RING COMBUSTION CHAMBER OF GAS-TURBINE ENGINE AND ITS OPERATION METHOD Russian patent published in 2015 - IPC F23R3/46 F23R3/28 

FIELD: engines and pumps.

SUBSTANCE: ring combustion chamber of gas-turbine engine has nozzles group located in same plane on the face wall of the combustion chamber, by at least two coaxial rings. In each ring the same and even number of the low-emission burners is installed. The internal ring burners are displaced in the circumferential direction relatively to the burners of the external ring by half-step. All burners are made as two-channel. The internal channels of the burners are used to supply pilot fuel in them only, and the external channels of the burners are used to supply the compressed air in them from the compressor and the main fuel with creation of the lean air-fuel mixture. The external channel of each burner contains input guide vanes, their walls has holes for the fuel supply in the air cross-flow, the blade swirler installed at the channel output, and permeable element with set porosity, installed between the input guide vanes and blade swirler. The flow swirling direction in the burners using the blade swirlers alternates by the opposite direction upon transition from one burner to the another adjacent burner within the same ring. Besides, each burner contains a ring fuel receiver installed above the input guide vanes. The internal channels of the burners of the internal and external rings are combined respectively to the internal and external headers of the pilot fuel. The ring fuel receivers of the burners of the internal and external rings are combined respectively to the internal and external headers of the main fuel. At the inputs of the pilot and main fuel mains one fuel flow regulator is installed. Upstream the inputs of the internal headers of the pilot and main fuel in the supply fuel mains one valve in each is installed.

EFFECT: invention reduces full pressure losses, increases operation reliability of the ring combustion chamber, range of stable burning of the lean air-fuel mixture, and uniformity of the temperature fields in the radial and circumferential directions upon decreasing of emission of nitrogen oxides and carbon oxides.

7 cl, 5 dwg