Kazan National Research Technical University named after A. N. Tupolev has received a patent for a new design of a fuel-air nozzle for gas turbine engines operating on gas. The developers changed the geometry of the mixing sleeve, atomizer, and the inlet section of the air duct, expecting to achieve more stable combustion and reduce the risk of overheating of combustion chamber parts.

The patent describes a system in which fuel is distributed through openings in the atomizer and nozzle body, and then mixed with air swirled by a bladed swirler. Additional openings in the mixing sleeve and transition cone ensure the exit of the mixture, and a separate axial opening of the atomizer supplies part of the gas directly to the central area.

One of the key design details is an expanding mixing sleeve with an annular wall, perforation, and a transition cone. According to the authors, such a geometry should help stabilize combustion and dissipate heat, preventing overheating of the sleeve.

Another change concerns the air inlet: the hollow crown nut received a spherical inlet, which smoothly transitions into a cone and a cylindrical channel. This solution is designed to reduce the risk of air flow separation before the bladed swirler.

The developers also expect to improve the mixing of gas with air and increase the completeness of fuel combustion. Nozzles of this type are intended, in particular, for combustion chambers of gas turbine units that drive gas pumping units and electric generators.