LIQUID FUEL SYSTEM METHOD AND APPARATUS

Abstract: System for improving performance of spark ignition, internal combustion engines using fuels such as liquified petroleum gas (LP-gas), which have conventionally been stored as a liquid and delivered to the engine as a vapor. This system stores such fuels as liquids (10) and delivers the fuel to the engine inlet air stream as a liquid. The absorption of heat by the vaporizing fuel lowers engine inlet air temperature, increasing its density and permitting more fuel to be burned in each cycle. Vaporizing heat in a pilot line (17) provides the cooling to the liquid fuel in the main fuel line (20) and provides fuel to maintain the engine idling. A member (27) slides within a fuel delivery chamber (25) for covering or uncovering a series of orifices (26) through which the liquid fuel passes into the inlet air stream of the engine.

Description: Description Liquid Fuel System Method and Apparatus Technical Field The invention relates to the field of fuel delivery to engines. Background Art Internal combustion engines have been run at one time or another, on nearly every conceivable fluid fuel. Fluid is used here to describe both liquid and gaseous fuel. The principal fuels in current and past practice are in the liquid, vapor or gaseous phase at normal environmental temperatures and within the normal commercial transportation pressure limits (1 to 200 atmospheres) . Fuels of commercial significance fall conveniently into three categories with respect to the locations of their phase transitions. They are so labeled and described as follows: 1. Liquid Fuel. Liquid at atmospheric pressure and normal climatic tempera¬ tures (-40°F. to 120°F.). Examples are gasoline, diesel fuel and alcohol. 2. Vapor Fuel. Vapor at atmospheric pressure and normal climatic tempera¬ tures (-40°F. to 120°F.) but liquid under elevated (2 to 200 atmospheres) pressures. Generally this corresponds to a critical temperature in excess of 100°F. Critical temperature is the highest temperature at which a vapor CV.7 can be condensed by isothermal compres¬ sion. Examples are gas, (propane, butane, etc.) . 3. Gas Fuel. Gas at atmospheric and elevated pressures, and normal climatic temperatures. Generally this corre¬ sponds to a critical temperature less than -40°F. Examples are hydrogen, methane, natural gas, etc. Fuels that remain liquid throughout normal ambient conditions (Type 1 above) are stored and delivered as liquids. Gaseous fuels (Type 3), which cannot be liquified by pressure alone at normal ambient temperatures are stored and delivered as gases. Vapors (Type 2) which may be liquified by high pressures, at ambient temperatures, are generally stored as liquids and delivered as vapors. Internal combustion engines initiate fuel burning within the cylinder in two general ways and are classified accordingly. 1. "Compression ignition" in which the energy of compression is such that the resultant air temperatures initiate combustion. Compression ratios in excess of 16 are common and primary fuel is injected directly into the cylinder or prechamber in order to control burning. 2. "Spark ignition" in which an electrical spark is used to start fuel burning. Fuel is generally delivered to the inlet air stream, as a liquid and partially vaporizes en route to the cylinder. Compression ignition engines may use supple- mentary equipment, such as glow plugs, for start-up (when the engine is cold) but they remain compression ignition engines. Table I summarizes past practice with respect to the types of fuel storage and delivery systems and engine types with which they are used. In no known previous patents involving a vapor fuel (Type 2) has the fuel been delivered in liquid phase to the air stream of a spark ignited engine. For compression ignition engines, vapor fuels have been used only as supplementary fuels and have generally been introduced into the air stream as a vapor. fiBLE I PAST PRACTICE IN USE OF VARIOUS FUELS IN I.C. ENGINES FUEL ENGINE IGNITION Storage Delivery Type Phase Phase Compression Spark Liquid Vapor Liquid Vapor 1. Liquid Fuel. X Examples - Ga.soline Diesel, Alcohol, etc. 2. 3. Gas Fuel. Ex-amples - Hydrogen, methane, CNG, etc. X- = Supplementary Fuel only X = U.S. Patent 2,767,691 In Table I it is evident from the blank spaces that Type 2 vapor fuels are delivered almost exclusively as vapors rather than liquid. General past practice with Type 2 vapor (fuels that can change phase at ambient temperature with pressure changes) is to store as a liquid and deliver as a vapor. In fact, to insure vaporization, most such systems have a separate* vaporizer which uses either exhaust gases or engine coolant to add heat to the fuel. Vapor is then introduced into the inlet air stream of the engine at some convenient point. As a rule, the fuel is begin¬ ning to vaporize in varying degrees from the tank on downstream to the vaporizer, after which it is required to be 100% vapor. On