 TUBETM.
• 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 TUBETM to compensate for changes in induction air flow, as when the accelerator pedal is depressed to a greater or lesser degree.
• a computer such as an engine controller
• mechanical linkages coupled to valving apparatus may be employed for such increases and decreases in the motive flow through the STAR TUBETM.
• Fig. la illustrates, by way of example, one possible embodiment of a STAR TUBETM 10.
• the STAR TUBETM 10 is mounted between a conventional fuel injector 12 and injection port 14 in a throttle body 16 (dashed lines) or in a port of an intake manifold of an internal combustion engine near a respective intake valve, or in the case of a two- stroke engine an intake port.
• a fuel injector 12 is fitted to injection port 14 so as to provide a spray of fuel to induction air, as indicated by arrows 18, flowing through the throttle body and intake manifold.
• one end B of STAR TUBETM 10 is configured as a fuel injector port to receive the injection end of a fuel injector 12, with the other end A of the STAR TUBETM configured as a fuel injector tip so as to be mountable in the fuel injection port 14 that otherwise would receive the fuel injector.
• these ports are typically located in the intake manifold proximate to a respective intake port or valve, with the fuel injector body mounted outside the intake manifold.
• the STAR TUBETM may be configured at this end A as a fuel injector to fit the fuel injector port, and be configured at the other end B as a fuel injector port so as to receive the injecting end of a fuel injector.
• a portion of the induction air may be directed and routed through the STAR TUBETM so as to create a motive airflow therethrough, or a carrier gas may be provided independently of the induction air flow.
• This carrier gas may be separate from the induction airflow, and may be an inert gas such as dry nitrogen or filtered atmospheric gases, or a combustible gas such as propane or butane.
• the carrier gas may be or include an oxidizing gas such as nitrous oxide, which may be supplied through the STAR TUBETM, this flow being of a sufficiently high rate so as to generate turbulence to mechanically break the fuel droplets into smaller droplets having a size within the predetermined range as described above, and expel the fuel particles from the STAR TUBETM.
• an oxidizing gas such as nitrous oxide
• the gas flow may be continuous, or pulsed ON and OFF by using the ON-OFF signals provided to the fuel injectors, possibly with a short delay to allow the fuel droplets to clear the STAR TUBETM.
• the portion of induction air flow may be switched ON and OFF corresponding with the fuel bursts from the fuel injectors.
• a supply of gas 22 may be coupled to closed STAR TUBEsTM via a metering valve 24 and may be energized ON and OFF responsive to signals to the fuel injectors.
• An annular hollow collar 20 receives the gas from valve 24, and may be simply left open on a bottom side thereof, or may be provided with interior openings O that communicate with an upper interior end of the STAR TUBETM.
• An injector 12 sealably fits in the opening of the annular collar 20 and communicates with an interior of the STAR TUBETM.
• valve 24 may be operated to release a burst of gas in conjunction with the fuel injector being energized to release a spray of fuel.
• the gas may simply flow continuously through the STAR TUBETM in conjunction with a continuously metered flow of fuel from the fuel nozzle of the jet engine.
• the fuel supply 250 is coupled to a fuel pump 252, which provides the jet fuel to a STAR TUBETM 254 that may be configured generally as described for Fig. lb, except the STAR TUBETM construction is optimized for turbine and jet engines and constructed of materials consistent with jet engine design.
• STAR TUBETM 254 may be mounted in combustion chamber 256 generally where the fuel nozzle for the jet engine would be located.
• a small amount of compressor bleed air may be taken from the compressor portion 258 of the jet engine and applied through the STAR TUBETM as a carrier gas a shown in Fig. lb.
• a STAR TUBETM for each fuel nozzle.
• a different source of compressed gas such as ram air, may also be used.
• a gas having beneficial or selected properties such as nitrous oxide, may temporarily be used as all or some of the carrier gas to provide a temporary boost in power, or a gas that would temporarily reduce or eliminate pollution may be temporarily included in the carrier gas to promote more complete combustion in locations where pollution from a jet engine is a problem.
• certain liquids that would flash into a vapor upon being exposed to heat from the combustion chamber may be used to develop a carrier gas.
• gases or liquids, such as water that may have beneficial properties may also be used, either continuously or on a temporary basis.
• the proportion of gas to fuel in a jet or turbine engine would be such that the fuel/ air proportion is too rich to burn inside the STAR TUBETM and would produce a dense fog of jet fuel that would burn more efficiently and completely than can be accomplished by current methods of jet fuel management in a jet engine.
