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The thrust chamber's injector.

Sutton's History of Liquid Propellant Rocket Engines describes the combustion chamber's bipropellant injector elements:

Spiral inserts into the center tube and tangentially drilled holes allow for tangential rows of the oxygen and the fuel inside each injection element. The propellants then flow in spirals and are "whirled." At the exit of each injection element the propellant flows form two conical propellant sprays. There are 337 such tubes or injection spray points, arranged in 10 rings. The outer rings spray only fuel on the inner chamber wall (film cooling) and keep the wall temperature below 380° C or 716° F.

I've made a page regarding the RD-107 injector.