Abstract: Provided are gas turbine engines 10, combustion chambers 46 and methods of operation for reducing NOx and CO emissions in aerospace and industrial applications. An upstream compressor 18 provides pressurized air 32 to a combustion chamber having an inner liner 58 and an outer shroud 62 circumscribing a portion of the inner liner 58. The inner liner 58 having a wall 74 with an inwardly facing hot side 76 and an outwardly facing cold side 78. The shroud 62 is spaced from the inner liner 58, forming an annulus 100 for accepting a pressurized air stream 32B therein. Heat transfer features 82, disposed on the cold side 78, exchange heat from the liner wall 74 to the air stream 32B. Methods of operation include introducing fuel and air inside a liner wall 74 without premixing, and producing combustion products without introducing any additional pressurized air adjacent the hot side 76.

Abstract: A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing radial and axial support to the ceramic component. The at least one metal support component includes a structure, such as axial slots or radial slots, for minimizing stress and for increasing compliance of the metal support component with respect to the ceramic component.