• an optimum droplet size may be different for jet or turbine engines than for sparked ignition engines.
• droplet size may be adjusted for a jet or turbine engine by providing a larger STAR TUBETM with more or fewer Star Spin and Shear plates and adjusting size of the central opening and slits.
• STAR TUBETM with more or fewer Star Spin and Shear plates and adjusting size of the central opening and slits.
• Such sizing of the Star plates and tubes is true for other engines and fuels.
• smaller slits and more Star plates develops smaller fuel droplets, while larger slits and fewer plates produce larger droplets.
• a rate of carrier gas flow through a STAR TUBETM affects droplet size, with faster flow producing smaller droplets and slower flow producing larger droplets.
• Fig. 8a illustrates a STAR TUBETM 254 installed in a jet engine wherein the STAR TUBETM is closed to external carrier gas.
• the fuel flows through a heater 260, which may be heated by combustion temperatures in the burn chamber 256 of the jet engine. So heated, a portion of the fuel flashes into vapor when applied to the STAR TUBETM, providing a carrier gas that processes the remainder of the liquid fuel passing through the STAR TUBETM.
• 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 TUBETM.
• a partial vacuum in the intake manifold that is felt by the volume of air in the STAR TUBETM.
• air and fuel vapor along with fuel droplets from the fuel injector, are drawn outward, pulling and processing the fuel droplets through the STAR TUBETM.
• the partial vacuum dissipates, allowing air in the intake manifold to re-enter the STAR TUBETM.
• 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 TUBETM need be mounted between each fuel injector and its respective port.
• the STAR TUBETM and fuel injectors assemblies are mounted and supported by brackets or other similar structure (dashed lines in Fig. la), as should be apparent to one skilled in the art.
• a STAR TUBETM 10 may be mounted in the throttle body or intake manifold 16 between a respective fuel injector and an associated injector port.
• the liquid fuel is pumped by low-pressure fuel pump 26 in a fuel tank to a high- pressure fuel pump 28, on the order of about 30 PSI or so, which conventionally develops fuel pressure and flow as shown to the fuel injectors 12.
• injectors 12 produce bursts of fuel spray as controlled by an engine controller (not shown), which determines both duration and timing of the bursts of fuel.
• bursts of fuel spray are fed directly into STAR TUBEsTM 10 where the fuel spray is processed into a fuel fog of smaller droplets of 50 microns and less in diameter, and subsequently fed into the throttle body, intake manifold or any other regions in which fuel would be appropriately injected. Induction air and the fuel fog as developed by the STAR TUBETM is then drawn into a combustion chamber (not shown).
• the fuel feeding the fuel injectors may be conventionally regulated to a constant pressure by fuel pressure regulator 30, which relieves excess pressure by controllably bleeding high-pressure fuel via return line 32 to fuel tank 34 as shown by arrow 36, along with any vapor that has formed within the high-pressure feed line or fuel rail.
• Fig. 1 may be substituted for the STAR TUBETM 10, preferably within a closed environment communicating with the induction air flow.
• Fig. 2 shows a cross section of one of STAR TUBEsTM 10.
• a cap as shown enlarged in Fig. 2a, or other closure 40 may be configured with an opening 41 that may be tapered to match a taper of fuel injection end 38.
• a plurality (9 shown) of openings O Positioned in cap 40 around injection end 38 are a plurality (9 shown) of openings O, which may be sized to handle air flow through the STAR TUBETM for a particular engine. While a plurality of openings O are disclosed, other sizes and types of openings are also workable.
• a single, annular opening 37 around end 38 of fuel injector 12 may be provided, possibly out to the inner diameter of the STAR TUBETM, or a smaller number of openings O may be constructed in end B of the STAR TUBETM. Also as described, the openings may also be omitted, with the injector and cap sealed to form a closed end to the STAR TUBETM.
• the volume of the interior of the STAR TUBETM forms a gas and fuel vapor reservoir that provides a motive flow responsive to suction developed by a piston on its intake stroke, and the lighter components of fuel flashing into vapor.
• the STAR TUBETM diameter may be enlarged, or the length extended, so as to create a larger gas/vapor reservoir within the volume of the STAR TUBETM.
• a STAR TUBETM constructed for use in a 350 cubic inch displacement engine is shown.
• the fuel injectors and STAR TUBEsTM are mounted and supported by brackets (schematically illustrated by dashed lines) so that there is a STAR TUBETM mounted between each fuel injector and fuel injector port.
