US 12,006,826 B2
Aircraft engine with opposed piston engine
Carlos Marcelo Todeschini Hilgert, Bento Goncalves (BR); and Gustavo Ludwig Schneider, Rio de Janeiro (BR)
Assigned to HTS LLC, Houston, TX (US)
Appl. No. 17/766,142
Filed by HTS LLC, Houston, TX (US)
PCT Filed Sep. 3, 2020, PCT No. PCT/US2020/049143
§ 371(c)(1), (2) Date Apr. 1, 2022,
PCT Pub. No. WO2021/046180, PCT Pub. Date Mar. 11, 2021.
Claims priority of provisional application 62/895,435, filed on Sep. 3, 2019.
Prior Publication US 2022/0389818 A1, Dec. 8, 2022
Int. Cl. F01B 3/00 (2006.01); B64D 27/02 (2006.01); B64D 27/04 (2006.01); B64D 27/16 (2006.01)
CPC F01B 3/0005 (2013.01) [B64D 27/04 (2013.01); B64D 27/16 (2013.01); F01B 3/0026 (2013.01); B64D 27/026 (2024.01)] 24 Claims
OG exemplary drawing
 
1. 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 disposed along a driveshaft axis 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 turbine coaxially mounted on one of the driveshaft or the spool, wherein the turbine is a high-pressure compressor turbine mounted on the driveshaft adjacent the first driveshaft end; and
a drive turbine disposed along a driveshaft axis and a low-pressure compressor turbine mounted on spool adjacent the high-pressure compressor turbine.