spark ignition engines there is no known prior practice of liquid fuel delivery for Type 2 fuel. On compression ignition engines, liquid delivery of vapor fuels was used only as a supplement to normal diesel fuel. In this latter case, the Type 2 fuel was injected into the cylinder at the beginning of compres¬ sion. In this arrangement the vaporization heat of the fuel reduces compression work, but does not improve air mass charging density. In U.S. Patent 2,767,691 to Mengelka p et al., vapor (Type 2) fuels are injected in liquid phase into a compression ignition engine after cylinder filling and as a supplementary fuel only. Mengelkamp et al. suggest that liquid delivery of vapor (Type 2) fuel, requires one of two approaches to maintaining the fuel in liquid phase: 1) increased external pressure or, 2) external cooling. In the first approach an external gas supply was used to build up pressure in the vapor fuel tank and thus drive the liquid further into the subcooling region. The second approach by heat removal involved external heat exchange such as with a cool water supply system. CMrl Vapor (Type 2) fuels are delivered primarily in vapor form and the metering devices used to modulate this flow come in every conceivable shape and configura¬ tion. Among the metering devices are those disclosed in U.S. Patents 2,443,120 to Saucier and 3,443,551 to Laubach based upon a piston uncovering successively more flow passages as it is moved axially. A variation in U.S. Patent 2,817,324 to Sievers is two concentric tubes with apertures which may be matched in varying degrees, thereby varying the flow restriction and hence the flow. In Mengelkamp, et al. , 2,767,691 the fuel was etered into the compression ignition engine by an additional injection pump. Disclosure of Invention Broadly stated, the present invention, to be described in greater detail below, is directed to a liquid fuel system method and apparatus for injecting vapor fuel under pressure in liquid phase directly into the inlet air stream of a spark ignition engine utiliz- ing vaporization of a small portion of the fuel to cool the remainder of the fuel to insure injection of a liquid. One feature and advantage of the present invention is that the heat required to vaporize the fuel is absorbed from the inlet air stream thereby lowering its temperature and increasing its density. Since the air density is greater, each charge has a greater weight of air. For any consistent stoichio- metry a greater weight* of fuel results and therefore greater power output for a given engine speed. Also, since the combustion temperatures are lower there will be .lower exhaust emission in the category, oxides of nitrogen. In accordance with another aspect of the present invention a pilot fuel line is provided for directing fuel initially in liquid phase but throttled to a reduced pressure into heat exchange with the main fuel line so that vaporizing fuel in the pilot fuel line cools fuel in liquid phase in the main fuel line thereby preventing vaporization. In a preferred embodiment of this aspect of the invention the pilot fuel line is located within, typically concentrically within, the main fuel line. In accordance with the latter aspect of the present invention vaporization of a small portion of the vapor fuel in liquid phase is utilized to cool the remainder of the fuel in liquid phase and the vaporized fuel is utilized to operate the engine in idling condition. In accordance with another aspect of the present invention a fuel system is provided including a fuel delivery adapter for securing in place along the inlet air stream of an engine and having a fuel delivery chamber with a series of liquid phase flow orifices connecting the chamber to the inlet air stream of the engine and a slidable member within the delivery chamber for progressively uncovering the series of orifices with actuator means for moving the member to cover or uncover the flow orifices for passage of fuel therethrough in response to engine fuel needs. One feature and advantage of the latter • aspect of the present invention is a uniformly con- trollable introduction of the desired amount of liquid fuel directly into the inlet air stream of the engine. Another feature and advantage of the present invention is the provision of a liquid fuel system which can be directly assembled onto an existing spark injection engine for operation of that engine more c:.:π efficiently with vapor fuel delivered to the engine in liquid phase than the conventional gasoline fuel with which the engine was initially designed to operate. In accordance with still another aspect of the present invention the orifices have a diameter in the range of .002 to .006 inches. Smaller holes offer excessive pressure drop and larger holes allow fuel to pass in large droplets which do not vaporize readily enough. In accordance with another aspect of the present invention the axes of at least certain of the orifices