An aircraft with a jet engine that has a radially outer engine cowling and an auxiliary gear appliance that has multiple auxiliary devices and that can be driven by a shaft that is in operative connection with an engine shaft that rotates about a central axis. The auxiliary gear appliance is arranged in the radial direction of the jet engine at least partially outside the outer engine cowling of the jet engine.

A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.

A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.

A five-degree-of-freedom adjustment and positioning method and apparatus for assembly/measurement of rotor and stator of an aircraft engine; said method comprises adjusting a plane motion and a rotation of a tested piece through composite motion comprising five degrees of freedom: a 360 rotatory motion around a Z axis, a plane motion along an X axis and a plane motion along a Y axis, a rotatory motion around the X axis and a rotatory motion around the Y axis; said apparatus comprises: a clamping mechanism, a turning platform component, a translational platform component and a rotational platform component. The present invention designs a five-degree-of-freedom adjustment and positioning method and apparatus having properties of large load bearing, high precision and high stiffness, thus improving assembly efficiency and measurement accuracy of the aircraft engine.

A five-degree-of-freedom adjustment and positioning method and apparatus for assembly/measurement of rotor and stator of an aircraft engine; said method comprises adjusting a plane motion and a rotation of a tested piece through composite motion comprising five degrees of freedom: a 360 rotatory motion around a Z axis, a plane motion along an X axis and a plane motion along a Y axis, a rotatory motion around the X axis and a rotatory motion around the Y axis; said apparatus comprises: a clamping mechanism (1), a turning platform component (A), a translational platform component (B) and a rotational platform component (C). The present invention designs a five-degree-of-freedom adjustment and positioning method and apparatus having properties of large load bearing, high precision and high stiffness, thus improving assembly efficiency and measurement accuracy of the aircraft engine.