• the embodiments of the STAR TUBESTM that utilize a portion of the induction air flow as carrier gas perform better when mounted in a throttle body due to the fact that the low-pressure pulses developed by intake strokes of the pistons are attenuated because of the distance between the intake valves and the throttle body.
• a closed STAR TUBETM and associated fuel metering valve located proximate an intake valve may function well because the low-pressure pulse associated with an opening intake valve is more strongly felt by the liquid fuel/gas in the STAR TUBETM.
• Fig. 2 One STAR TUBETM that has been found to work well for the aforementioned 350 cubic inch engine is shown in Fig. 2.
• the tube portion 42 is about 1.5 inches outside diameter and about 1 inch inside diameter and about three to four inches long.
• Cap 40 is provided with a plurality (9 shown) of openings O around a periphery of the cap, these openings O each being about 0.187 inch in diameter.
• a central opening 44 in cap 40 is about 0.5 inch in diameter to receive the fuel injector end 38.
• the injector body would be supported exterior of the STAR TUBETM so that end 38 is generally coaxially positioned with respect to the STAR TUBETM.
• 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 TUBETM.
• the STAR TUBETM may be constructed of thinner material.
• the spray of fuel from the fuel injector is initially introduced into the STAR TUBETM 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.
• 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 TUBETM 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 Fig. 2. Further, in the event a plate inadvertently loosens within a STAR TUBETM, an end of the STAR TUBETM closest to the intake manifold ports or throttle body port may be slightly narrowed or otherwise constructed so that the Star Spin and Shear plate is not drawn into the intake manifold.
• the Star Spin and Shear plates 46 each have a plurality of types of openings (Fig. 3), these openings being a central opening 50 of about 0.5 inches in diameter and a plurality, in this instance 6, of narrowing spoke-like slits or openings 52 communicating with and radially extending from central opening 50.
• openings 52 may be initially relatively wide at central opening 50, and converge with distance from central opening 50 to a point 54 radially positioned at approximately 50 percent to 85 percent or so of a diameter of the plates 46.
• a ratio of the diameter of plate 46 with respect to central opening 50 may be about 3 to 1, but a range of about 1.5 to 1 or so up to about 5 to 1 has been discovered to be workable.
• Figs. 3 - 5 also illustrate a downwardly depending vane 56 positioned on edges of each of openings 52.
• Vanes 56 may be downwardly angled, as shown in Figs. 4 and 5, at about from a few degrees to almost 90 degrees from a plane of the plate. However, in one contemplated embodiment that works well, a vane angle of about 40 degrees is used.
• Vanes 56, in conjunction with an opposed edge 58 of openings 52 serve to provide edges 60 (Fig. 5) that create turbulence when the airflow passes through a respective opening 52. This turbulence shears and breaks up larger fuel droplets into smaller droplets as the flow passes through successive star plates 46 until a desired droplet size of about 50 microns is reached.
• vanes may be angled either upward or downward, with approximately equal performance with respect to breaking up larger droplets into smaller droplets.
• rotation imparted by downwardly extending vanes causes axial spin of fuel/ air mixture through the STAR TUBETM
• upwardly extending vanes also creates spin through the STAR TUBETM, in addition to the aforementioned shearing action around edges of openings 52.
• Star Spin and Shear plate 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.
• the Star Spin and Shear plates were replaced with conventional flat washers having only a central opening.
• 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.
• the Star Spin and Shear plates were replaced with TENON-type quick-connect nuts, which are configured similarly to the Star plates.
• 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.
• 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.
• 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 TUBEsTM and Star plates may be scaled as necessary depending on displacement of the engine and number of fuel injector/ STAR TUBETM 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.
• the fuel injector simply serves as a variable fuel metering valve responsive to the engine controller.
• the fuel injector may be replaced with a simple metering valve that provides the required amount of fuel, and generally as a spray or stream, to a STAR TUBETM responsive to a signal from the engine controller, with the STAR TUBETM breaking up the fuel into droplets of the predetermined size of about 50 microns and less.
• the carrier gas passing through all the STAR TUBEsTM 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.
• 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.
• 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.
• 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.
• lighter fuels such as gasoline
• STAR TUBETM 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 TUBETM so that further evaporation of the remaining heavier-component fuel droplets is prevented.
• 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 TUBEsTM. 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.
• Tube ID 13/ 16 in.
• Tube OD 1 1/4 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.
• the STAR TUBEsTM 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.
