The invention relates to an engine (2) for an aircraft (1), comprising a ring-shaped vortex guide element (3) which has, in a sectional view, an air inlet opening (6) which is located centrally in relation to a longitudinal center axis (4) of the engine (2), and an air outlet opening (7) which is located centrally in relation to the longitudinal center axis (4) and is spaced apart from the air inlet opening (6), which openings are fluidically interconnected via an intake channel (5) which is delimited by the vortex guide element (3) and accommodates an air conveying device (8), wherein an air deflecting element (9), which is located geodetically above the vortex guide element (3) during operation of the engine (2) as intended, extends over the air outlet opening (7), which air deflecting element extends radially outward from the air outlet opening (7) so as to delimit, together with the vortex guide element (3), an air exit gap (11) which is in flow connection with the air outlet opening (7). According to the invention, the vortex guide element (3) is provided as a rotary body which is formed by the rotation of a closed cam about an axis of rotation, which cam has a continuous course at least on its radially outer side, and the air inlet opening (6) opens directly into the outer surroundings (19) of the engine (2), so that, during operation of the engine (2) as intended, air is conveyed from the side of the engine (2) which is remote from the air deflecting element (9) through the air inlet opening (6) and into the intake channel (5). The invention also relates to a method for operating an engine (2) for an aircraft (1) and to an aircraft (1) having at least one engine (2).
Engine for an aircraft, method for operating an engine for an aircraft, and aircraft having at least one engine
2023-03-02
Patent
Electronic Resource
English
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