Air-compressing, direct-injection internal combustion engine

Claim 1

An internal combustion engine, each piston of which has a crown and a combustion chamber including a longitudinal axis as well as a wall in a circumferential direction along with a lower quarter of the combustion chamber and being in the shape of a solid of revolution and having a constricted throat opening of oval cross section with a major diameter as well as a minor diameter and a varying wall height in the circumferential direction, said throat opening including an edge and being located in the crown of said piston and opening in the direction toward an associated cylinder head; means are provided for imparting a rotary motion, about the longitudinal axis of said combustion chamber, to in-flowing air for combustion; an injection nozzle is arranged off-center in said cylinder head in the vicinity of the edge of said throat opening and has a fuel jet discharge point communicating with said combustion chamber for injecting fuel therein, said fuel being injected into said combustion chamber in the form of a single jet, in the direction of rotating air for combustion, in such a way as to permit formation of a fuel film on the wall of said combustion chamber, with the point of impingement of said fuel jet on the wall of said combustion chamber being located in the lower quarter of said combustion chamber by appropriate selection of the nozzle angle and nozzle position; viewing said combustion chamber in a top view thereof, the major diameter of said throat opening, across the center of said combustion chamber, extends in the direction toward said fuel jet discharge point of said injection nozzle, with the distance of said fuel jet discharge point from the center of said combustion chamber being 0.35 to 0.70 times the diameter of said combustion chamber, and with the direction of a fuel jet, on the one hand being geometrically projected in a plane intersecting at a right angle to the longitudinal axis of said combustion chamber, forming an angle of 10° to 50° with a straight line extending from said fuel jet discharge point through the longitudinal axis of said combustion chamber (center of said combustion chamber), and on the other hand forming an angle of 20° to 60° with a plane intersecting at a right angle to the longitudinal axis of said combustion chamber; said combustion chamber being spherical; the distance of said fuel jet discharge point from the center of said combustion chamber being 0.50 to 0.55 times the diameter of said combustion chamber; said angle of said direction of a fuel jet with said straight line from said fuel jet discharge point being between 15° and 40°; said angle of said direction of a fuel jet with a plane at a right angle to the longitudinal axis of said combustion chamber being between 40° and 50°; and the ratio of the major diameter of said oval throat opening to the minor diameter thereof being in a range from 1.10 to 1.15.