• engine runs were from 5000 rpm down to 2500 rpm, with data readings taken by conventional engine monitoring equipment.
• Peak torque was always equal to or better with STAR TUBESTM 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 TUBESTM is indicative that the 80 octane fuel fog burns faster than the C-12.
• a ROTORWAYTM helicopter engine in a helicopter was modified with STAR TUBEsTM and extensively tested.
• the tubes were similar to the ones used in the ChevroletTM engine as described, except were closed to any external carrier gas.
• the gasoline feed region of the STAR TUBETM serves as a gas/vapor reservoir.
• the ROTORWAYTM 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 TUBETM mounted in each fuel injector port.
• the fuel injector was then mounted at the other end of the STAR TUBETM, and as stated, closed to any external source of carrier gas so that there was a small air reservoir approximately %" - 1" or so between the fuel injector tip and the first Star plate.
• the ROTORWAY engine equipped with STAR TUBEsTM produced over 200 horsepower, as opposed to 145 horsepower for a full power test of the conventional version of the engine.
• the ROTORWAY helicopter equipped with STAR TUBEsTM used slightly under three gallons of gasoline at a 1/3 power throttle setting, as compared to the same helicopter without STAR TUBEsTM which used four gallons of gasoline at a 2/3 power throttle setting in the same 30 minute hover test.
• the embodiment of STAR TUBEsTM 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 TUBETM of the instant invention may also work with certain Diesel or Diesel-type engines wherein the fuel is ignited by compression.
• a swirl chamber 62 is conventionally provided in a head portion 64 of the combustion chamber, and a swirl cutout 66 is conventionally provided in a piston 68.
• a passageway 70 communicates between swirl chamber 62 and combustion chamber 72.
• a fuel injector 74 is mounted so as to inject fuel into swirl chamber 62, with a STAR TUBETM 76 of the present invention mounted in passageway 70 so as to receive fuel from injector 74 and convey a fuel fog to combustion chamber 72.
• the STAR TUBETM 76 is sized so as not to completely fill passageway 70, thus allowing some of the combustion air to bypass STAR TUBETM 76.
• the dimensions of the Star plates and STAR TUBEsTM for a Diesel engine may be adjusted to obtain a different particle size if a particle size other than less than 50 microns is found to be optimal. Operation of the embodiment of Fig. 6 is as follows. During the compression stroke, essentially all of the combustion air is compressed into the swirl chamber. At the appropriate time, which is typically 2 degrees or so before top dead center for a Diesel engine, fuel is injected into the STAR TUBETM.
• the engine may be started by means of a conventional glow plug 80 positioned below STAR TUBETM 76.
• a combined fuel injector or fuel nozzle and STAR TUBE form an integral assembly 200 that is more compact in length than a sealed fuel injector and STAR TUBETM combined as described above. This is accomplished by moving the fuel nozzle or other fuel-supplying orifice 212 up into assembly 200 to a point near a fuel rail 230.
• a STAR TUBETM 208 is mounted to receive, at one end, fuel from the fuel port or nozzle 212, with the other end of the STAR TUBETM configured to be mountable into a fuel injector port 238 of an intake manifold or throttle body 236.
• the assembly 200 is conventionally sealed at fuel rail 230 and at port to 38, as by O-rings 209.
• an air/ vapor reservoir 216 may be provided and which is sealably coupled to a top of STAR TUBETM 208, with nozzle or tube 212 extending as shown therethrough to a point near an entrance of the STAR TUBETM.
• tube 212 and the reservoir 216 may be shortened or omitted entirely in order to shorten the assembly 200, with fuel provided directly from the metering valve into the STAR TUBETM.
• Such an embodiment may be used in conjunction with heating the fuel to develop vapor that serves as a carrier gas, as will be further explained.
• 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 TUBETM 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.
• armature 218 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 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.
• fuel rail 230 provides fuel to the interior of housing 202 via opening 232, from which pressurized fuel flows to opening 226.
• 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.
• 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 TUBETM, with or without an air reservoir, and all as a single, integral, compact unit.
• 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.
• 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 TUBETM and out port 238.
• 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 TUBETM 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 TUBETM.
• an external supply of gas or air need not be provided to the STAR TUBETM, and the entire assembly 200 may be constructed in a more compact form, possibly a short as the length of a conventional fuel injector.
• 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.
• the lighter- component, fuel saturated environment in the reservoir assists in preventing further evaporation of the heavier-component fuel droplets.
