Injector with injector elements in circumferential rows that alternate between counter-clockwise and clockwise swirl

A liquid rocket engine comprising:

• a combustion chamber;
• a nozzle attached with the combustion chamber;
• and
• an injector attached at an end of the combustion chamber, the injector having a circular configuration and including
• an array of injector elements, each injector element includes a central passage defining a central axis and a plurality of peripheral transverse passages, the central passages are configured to provide axial injection flow and the peripheral transverse passages are configured to provide swirl injection flow about the axial injection flow, wherein a portion of the injector elements are configured to provide the swirl injection flow in a clockwise direction and another portion of the injector elements are configured to provide the swirl injection flow in a counter-clockwise direction,
• the injector elements are arranged with a single, center injector element and a plurality of circumferential rows disposed around the single, center injector element, the injector elements of each one of the circumferential rows are either all of the clockwise direction or all of the counter-clockwise direction, and from the single, center injector element moving radially outwardly the circumferential rows alternate between the clockwise direction and the counter-clockwise direction, and
• the injector elements provided in 60° wedge repeat units that together form the circular configuration.