Hybrid internal combustion reciprocating engine
This patent describes a hybrid type reciprocating internal combustion turbine fuel engine with combined spark ignition, torch-assisted to compression ignition modes comprising: a cylinder; a cylinder head mounted on the cylinder having a substantially planar inner surface; exhaust and inlet valves positioned in the head connected to corresponding exhaust and unthrottled inlet passages; a piston reciprocally mounted within the cylinder having a top surface thereon which surface in the top dead center position of the piston is in close proximity with the inner surface of the cylinder head; a substantially spherical precombustion chamber located in the head; a lineal passage tangentially joining the precombustion chamber with the inner surface of the cylinder head; a pilot fuel injector means and an igniter means both located in the precombustion chamber which inject and ignite a precharge; a main fuel injector means in the cylinder head; a bowl-shaped recess comprising the main combustion chamber located in the top surface of the piston in close proximity with the main injector means in the top dead center position with the lineal passage tangentially aligned with the main combustion chamber, whereby the burning gases exiting the precombustion chamber are directed into the main combustion chamber causing ignition therein.
- Assignee:
- Cessna Aircraft Co., Wichita, KS
- Patent Number(s):
- US 4765293
- OSTI ID:
- 6620252
- Resource Relation:
- Patent File Date: Filed date 7 May 1986
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
SPARK IGNITION ENGINES
IGNITION SYSTEMS
COMBUSTION CHAMBERS
COMPRESSION
DESIGN
FUEL INJECTION SYSTEMS
HYBRID SYSTEMS
PISTONS
TURBINES
VALVES
CONTROL EQUIPMENT
ENGINES
EQUIPMENT
FLOW REGULATORS
FUEL SYSTEMS
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINERY
TURBOMACHINERY
330101* - Internal Combustion Engines- Spark-Ignition