BURNER FOR COMBUSTION CHAMBER OF GAS TURBINE (VERSIONS) Russian patent published in 2010 - IPC F23R3/34 

FIELD: engines and pumps.

SUBSTANCE: burner for combustion chamber of gas turbine is equipped with burner body having on its opposite ends along the axis the above located and below located extreme parts in the direction of the main flow, inner chamber, at least one main fuel inlet channel and at least one main air inlet channel, which are located so that they can supply fuel and air respectively to inner chamber. Burner also includes start-up combustion chamber and extinguisher. Start-up combustion chamber is located along the burner body axis and has the inlet of rich air-and-fuel mixture, combustion chamber of rich air-and-fuel mixture so that combustion products are obtained, and outlet of combustion products from the above combustion chamber of rich air-and-fuel mixture. Extinguisher is located in inner chamber of burner body along the central axis in the outlet zone of start-up combustion chamber and has the air inlet and group of outlets oriented in radial direction with possibility of supplying the cooling air to the outlet of start-up combustion chamber and extinguishing of the combustion products leaving it. According to the second version, flame stabiliser is located in inner chamber of the burner body and includes the main part adjacent to the burner body, and cylindrical body of bluff shape and elongated along the axis downwards in the direction of the main flow from the main part to inner chamber.

EFFECT: flame stabilisation.

10 cl, 3 dwg