are arranged non-parallel with the axes of other orifices to provide fuel atomization in a very short distance into the air stream for thorough mixing of fuel and air. Other features and advantages of the present invention will become more apparent upon a perusal of the following specification taken " in conjunction with the accompanying drawings wherein similar characters of reference refer to similar structural elements in each of the several views. Brief Description of Drawings FIGURE 1 is a foreshortened schematic eleva- tional view, partially in section, illustrating certain aspects of a fuel system in accordance with the present invention. FIGURE 2 is an enlarged sectional view of a portion of the structure shown in FIGURE 1 delineated by line 2-2. FIGURE 3 is a side sectional view of a portion of the structure shown in FIGURE 1. FIGURE 4 is an enlarged sectional view of a portion of the structure shown in FIGURE 3 delineated by line 4-4. o;.π?ι FIGURE 5 is a graph of pressure plotted versus enthalpy illustrating certain aspects of the present invention. FIGURE 6 is a graph of saturated pressure plotted versus temperature illustrating other aspects of the present invention. FIGURE 7 is an elevational sectional view of an alternative embodiment of the present invention. FIGURE 8 is an exploded plan view of the structure shown in FIGURE 7. FIGURE 9 is an enlarged view of the orifices shown in FIGURE 7. Best Mode for Carrying Out the Invention The preferred embodiment of the present invention is a liquid fuel system for LP-gas maintained under pressure in liquid phase with liquid and vapor in equilibrium for direct attachment onto a spark ignition engine. Referring now to the drawing, with particular reference to FIGURE 1, there is shown a liquid fuel system in accordance with the present invention. An LP-gas fuel tank 11 is provided for storing liquid fuel 10 with liquid and vapor in equilibrium in the tank 11. Liquid fuel flows out through the discharge line 12 and into the upstream pipe tee 13 where it divides into main fuel flow through main fuel line 20 and pilot fuel flow through pilot flow connecting tube 14. Pilot fuel flows through the pilot flow connecting tube 14, the fuel lock 15 and is throttled through the orifice 16 (see FIGURE 2). The pilot fuel then flows down the pilot fuel line 17 coaxially located within the main fuel line 20 and through the downstream pipe tee 18 and out through a pilot fuel c:.;? Y.-h- line 21 to a fuel delivery adapter block 19. This adapter block 19 is constructed for positioning on a conventional spark ignition engine where the air stream and fuel is normally inducted into the engine manifold. Pilot fuel flow through the orifice 16 reduces the pressure to a point where the liquid fuel will vaporize. Vaporization takes place as the fuel in the pilot line 17 moves along the length of the main fuel line 20 and heat is transferred from the liquid fuel in the main fuel line into the pilot fuel, all along the run of both lines. Main fuel flows out of the upstream pipe tee 13, through the main fuel line 20 into the downstream pipe tee 18 and into the fuel delivery adapter block 19. The transfer of heat from the main fuel to the pilot fuel across the wall of the pilot fuel line 17 subcools the main fuel. Heat transfer into the main fuel line 20 from the surroundings may be controlled by proper design of the main fuel conduit. Since it is important for fuel metering accuracy that the main fuel flow remain totally liquid through the metering valve into the inlet air stream, the design of the liquid fuel maintenance hardware is such as to minimize local turbulence and vortices and their accompanying local pressure drop. Excessive pressure drop in the main line can cause vapor bubbles to form. Fuel metering is accomplished by introducing a variable flow impedeήce at the end of the main fuel line farthest from the fuel storage tank and nearest to the engine inlet air stream. The impedence is provided by the incremental valve schematically illustrated as 24 in FIGURE 1 and illustrated in greater detail in FIGURE 3. In addition to fuel metering, this incre- mental valve distributes and disperses the main fuel flow. Referring now to FIGURES 3 and 4, the incre¬ mental valve 24 consists of a chamber or valve cylinder 25 in the adapter block 19 (FIGURE 1) and in the walls of which are drilled a longitudinal series of flow orifices 26 which can be completely covered or progres¬ sively uncovered by movement of a piston 27 by applying a force to a piston rod 28 through an actuator mechan¬ ism in response to fuel needs. The piston 27 is provided with a pair of sealing rings 29, and the piston rod 28 is similarly provided with a seal 31 where the rod extends through an apertured end wall 32 of the cylinder. Pressure equalizing ports 33 are provided through the piston 27 to equalize the pressure from the inlet into a rear chamber 34 between the back of the piston 27 and