Abstract: A combustion structure for a turbine engine includes an annular combustion cavity into which flows a part of each of a plurality of radially outwardly flowing primary air jets to define a rotating toroid of primary combustion air. Plural annular louvers defined in the walls of the combustion cavity provide plural film-like wall cooling air flows moving in agreement with the rotating toroid of primary combustion air. An annular array of circumferentially spaced apart and disposed louvers in a radially outer wall of the combustor structure provide film-like air flows to energize the rotating toroid of combustion air to swirl about the combustion cavity.