Patent ID: 9476346
Filing Date: 2016-10-25
CPC Classification: F02B,Y02T

Claim Text:
1. A combustion method having auto-ignition for direct-injection internal combustion engines, comprising: the internal combustion engine having at least one cylinder with a combustion chamber laterally delimited by a cylinder wall, and is delimited axially on one side by a cylinder head, and is delimited axially on a second side by an adjustable-stroke piston in the cylinder, the piston having an annular circumferential piston step axially recessed in the piston relative to an annular circumferential piston crown, and which via an annular circumferential jet divider contour merges into a piston cavity axially recessed in the piston relative to the piston step, an injection nozzle situated in the cylinder head being associated with the particular cylinder, wherein for a combustion operation in auto-ignition mode the injection nozzle simultaneously injects multiple injection jets into the combustion chamber in a star-shaped pattern, wherein the injection jets are each divided at the jet divider contour into a first partial quantity, a second partial quantity, and third partial quantities, the first partial quantity entering into the piston cavity, the second partial quantity entering via the piston step into a region between the piston crown and the cylinder head, and the third partial quantities, starting from the respective injection jet, spreading out on both sides in the peripheral direction in opposite directions along the piston step, and the respective third partial quantities colliding with one another between two adjacent injection jets within the piston step and being deflected radially inwardly, the first partial quantity and the second partial quantity forming a first combustion front and a second combustion front, and the partial quantities which in each case are jointly deflected inwardly forming a third combustion front radially inwardly into a gap between the injection jets, and wherein the injection jets are deflected above the piston cavity upstream from the jet divider contour in a direction of the piston by a resulting flow formed essentially from a swirl flow, a squish gap flow, and a jet flow, wherein a flow vector of the resulting flow includes a portion that forms above the piston cavity and coaxially with respect to a longitudinal center axis of the cylinder in a direction of the piston cavity.