Dual-fuel constructions for opposed-piston engines with shaped combustion chambers

Patent metadata

Field	Value
Publication number	US-10465616-B2
Application number	US-201414910174-A
Country	US
Kind code	B2
Filing date	Jul 31, 2014
Priority date	Aug 5, 2013
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A compression-ignited, opposed-piston engine equipped for multi-fuel operation includes at least one cylinder, a pair of pistons slidably disposed in the cylinder for opposing movement between respective bottom and fop center locations, and spaced-apart intake and exhaust ports near respective ends of the cylinder. The pistons include end surfaces constructed to form a shaped combustion chamber when the pistons are near top center locations during a compression stroke of the engine. At least one gaseous fuel injector communicates with the bore of the cylinder through an injector site in the cylinder between the intake port and the exhaust port. At least one liquid fuel injector communicates with the bore through an injector site in the cylinder. A fuel injection system coupled to the at least one gaseous fuel injector and to the at least one liquid fuel injector is operable to cause the at least one gaseous fuel injector to inject a main charge of gaseous fuel when the pistons are between the bottom and top center locations and to cause the at least one liquid fuel injector to inject a pilot charge of liquid fuel.

First claim

The invention claimed is:

1. A multi-fuel opposed-piston engine, comprising:
a cylinder with a bore, an intake port, and an exhaust port, the intake port and the exhaust port being spaced apart and located at respective ends of the cylinder;
a pair of pistons slidably disposed within the cylinder for opposing movement between respective bottom center and top center locations;
each piston of the pair of pistons having an opposing end surface constructed to form a combustion chamber, the combustion chamber formed by the opposing end surfaces having a generally ellipsoidal shape for promoting turbulent bulk air motion when the pair of pistons are near the top center locations during a compression stroke of the engine, each opposing end surface having diametrically opposed notches formed in a periphery of the opposing end surface so as to define a line of symmetry of the combustion chamber;
a pair of gaseous fuel injectors communicating with the bore of the cylinder through first injection ports at first diametrically opposed injector sites within the cylinder and between the pair of pistons, wherein the pair of gaseous fuel injectors are positioned to inject gaseous fuel in opposing radial directions of the bore of the cylinder transverse to the line of symmetry;
a pair of liquid fuel injectors communicating with the bore of the cylinder through second injection ports at second diametrically opposed injector sites within the cylinder and between the pair of pistons, wherein the pair of liquid fuel injectors are positioned to inject liquid fuel in opposing radial directions of the bore of the cylinder aligned with the line of symmetry; and
a fuel injection system operatively connected to an engine control unit, the fuel injection system comprising:
a gaseous fuel system coupled to the pair of gaseous fuel injectors and operable to cause the pair of gaseous fuel injectors to inject a main charge of gaseous fuel during a first crank angle window of the compression stroke so as to create a mixture of the main charge of gaseous fuel and charge air, the injection of the main charge of gaseous fuel taking place after both the intake port and the exhaust port have been closed by the pair of pistons as the pair of pistons transition from the bottom center locations toward the top center locations, and
a liquid fuel system coupled to the pair of liquid fuel injectors and operable to cause the pair of liquid fuel injectors to inject a pilot charge of liquid fuel during a second crank angle window of the compression stroke so as to facilitate an ignition of the mixture of the main charge of gaseous fuel and charge air, the injection of the pilot charge of liquid fuel taking place as the pair of pistons pass through the top center locations.

2. A method of operating the multi-fuel opposed-piston engine of claim 1 , the method comprising:
introducing charge air through the intake port and into the cylinder between the pair of pistons;
moving the pair of pistons toward each other during a compression stroke of the engine;
injecting a main charge of gaseous fuel into the cylinder between the pair of pistons, wherein the main charge of gaseous fuel is injected in opposing radial directions of the bore of the cylinder transverse to the line of symmetry of the combustion chamber through the first injection ports at first diametrically opposed injector sites within the cylinder during a first crank angle window of the compression stroke so as to create a mixture of the main charge of gaseous fuel and charge air as the pair of pistons transition from respective bottom center locations toward respective top center locations;
compressing the mixture of the main charge of gaseous fuel and charge air in response to the movement of the pair of pistons toward each other during the compression stroke;
forming a generally ellipsoidal-shaped combustion chamber constructed from the opposing end surfaces of each piston to contain the compressed mixture of the main charge of gaseous fuel and charge air as the pair of pistons approach the top center locations; and
injecting a pilot charge of liquid fuel into the cylinder between the pair of pistons, wherein the pilot charge of liquid fuel is injected in opposing radial directions of the bore of the cylinder aligned with the line of symmetry of the combustion chamber through the second injection ports at second diametrically opposed injector sites within the cylinder during a second crank angle window of the compression stroke so as to facilitate an ignition of the compressed mixture of the main charge of gaseous fuel and charge air as the pair of pistons pass through the top center locations.

3. The method of claim 2 , wherein the combustion chamber formed has an elongated semi-ellipsoidal shape having an axis that is collinear to the line of symmetry of the combustion chamber.

4. The method of claim 2 , wherein injecting the main charge of gaseous fuel during the first crank angle window of the compression stroke takes place after both the intake port and the exhaust port have been closed by the pair of pistons as the pair of pistons transition from the bottom center locations toward the top center locations.

5. The method of claim 4 , wherein injecting the pilot charge of liquid fuel during the second crank angle window of the compression stroke takes place at a crankshaft angle that precedes a minimum combustion chamber volume.

6. The method of claim 2 , wherein injecting the main charge of gaseous fuel during the first crank angle window of the compression stroke begins after both the intake port and the exhaust port have been closed by the pair of pistons as the pair of pistons transition from the bottom center locations toward the top center locations, and ends at a crankshaft angle that precedes a minimum combustion chamber volume.

7. The method of claim 6 , wherein injecting the pilot charge of liquid fuel during the second crank angle window of the compression stroke takes place at a crankshaft angle that precedes a minimum combustion chamber volume.

8. The method of claim 2 , wherein injecting the pilot charge of liquid fuel during the second crank angle window of the compression stroke takes place at a crankshaft angle that precedes a minimum combustion chamber volume.

Assignees

• Achates Power Inc

Inventors

• Redon Fabien G
• Regner Gerhard
• Venugopal Rishikesh

Classifications

• F02D41/3047

  said means being a secondary injection of fuel · CPC title

• F02D19/0647

  the gaseous fuel being liquefied petroleum gas [LPG], liquefied natural gas [LNG], compressed natural gas [CNG] or dimethyl ether [DME] · CPC title

• F02B75/28

  Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders (arranged oppositely relative to main shaft F02B75/24) · CPC title

• F02B23/0675

  the combustion space being substantially spherical, hemispherical, ellipsoid or parabolic · CPC title

• F02B23/0663

  having multiple injectors per combustion chamber · CPC title