COMBUSTION CHAMBER OF A GAS TURBINE ENGINE WITH A FRONT DEVICE Russian patent published in 2023 - IPC F23R3/28 

FIELD: gas turbine engines.

SUBSTANCE: invention relates to gas turbine engines and can be used in the combustion chambers of aircraft gas turbine engines and ground installations. The combustion chamber of a gas turbine engine with a front device contains a flame tube, a front device made in the form of a hollow receiver, on the side surfaces of which there are wedge-shaped pylons, the main and additional fuel supply systems, each of which has the corresponding fuel supply lines, branch pipes and manifolds with spray holes. The hollow receiver is made in the form of two side walls connected on one side by a rounded wall, and on the other side by a flat wall. The cavity of the hollow receiver is divided into two parts, one of which is the manifold of the main fuel supply system, and the other is the manifold of the additional fuel supply system. The pylons are made in the form of two side walls connected by mating surfaces, a rounded surface and a rear flat end, the inner cavity of the pylon is in communication with the cavity of the hollow receiver. The cavity of each pylon and the cavity of the hollow receiver are equipped with deflectors with holes evenly distributed on them. The fuel supply lines of the main and additional fuel supply systems are located in front of the front device and are connected by branch pipes with a rounded wall of the hollow receiver, and the branch pipes of the main and additional fuel supply systems are connected to the corresponding manifolds. The spray holes of the main fuel supply system are located on the rear ends of the pylons, and the spray holes of the additional fuel supply system are located on the flat wall of the hollow receiver.

EFFECT: reducing nitrogen oxide (NO_x) emissions, as well as eliminating carbon monoxide (CO), unburned hydrocarbons (UHC) and sooting.

5 cl, 8 dwg