The invention relates to marine fuel supply systems for fuel injected internal combustion engines, particularly where boating regulations prohibit fuel return from the engine to the remote fuel tank. In fuel injected engines it is important to accurately control the quantity of fuel delivered to the engine through the fuel injectors. Many systems have been designed to control the operation of a fuel injector to accurately meter the fuel to the engine. It is common to use a high pressure pump to supply fuel to the injectors, with a pressure regulator pro¬ viding an essentially constant fuel pressure at the injector. When the engine is located a significant distance from the fuel tank, it is common to provide a high capacity pump and recirculate excess fuel, i.e. the amount of fuel over and above that required by the engine, back to the fuel tank. In marine applica¬ tions, however, it is undesirable to provide an ex¬ tended fuel return line to the fuel tank, since fire or other hazards could arise.

Some prior systems have used recirculating type fuel injection pumps, with the excess fuel re¬ turning immediately to the inle tof the pump. In such systems, however, if the engine is operated at idle or low speeds for significant periods of time, the recirculating fuel accumulates heat from the pump and may vaporize. This typically would reduce the output of the pump to such a degree that adequate fuel pres¬ sure could no longer be maintained at the fuel injector.

The object of the present invention is to provide a fuel supply system which eliminates the fuel return line and eliminates recirculation through the fuel pump. The present invention provides a marine fuel system for an internal combustion engine with a remote fuel tank, comprising an induction system for supplying combustion air to said engine; fuel injection means for mixing fuel with said combutsion air; and fuel pump means connected to draw fuel from said re¬ mote fuel tank and supply fuel under pressure to said fuel injection means characterized by pressure sen¬ sor means connected to sense the fuel pressure at said fuel injection means and connected to turn off said fuel pump means when said fuel pressure at said fuel injection means is above a first value, and to turn on said fuel pump means when said fuel pressure at said fuel injection means is below a second value less than said first value; and a high pressure fuel line connected from said fuel pump means to said fuel injection means, said pressure sensor means comprising differential pressure transducer means connected between said high pressure fuel line and said in¬ duction system to sense differential pressure across said fuel injection means; said high pressure fuel line being connected to said fuel injection means without a return fuel line to said fuel pump means and without a return fuel line to said remote fuel tank. In the drawings: Figure 1 illustrates a marine fuel system in accordance with the invention.

Figure 1 shows one cylinder of a two cycle, crankcase compression, internal combustion engine 10. The engine includes a cylinder block 11 having a cy- linder bore 12 in which a piston 13 is supported for reciprocation. The piston 13 is connected by means of

a connecting rod 14 to a crankshaft 15 that is jour- nalled for rotation in the crankcase 16 of the engine

10.

The engine 10 includes an induction system including an intake manifold 17 connected to supply combustion air to crankcase 16 of engine 10. A reed type check valve 18 is provided in the passage to minimize blow back flow out of crankcase 16 into induction manifold 17. A transfer passage 19 extends from crankcase 16 through cylinder block 11 and ter¬ minates at an inlet port 20 in the cylinder wall at a point above the bottom dead center position of piston 13. A sprak plug 21 is provided in the cylinder head 22 for firing the charge, and an exhaust port 23 is formed in the cylindr bore 12 to discharge exhaust gases to the atmosphere.

Engine 10 is provided with a fuel injection system that includes an electromagnetically controlled injector nozzle 24 that discharges into the induction system, either into crankcase 16, or into induction manifold 17 as shown. Fuel, typically gasoline, is supplied to injector 24 vy a high pressure fuel pump 25 through high pressure fuel line 27. An electronic controller 28 controls the operation of injector 24 in known manner to deliver the desired amount of fuel to induction manifold 17 at the desired times.

During running of the engine, air is deliv¬ ered to induction manifold 17 and fuel is injected by injector 24 to provide a fuel air mixture which is admitted to crankcase 16 through reed valve 18 while piston 13 is moving upwardly toward spark plug 21. Reed valve 18 opens during these conditions as long as the pressure in crankcase 16 is lower than that in induction manifold 17. As piston 13 moves downward toward crankcase 16, exhaust port 23 opens to discharge spent combustion products, and intake port 20 opens to

allow transfer of air fuel mixture from crankcase 16 to cylinder 12. On the up stroke of piston 13, spark plug 21 is fied to ignite the mixture and the cycle continues in conventional manner. Fuel is drawn from a remote fuel tank 29 to the inlet 30 of high pressure fuel pump 25. In preferred form, a low pressure pump 31 such as a diaphragm pump operated by the pulsating pressure in the engine's crankcase 16 is used to draw fuel from the remote fuel tank 29 and supply the fuel at low pressure through low pressure fuel line 32. Such diaphragm pumps are commonly used on outboard motors and produce a fuel output closely matched to engine requirements. A reservoir 34 is preferably provided in low pressure fuel line 32 from which fuel is drawn by high pressure pump 25 and which may alos provide vapor separation. In an alternative embodiment, reservoir 34 is eliminated. In a further alternative embodiment, low pressure pump 31-is eliminated, and high, pressure pump 25 draws fuel directly from tank 29 through fuel line 32.

High pressure fuel pump 25 is controlled by pump control 33 including a pressure sensor connected to sense the fuel pressure at the fuel injector and turn off pump 25 when the fuel pressure at thein- jector is above a first value and turn on the fuel pump when the fuel pressure at the injector is below a second value less than the first value. The pre¬ ferred embodiment uses a Microswitch Control Corp P/N 142PC60A differntial presure transducer having a hgih pressure input connected to the high pressure fuel line 27 and a low pressure input connected to induction manifold 17 which varies in pressure from atmospheric to below atmospheric. The.fuel flow rate through the orifice of the injector nozzle is deter¬ mined by differential pressure across the orifice.

By sensing the actual differential pressure across the injector, rather than comparison with atmospheric, there is enabled a more accurate control of the quan¬ tity of fuel delivered to the engine through the fuel injectors. A small range of pressure across the in¬ jector is preferred, such as 35.5 to 36.5 psi, with the fuel pump being turned off when the pressure in high pressure line 27 relative to induction manifold 17. is higher than such range, and with the fuel pump being turned back on when the relative dif¬ ferential pressure is below such range. High pres¬ sure fuel line 27 is thus deadheaded and dead-end connected to fuel injector 24 without a return fuel line to the fuel pump and without a return fuel line to remote fuel tank 29.

It is recognized that various equivalents, alternatives and modifications are possible.