ANNULAR COMBUSTION CHAMBER OF A GAS TURBINE ENGINE Russian patent published in 2022 - IPC F23R3/50 

FIELD: gas turbine engines.

SUBSTANCE: invention relates to gas turbine engines (GTE) and can be used in the combustion chambers of aircraft gas turbine engines and ground-based gas turbine units (GTU). The task of reducing the length and weight of a gas turbine engine while ensuring the reliability of its operation is solved by an annular combustion chamber of a gas turbine engine, containing coaxially located outer 1 and inner 2 housings with an annular diffuser 3 formed by their walls at the entrance to the chamber; placed in the annular cavity between the housings of the flame tube 4, made of outer 5 and inner 6 shells with air supply holes; located at the entrance to the flame tube front device in the form of an annular flame stabilizer Δ-shaped section 8 with fuel injectors 11 and radial stabilizers 9 evenly placed on the outer and inner shells of the flame tube, made in cross-section in the form of wedge-shaped profiles facing the diffuser with blunted leading edges 10; nozzle blade profiles 15 are placed in the outlet part of the flame tube, the leading edges of which are hollow and have grooves 18 in the walls for communicating the annular cavity of the combustion chamber with the cavity of the flame tube; wherein the input edges of the blade profiles 16 and the radial stabilizers 9 are installed relative to the longitudinal axis of the flame tube at an angle corresponding to the angle of the air flow entry into its front device.

EFFECT: gas turbine engines improvement.

1 cl, 4 dwg