the end wall 32. The multiple small orifices 26 permit the refrigeration potential of the propane to be realized in lowering the air fuel mixture temperature substan- tially, hence increasing power and engine performance. For a fuller understanding of the present invention and its comparison with prior art. Table II details the comparison of gasoline, propane vapor and propane liquid as fuels and shows that the energy volume density for liquid propane is theoretically about 10 percent greater than for propane vapor. For equal thermal efficiencies the power output of a given engine would increase in the same proportion as the energy volumetric density increase. c-rπ ENERGY DENSITY COMPARISON-" Gasoline and Propane as Fuels In Internal Combustion Engines Parameter Shits Gasoline Propane Vapor Liquid Lower Heating Valve btu/lb. 18,900 19,800 19,800 Stoichicπ * etric Air/fuel ratio lb/lb 14.5 15.7 15.7 Stoiahicinetriσ Air/fuel mixture energy density btu/lb -air 1303 1261 1261 Ό / Heat of Vaporization btu/lb 150 o2 183 Air Specific heat (Cp) btu/lb °F 0.24 Air cooling effect frcm fuel vaporization op 43.1 0 48.6 Inlet air density- . lb/ft 3 .0816 .0749 .0825 Air/fuel mixture volumetric energy density -btu/ft 3 air 106.3 94.4 104.0 Normalised to Propane vapor 1.13 1.00 1.10 1/ At .standard pressure and temperature. 2/ Since fuel is alr^eady vaporized. FIGURE 5 illustrates a typical pressure- enthalpy diagram wherein enthalpy "h" is defined in terms of specific internal energy " ," pressure "p" and specific volume "v" as in "Thermofluid Mechanics" by Pefley and Murray, McGraw-Hill Book Co., 1966, p. 155. (h = u + pv) Prior practice to maintain a fluid in liquid phase has been to change its environment by raising pressure or extracting heat by external cooling. Referring to FIGURE 5, the starting point for a stored fuel is a mixture of saturated liquid (point 0) and SUBSTITUTE SHEET saturated vapor point 6. The fuel tank contains saturated liquid in the lower portion of the tank and saturated vapor in equilibrium at the same pressure and temperature in the upper portion. Note in FIGURE 5 that within the saturation region (mixture of liquid and vapor) isothermal and isobaric lines are parallel. Any liquid withdrawn from the tank leaves as saturated liquid (point 0). As it flows it can exper¬ ience heating or cooling and a loss of pressure due to fluid friction. Any transfer of heat into the fuel raises the enthalpy (h) and transforms part of the saturated liquid to saturated vapor (point 6). The flowing fuel moves into the saturation region. This means that vapor bubbles are forming- in the flowing line and the fuel is a mixture of liquid vapor, increasing in vapor and decreasing in liquid as it moves down the line. If the flow is adiabatic (no heat transfer) but drops to a lower pressure and the same velocity then the fluid moves from saturated liquid (point 0) into the saturation region at a constant enthalpy and lower pressure (point 1). Again the fuel is a mixture of liquid and vapor, and increasing in vapor. The present invention uses the refrigerating effect of the vaporizing fuel in pilot fuel flow to extract heat from the main flow and maintain it in the liquid phase by overcoming the effects of pressure drop and heat transfer described above. By throttling, (constant enthalpy expansion to a lower pressure from point 0 to point 1) a lower temperature is generated in the pilot flow. The pilot flow then draws heat from the main fuel flow, subcooling it from point 0 to point 4 in FIGURE 4, as the pilot flow continues to vaporize along the path from point 1 to point 2. For propane the enthalpy change from point 1 to point 2 is in the range of 100 btu/lb. The specific heat of liquid propane is approximately 0.6 btu/lb.°F. Hence, a very small vapor bleed flow will produce a significant reduction in liquid temperature of a larger main fuel flow, and thus assure that the main flow remains liquid up to the point of introduction to the engine. The theoretical end point of the heat exchange process occurs when both streams come to the same temperature (point 4 for the main flow and point 3 for the pilot flow) . In practice there will be some effect of external heat transfer from the ambient air into the main fuel stream and pressure drop in the main stream which will partially offset the effect of the cooling „ pilot flow. Design of the device, therefore, balances the magnitude of bleed flow, design of the delivery system and environmental conditions to achieve the most cost effective approach to liquid flow at the metering point. There is no danger of over cooling the main flow as solidification of the propane is not possible. An added benefit of this pilot flow sub- cooling is that the pilot flow may be used for idling fuel flow on the engine. Thus, at start-up and during all engine operation, the delivery system is being cooled by the vaporization of the pilot fuel. In this invention for a liquid fuel delivery system at a given ambient temperature, the pressure within the tank 11 remains constant, and as fuel flows out, more liquid vaporizes restoring the saturation pressure. As ambient temperature varies, the satura¬ tion pressure for LPG varies. Saturation pressure for propane, for example, varies according to the curve shown in FIGURE 6. The fuel delivery system described c:.:?