COMBUSTION CHAMBER OF GAS TURBINE ENGINE Russian patent published in 2024 - IPC F23R3/46 F23R3/60 

FIELD: gas turbine engine construction.

SUBSTANCE: invention relates to the designs of combustion chambers of gas turbine engines used to drive an electric generator or a supercharger of a gas pumping unit. The combustion chamber of a gas turbine engine contains a housing on the bosses of which fuel injectors are secured with flanges, the ends of the injectors are installed in the opening of the swirler housings included in the burners, fixed in the annular head of the flame tube using threaded nuts, a sealing unit is installed between the ends of each injector and the swirler body, fixed in the hole of the swirler housing. It differs in that the swirler consists of a cone-shaped gas distributor, hollow blades with three holes in height, the diameters of which increase from the base to the periphery, the swirler housing has a tapering shape with a smooth transition to the diffuser, the ends of the nozzles have a hole with a chamfer and are installed in a sealing unit located in gas distributor. The flame tube consists of sections, each section has a profile with a bend in which there are holes for supplying cooling air, the sections are connected to each other by spot electric welding, form the outer and inner casings of the flame tube. The annular head of the flame tube is made of sheet material and represents two connected half-plates with holes for installing swirler housings. Perforations are made in the half-plates around each swirler housing, to ensure structural rigidity. A sheet ring with holes for placing swirler housings is installed on the half-plates, the swirlers installed in the half-plate and the sheet ring are pressed with a threaded nut having grooves between the half-plate and the swirler housing forms a channel, a spherical flame tube profile in the combustion zone. In a cylindrical mixing zone, the combustion and mixing zone is divided by air supply bushings installed in the sections of the outer and inner casings, and the nozzle body is drop-shaped.

EFFECT: technical solution is provided by making design changes to the design of the swirler, annular head, flame tube and nozzle, their more efficient use in the combustion chambers of gas turbine engines operating primarily on gaseous fuel, namely: preliminary mixing of fuel with air is ensured before supply to the zone, continuous flow at the entrance to the swirler is ensured, flame stabilization is ensured in the fixed area of the flame tube when operating conditions of the combustion chamber change, fuel combustion is ensured at an excess air mixture ratio of 1.6-1.8, uniform mixing of fuel with air is ensured, low concentration of nitrogen oxides and carbon oxides is ensured, the low temperature of the annular head around is ensured, the manufacturability of the design of the annular head and the flame tube is ensured.

1 cl, 1 dwg