LOW-EMISSION COMBUSTION CHAMBER OF JET TURBINE ENGINE ON HYDROGEN FUEL Russian patent published in 2025 - IPC F02C3/14 

FIELD: engines.

SUBSTANCE: invention relates to propulsion engineering, specifically to low-emission combustion chambers of hydrogen-fuel turbojet engines, and can be used in advanced high-parameter jet turbine engines on hydrogen fuel. Low-emission combustion chamber of a hydrogen-fuelled turbojet engine includes a housing, a combustion chamber installed therein, comprising a front device and an annular flame tube formed by outer and inner walls, wherein the latter are double, a device for inlet and outlet of hydrogen fuel, a heat exchanger formed by double walls of the flame tube, and a turbine nozzle block. Hydrogen fuel inlet device is made in the form of an inlet toroidal collector located at the flame tube outlet and enveloping the turbine nozzle block on the outer wall side. Hydrogen fuel outlet device is made in the form of outlet toroidal headers located at the flame tube inlet concentrically relative to the combustion chamber axis, one of which encloses the outer wall of the flame tube, and the second one encloses the inner wall of the flame tube. Combustion chamber is equipped with additional toroidal headers located at the flame tube outlet; at that, one of the additional toroidal headers covers the outer wall of the flame tube, and the second one covers the inner wall of the flame tube. Heat exchanger is made in the form of multi-thread spiral channels; at that, nozzle block blades include loop and semi-loop channels separated with the appropriate partitions, and are arranged radially and alternately. Inlets of loop and semi-loop channels of nozzle block blades are interconnected with inlet toroidal collector. Outlets of loop channels are interconnected with inlet of additional toroidal header enveloping external wall of flame tube; outlets of semi-loop channels are interconnected with inlet of additional toroidal collector enveloping inner wall of flame tube. Outlet of the additional toroidal collector covering the outer wall of the flame tube is connected to the inputs of helical channels located in the outer wall of the flame tube, outlet of additional toroidal collector enveloping inner wall of flame tube is interconnected with inlets of spiral channels located in inner wall of flame tube. Outlets of spiral channels enveloping external and internal walls of flame tube are interconnected with the appropriate inlets of outlet toroidal collectors, and outlets of the latter are interconnected with front device.

EFFECT: cooling of turbine nozzle unit blades, external and internal walls of annular flame tube by gaseous hydrogen without using air in cooling systems and combustion of depleted and homogenised fuel-air mixture at reduction of combustion products temperature.

1 cl, 5 dwg