ι here senses the engine fuel requirements and offers a varying impedence to flow at the fuel delivery point such that the fuel tank pressure will induce flow through the system equal to that required. In this design the dispersion and mixing of the fuel in air is accomplished in the same device as the impedence variation. These functions are performed by the incre¬ mental valve which consists of piston 27 within cylin- der 25 which has the longitudinal series of small orifices or ports 26. In its "off* position the piston 27 covers the orifices 26 and no fuel passes through the incremental valve. As the piston 27 is moved from its closed position, it uncovers progressively more orifices 26, thereby reducing the flow impedence and permits the flow rate of liquid fuel to increase in response to predetermined engine requirements. Fuel flowing through the holes uncovered by the piston is directed by the orientation of the holes which act as orifices and vaporizes at rates determined by fuel tank pressure, hole size and fuel properties. Very small (.0005 - .001 in.) holes offer excessive pressure drop. Large holes (larger than .006 in.) allow the fuel to pass in large droplets which do not vaporize readily enough. Orifices covering the range of .002 to about .006 in. are preferred. Since the piston will be moved in finite increments of distance, orifices 26 and spacing must be sized to provide a smooth variation of fuel flow rate, for all tank pressures. An alternative metering valve system and improvements is illustrated in FIGURES 7-9. As shown there the metering valve consists of a flat orifice plate 41 with side tab retaining arms 42 and upper c::π flanges 43 with the metering orifices 44 laser drilled through the plate 41. A slide metering tab 45 posi¬ tioned by an actuator rod 46 is utilized to cover and uncover a predetermined number of fuel metering orifices 44. The metering tab 45 is contained between the tab retaining arms 42 and the flanges 43 to pro¬ vide a mechanical alignment and preload sealing forces between the tab 45 and the plate 41. The underside of the orifice plate 41 has a milled out region 47 in the vicinity of the orifices 44 so that a wall thick¬ ness of about .010 inch exists through which the orifices 44 extend. This thin wall section has been found to produce reliable fuel flow for the very small orifice diameters used. As best illustrated in FIGURE 9 the orifices 44 have their axes in adjacent rows positioned non- parallel for impingement of the fuel streams therefrom to provide better fuel atomization in -a very short distance into the air stream for thorough mixing of fuel and air.

Claims: Claims 1. A liquid fuel system for an engine comprising: a fuel tank means for storing vapor fuel under pressure in liquid phase with liquid and vapor in equilibrium, a fuel delivery adapter means for securing in place along the inlet air stream of an engine, a fuel line means for carrying vapor fuel in liquid phase from the fuel tank means to said fuel delivery means for direct injection of vapor fuel in liquid phase into the inlet air stream of the engine, and means for vaporizing a small portion of vapor fuel to cool the vapor fuel in said fuel line and insuring direct injection of vapor fuel- in liquid phase. 2. The fuel system of claim 1 including: a pilot fuel line means for directing fuel from said fuel tank means or said fuel line means to said fuel adapter and positioned for heat exchange between vaporizing fuel in said pilot fuel line means and vapor fuel in liquid phase in said fuel line means, and throttling means for reducing the pressure on the fuel in said pilot fuel line means for allowing vaporization of fuel in said pilot fuel line means. f 3. The fuel system of claim 2 wherein said fuel line means and said pilot fuel line means include a pilot fuel line located within a main fuel line. 4. The liquid fuel system in accordance with claim 1 wherein said fuel delivery adapter means includes: a fuel delivery chamber in said adapter means, a series of liquid phase flow orifices connecting said delivery chamber to the inlet air stream of the engine, means slidable relative to said delivery chamber for progressively uncovering said series of orifices, and actuator means for moving said slidable means to cover or uncover said flow orifices for passage of fuel therethrough in response to engine fuel needs. 5. The liquid fuel system in accordance with claim 4 wherein said delivery chamber is a hollow cylinder and said slidable means is a piston slidable within said cylinder. 