Aircraft engine with opposed piston engine

An aircraft engine comprising:

• a hollow driveshaft having a first driveshaft end and a second driveshaft end and disposed along a driveshaft axis;
• a spool coaxial with the driveshaft and extending along the driveshaft axis from a first spool end to a second spool end and passing through the driveshaft;
• a first cam mounted on the driveshaft, the first cam having a circumferential shoulder of a first cam diameter and a first curvilinear shape with a first frequency;
• a second cam mounted on the spool and spaced apart from the first cam, the second cam having a circumferential shoulder of a second curvilinear shape which second curvilinear shape has a second frequency;
• a first combustion cylinder defined along a center cylinder axis, the combustion cylinder having a first end and a second end with an intake port formed in the cylinder between the first and second ends and an exhaust port formed in the cylinder between the intake port and the second end, the center cylinder axis being parallel with but spaced apart from the driveshaft axis, wherein a combustion chamber is defined within the cylinder between the two cylinder ends;
• a first piston assembly disposed in the first cylinder end of the first combustion cylinder and an opposing second piston assembly disposed in the second cylinder end of the first combustion cylinder, the first piston assembly engaging the curvilinear shaped shoulder of the first cam and the second piston assembly engaging the curvilinear shaped shoulder of the second cam, each piston assembly movable within the combustion cylinder;
• at least one fuel injector disposed within the combustion cylinder and in communication with said combustion chamber;
• and
• a turbine coaxially mounted on one of the driveshaft or the spool.

An aircraft engine comprising:

• a hollow driveshaft having a first driveshaft end and a second driveshaft end and disposed along a driveshaft axis;
• a spool coaxial with the driveshaft and extending along the driveshaft axis from a first spool end to a second spool end and passing through the driveshaft;
• a first cam mounted on the driveshaft, the first cam having a circumferential shoulder of a first cam diameter and a first curvilinear shape with a first frequency;
• a second cam mounted on the driveshaft and spaced apart from the first cam, the second cam having a circumferential shoulder of a second curvilinear shape which second curvilinear shape has a second frequency;
• a first combustion cylinder defined along a center cylinder axis, the combustion cylinder having a first end and a second end with an intake port formed in the cylinder between the first and second ends and an exhaust port formed in the cylinder between the intake port and the second end, the center cylinder axis being parallel with but spaced apart from the driveshaft axis, wherein a combustion chamber is defined within the cylinder between the two cylinder ends;
• a first piston assembly disposed in the first cylinder end of the first combustion cylinder and an opposing second piston assembly disposed in the second cylinder end of the first combustion cylinder, the first piston assembly engaging the curvilinear shaped shoulder of the first cam and the second piston assembly engaging the curvilinear shaped shoulder of the second cam, each piston assembly movable within the combustion cylinder;
• at least one fuel injector disposed within the combustion cylinder and in communication with said combustion chamber;
• a compressor turbine mounted on the driveshaft adjacent the first driveshaft end;
• a drive turbine mounted on the spool adjacent the second spool end;
• and
• a rotating component coaxially mounted on the spool.

An aircraft engine comprising:

• a driveshaft having a first driveshaft end and a second driveshaft end and disposed along a driveshaft axis;
• a first cam mounted on the driveshaft, the first cam having a circumferential shoulder of a first cam diameter and a first curvilinear shape with a first frequency;
• a second cam mounted on the driveshaft and spaced apart from the first cam, the second cam having a circumferential shoulder of a second curvilinear shape which second curvilinear shape has a second frequency;
• a first combustion cylinder defined along a center cylinder axis, the combustion cylinder having a first end and a second end with an intake port formed in the cylinder between the first and second ends and an exhaust port formed in the cylinder between the intake port and the second end, the center cylinder axis being parallel with but spaced apart from the driveshaft axis, wherein a combustion chamber is defined within the cylinder between the two cylinder ends;
• a first piston assembly disposed in the first cylinder end of the first combustion cylinder and an opposing second piston assembly disposed in the second cylinder end of the first combustion cylinder, the first piston assembly engaging the curvilinear shaped shoulder of the first cam and the second piston assembly engaging the curvilinear shaped shoulder of the second cam, each piston assembly movable within the combustion cylinder;
• at least one fuel injector disposed within the combustion cylinder and in communication with said combustion chamber;
• a compressor turbine mounted on the driveshaft between the first cam and the first driveshaft end;
• and a rotating component mounted on driveshaft adjacent the first driveshaft end;
• wherein the rotating component is selected from the group consisting of a propeller, a fan, a turbine and a gear.