The present application provides a
turbojet engine and aircraft, relating to the field of aero-engine technology, comprising a casing having a
combustion chamber, a compressor and a
turbine respectively arranged at the air inlet and air outlet of the casing, and a
tail nozzle connected to the
turbine, wherein the compressor and the
turbine are connected in a transmission manner, and a micro-perforated plate
metal foam
composite structure is provided along the circumferential direction on the inner wall of the air inlet of the casing to reduce the
noise generated when air enters the casing. A plurality of axially extending
airflow channels are provided along the circumferential direction on the inner wall of the
tail nozzle, each
airflow channel including a plurality of interconnected
airflow grooves, and the plurality of airflow grooves constituting the same airflow channel are connected end to end along the axial direction of the
tail nozzle so that each airflow channel forms a Tesla valve structure. The
flow diversion direction of the Tesla valve structure is consistent with the direction of airflow ejected from the casing into the
atmosphere, effectively suppressing the generation of
noise at the sound source, achieving a
broadband noise reduction effect, and reducing the complexity and weight of the
system, thereby controlling thrust loss to an extremely low level.