6. The liquid fuel system in accordance with claim 4 wherein said adapter means includes a flat plate in which said orifices are located and said slidable means comprises a slide metering tab slidable across said orifices in said plate. 7. The liquid fuel system in accordance with claim 4 wherein said orifices have a diameter in the range of .002 to .006 inch. 8. The liquid fuel system in accordance with claim 4 wherein at least certain of said orifices have axes which are non-parallel with the axes of other of said orifices for impingement of the fuel streams thereof. oι-:?ι 9. In a liquid fuel system for a engine for carrying liquid from a fuel tank to delivery into the inlet air stream of the engine, the improvement comprising: a fuel delivery adapter for securing in place along the inlet air stream of an engine and having a fuel delivery chamber and a series of liquid phase fuel orifices connecting said delivery chamber to the inlet air stream of the engine with the orifices having a diameter in the range of .002 to .006 inches, means slidable relative to said delivery chamber for progressively uncovering said series of orifices, and actuator means for moving said piston to cover or uncover said flow orifices for passage of fuel therethrough in response to engine fuel needs. 10. In a fuel system in accordance with claim 9 at least certain of said orifices having axes which are non-parallel with the axes of other of said orifices for impingement of fuel streams thereof. 11. A liquid fuel system for a spark igni¬ tion engine comprising: a fuel tank means for storing vapor fuel under pressure in liquid phase with liquid and vapor in equilibrium, a fuel delivery adapter means for securing in place along the inlet air stream of a conventional gasoline spark ignition engine, a fuel delivery chamber in said adapter means, said adapter means having a series of liquid phase flow orifices connecting said delivery chamber to the inlet air stream of the engine, means slidable relative to said delivery chamber for progressively uncovering said series of orifices, actuator means for moving said slidable means to cover or uncover said flow orifices for passage of fuel therethrough in response to engine fuel needs, a main fuel line means for carrying vapor fuel in liquid phase from the fuel tank means to said fuel delivery chamber, a pilot fuel line means within said main fuel line means for heat exchange between vaporiz¬ ing fuel in said pilot fuel line means and vapor fuel in liquid phase in said main fuel line means, a throttling orifice at the input end of said pilot fuel line means, a connecting line for carrying vapor fuel in liquid phase from either said fuel tank means or said main fuel line means to said throttling orifice, and OMFI the output end of said pilot fuel line means connected to said fuel adapter means for introducing throttled fuel in vapor phase to the inlet air stream of the engine in a quantity to maintain the engine idling. 12. In a liquid fuel system for a spark ignition engine for carrying vapor fuel under pressure in liquid phase from a fuel tank to delivery into the inlet air stream of the engine, the improvement comprising: a main fuel line means for carrying vapor fuel in liquid phase from the fuel tank means to the inlet air stream of the engine, a pilot fuel line means for carrying vapor fuel in vaporizing liquid phase to the inlet air stream of the engine and positioned for heat exchange between the vaporizing fuel in said pilot fuel line means and vapor fuel in liquid phase in said main fuel line means, and throttling means for reducing the pressure on the fuel in said pilot fuel line means for allowing vaporization of fuel in said pilot fuel line means. 13. A fuel system in accordance with claim 12 wherein said pilot fuel line means is located within said main fuel line means. 14. Method of delivering vapor fuel in liquid phase to the inlet air stream of a spark igni¬ tion engine comprising the steps of: storing vapor fuel under pressure in liquid phase with liquid and vapor in equilibrium, delivering vapor fuel under pressure in liquid phase from storage to the inlet air stream of a spark ignition engine, throttling a small amount of vapor fuel under pressure in liquid phase to a lower pressure for vaporization, and delivering the throttled fuel in heat exchange with the delivering fuel in liquid phase to cool the fuel in liquid phase as the throttled fuel vaporizes. 15. The method of claim 14 including delivering the throttled fuel in vapor phase to the inlet air stream of a spark ignition engine in a quantity to maintain the engine idling. 16. The method of claim 14 including throttling the vapor fuel in liquid phase into the inlet air stream through a series of progressively uncovered flow orifices. .'?ι

Inventors: PEFLEY R, PULLMAN J
Applicants: PEFLEY R, PRODATEK CORP, PULLMAN J
Application year: 1980
Main classification: F02B13
IPC codes: F02B29, F02B43, F02M13, F02M21