Injector device for an engine device, engine device, and air- and/or spacecraft

An engine device for at least one of an aircraft and a spacecraft, which engine device comprises a combustion chamber with a nozzle and comprises an injector device arranged opposite the nozzle, wherein the injector device is configured for introducing a fluidic fuel and a fluidic oxidizing agent into the combustion chamber, which injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber,

• wherein at least one of at least one first resonator element is associated with the at least one first injection element and wherein at least one second resonator element is associated with the at least one second injection element, and
• wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
• wherein at least one of:
• the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
• the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through
• the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.

An aircraft or spacecraft with an engine device and a fuel tank for accommodating a fluidic fuel, wherein the engine device comprises a combustion chamber with a nozzle and comprises an injector device arranged opposite the nozzle, wherein the injector device is configured for introducing the fluidic fuel and a fluidic oxidizing agent into the combustion chamber, which injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber,

• wherein at least one of at least one first resonator element is associated with the at least one first injection element and at least one second resonator element is associated with the at least one second injection element, and
• wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
• wherein at least one of:
• the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
• the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.

A method for operating an engine device, in which method a fluidic fuel and a fluidic oxidizing agent are introduced with an injector device into a combustion chamber of the engine device, which injector device comprises at least one first injection element for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber, wherein at least one of acoustic natural vibrations in the at least one first injection element and/or that acoustic natural vibrations in the at least one second injection element are dampened,

• wherein at least one of at least one first resonator element is associated with the at least one first injection element and at least one second resonator element is associated with the at least one second injection element, and wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
• wherein at least one of:
• the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
• the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.