FRONT DEVICE OF THE COMBUSTION CHAMBER OF A GAS TURBINE ENGINE Russian patent published in 2023 - IPC F23R3/18 

FIELD: gas turbine engines.

SUBSTANCE: invention relates to ground-based gas turbine engines and can be used for combustion of pre-mixed gaseous air-fuel mixtures in combustion chambers of gas turbine engines and gas turbine plants. The front device of the combustion chamber of a gas turbine engine contains a burner module with a longitudinal axis coaxial with the axis of the flame tube, a mixing channel of the burner module, fuel supply channels with fuel outlets, a flame stabilizer with petals is located at the outlet of the mixing channel, the petals are equally spaced around the circumference of the flame stabilizer and are each fixed by one side of the triangle on the outer surface of the flame stabilizer, and the ends of the side faces of the petals are placed radially in the plane of the end face of the flame stabilizer. The blades of the stabilizer are U-shaped; additionally, at the inlet to the flow part of the mixing channel, a radial-axial swirler with blades is made, inside which there are fuel supply channels with fuel supply outlets through which fuel is supplied to the mixing channel, while the angle of inclination α between the plane the symmetry of the blades of the radial-axial swirler and the corresponding radial plane passing through the axis of symmetry of the front device and the axis of the cylindrical section of the fuel supply channel to the fuel supply outlets is from 0° to 30°, the number of fuel outlets in the blades of the radial-axial swirler is in the range from 4 to 8, and the diameter ∅ of the fuel supply outlets is in the size range from 0.6 to 1.8 mm, the length L of the mixing channel is 3-7 of the height H of the mixing channel, the ratio of the radius of the inner wall of the mixing channel to the radius of its outer wall R1/R2 is within 0.4…0.65, angle β between the axis of the burner module and the line formed by the intersection of the plane passing through the central point of the upper part of the U-shaped petal equidistant from the side faces of the petal, and the plane passing through the axis of the burner module and perpendicular to the radial line passing through the central point of the upper part of the U-shaped petal is from 0° to 30°.

EFFECT: achieving a wide range of stable and pulsationless low-emission combustion in the combustion chamber in a wide range of engine operating modes and ambient temperature.

1 cl, 4 dwg