• the newly formed fuel vapor displaces any fuel vapor remaining in the STAR TUBETM along with the heavier-component droplets.
• Figs. 7a and 7b each show an integral device similar to that of Fig. 7, except that in Fig. 7a the reservoir is narrower and in-line with the STAR TUBE. In Fig. 7b, there is only a very small or no reservoir, the STAR TUBETM being directly below a fuel valve. This embodiment is functionally the same as was tested in the ROTORWAYTM helicopter. In addition to the designs described herein, it should be apparent from Applicant's disclosure to one skilled in the art that the combined fuel nozzle/ STAR TUBETM may take many forms.
• a fuel-dispensing tube may extend generally perpendicular into the STAR TUBETM, or at an angle over the top of the STAR TUBETM, to inject liquid fuel at a point just over the first Star Plate.
• the closed gas/vapor reservoir over the top of the STAR TUBETM would provide carrier gas and vapor as described on the intake stroke, or the fuel may be heated to flash some of the fuel into a vapor to provide carrier gas.
• a fuel injector nozzle may be mounted adjacent a top of the STAR TUBETM to dispense fuel into a top of the STAR TUBETM and in a direction generally perpendicular to the STAR TUBETM.
• the fuel injector portion may be fabricated alongside the STAR TUBETM so the assembly would be wider and shorter than the embodiments of Figs. 7, 7a and 7b.
• a tube or nozzle may also be extended to direct fuel approximately coaxially into the STAR TUBETM.
• a small heater or heating element 205 located or mounted to an exterior upper region of assembly 204 so as to heat liquid fuel just prior to the fuel passing through the needle valve. This or a similar embodiment may be used in cold environments where less fuel flashes into vapor that otherwise would reduce carrier gas flow through the STAR TUBETM.
• a heater such as heater 205 may be used continuously at a colder, higher altitude, and switched OFF at lower, warmer altitudes.
• a heater may be used in a ground vehicle travelling between cold and warm climates.
• such a heater may initially be used when starting a cold engine in order to develop more carrier gas/vapor, which in turn causes more flow through the STAR TUBETM that breaks cold liquid fuel into smaller droplets that are easier to ignite.
• STAR TUBETM breaks cold liquid fuel into smaller droplets that are easier to ignite.
• such heating of the fuel may be beneficial in engines fueled by heavier fuels that do not readily flash into vapor, such as jet fuel, in order to cause more of the fuel to flash into vapor or otherwise cause the fuel to be easier to ignite.
• the fuel may be heated continuously, or heated only as needed to effect faster burning of fuel with little or no pollutant generation.
• a heater is shown within the assembly 200 of Fig. 7b, it should be apparent from Applicant's disclosure to one skilled in the art that several embodiments that include heating of the fuel may be implemented.
• the entire assembly 200 may be insulated and heated as by wrapping an external heating element around the assembly, or the fuel may be heated in the fuel rail or in a connecting region between the fuel rail and assembly 200.
• the larger volume of fuel within assembly 200 may be heated, as by providing a heating element near solenoid 222, or a heating element may be incorporated in solenoid 222.
• tube 212 may be heated to flash a portion of the fuel into vapor to develop carrier gas, or the STAR TUBETM portion itself may be heated to flash a portion of the fuel to vapor.
• some or all the fuel may be sprayed directly from the fuel metering valve directly onto a heated screen, perforated plate or similar heater 207 to evaporate a portion of the fuel to develop carrier gas just prior to processing a remainder of the liquid fuel through the STAR TUBETM.
• cryogenic fuels such as liquefied propane or liquefied natural gas, and possibly hydrogen
• 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.
• 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 TUBETM with hydrocarbon gas and further cooling the fog of droplets, stabilizing the droplets and retarding further evaporation of the droplets until they are burned.
• an integral unit containing a STAR TUBETM 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.
• 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 TUBETM 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.

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• Electromagnetism (AREA)
• Fuel-Injection Apparatus (AREA)

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• 2004
  • 2004-01-27 CA CA002519355A patent/CA2519355A1/en not_active Abandoned
  • 2004-01-27 WO PCT/US2004/002186 patent/WO2004094810A1/en active Application Filing
  • 2004-01-27 CN CNB2004800074601A patent/CN100434686C/zh not_active Expired - Fee Related
  • 2004-01-27 AU AU2004233193A patent/AU2004233193A1/en not_active Abandoned
  • 2004-01-27 EP EP04705614A patent/EP1611337A4/de not_active Withdrawn

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