GAS TURBINE COMBUSTION CHAMBER Russian patent published in 2024 - IPC F23R3/28 F23R3/46 

FIELD: gas turbine engine building.

SUBSTANCE: invention relates to gas turbine engine building and to designs of combustion chambers of gas turbine engines. GTE combustion chamber comprises external housing (1), flame tube (2) and annular plate (3) with injector modules (4) installed on it and fuel manifold (5) connected to plate (3) and installed in front of plate (3), the cavity of which is connected on one side with fuel line (6), and on the other side with fuel channels (7) of injector modules (4), containing jet fuel sprayer (8) and air supply channels with swirling (9). At that, manifold (5) is made in the form of hollow ring with streamlined side wall (10) divided by horizontal partition (11) with bushing (12) in which tube (13) is installed. On outer wall of manifold there is fuel supply union (14) in flange of which rod (15) is installed, at that tube (13) passes coaxially to inner channel of rod (15). T-piece (16) with two unions (17) is installed to conical part of stock (15), each of which is connected by means of pipelines (6) to unions (18) of external double-cavity manifold (19) fixed to flange (20) of external housing at using brackets (21). External casing is turned with increased thickness, on which sleeve (23) is installed by means of bolted joint (22). In it there is a cylindrical part of rod (15) on which a sphere is placed between two hemispheres (25). Hemispheres (25) are pressed by a package of disk springs (26) by means of threaded bushing (27) installed in sleeve (23). Annular plate (3) with peripheral shields (28) provides arrangement of nozzle modules (4) in two rows in staggered order, includes three types of injector modules (4), casings (29) of flame tube (2) are turned, consisting of sections (30), each contains annular groove (31) with holes (32) for cooling. Diffuser (33) is made as detachable, fuel manifold (5) is arranged inside diffuser (33) in its centre.

EFFECT: combustion chamber of a gas turbine engine is proposed.

1 cl, 2 dwg