Aircraft comprising a gas turbine engine having an axially adjustable intake and a nacelle

1. An aircraft comprising:

a gas turbine engine comprising an intake, a nacelle, and gas turbine engine components located radially inside the nacelle; and

an aircraft structure;

wherein the intake of the gas turbine engine is mounted to the aircraft structure in a manner such that an axial position of the intake is adjustable;

wherein the nacelle and the gas turbine engine components located radially inside the nacelle are rigidly mounted to the aircraft structure;

wherein the intake is movable between a stowed position in which the intake is located adjacent the nacelle and a deployed position in which the intake is located at an axial distance to the nacelle during in-flight operation, wherein in the deployed position an axial gap is present between the nacelle and the intake;

an actuating mechanism that comprises at least one actuator and a sliding mechanism, wherein the actuating mechanism is configured to move the intake relative to the aircraft structure;

wherein an external portion of the intake is connected to the sliding mechanism and wherein the sliding mechanism is movable in the forward and rearward axial direction via the actuator;

wherein the actuator and the sliding mechanism are attached to an internal portion of the aircraft structure externally of the intake and nacelle;

wherein the aircraft structure is a fuselage of the aircraft.

2. The aircraft of claim 1 , wherein the aircraft is configured to move the intake into the deployed position during takeoff and at lower speeds of the aircraft.

3. The aircraft of claim 1 , wherein the intake and the nacelle comprise corresponding structures at their end faces that face each other wherein, in the stowed position, the intake and the nacelle create a consistent aerodynamic surface.

4. The aircraft of claim 1 , wherein the intake is movable to at least one intermediate position located between the stowed position and the deployed position.

5. The aircraft of claim 1 , wherein the actuating mechanism is a linear actuating mechanism moving the sliding mechanism and the intake in a linear manner.

6. The aircraft of claim 1 , wherein the intake is connected at a minimum of two mounting positions to the sliding mechanism.

7. The aircraft of claim 1 , wherein the sliding mechanism comprises at least one guidance rail that is movable relative to the aircraft structure, wherein the intake is connected to the guidance rail and wherein the guidance rail is driven by the actuator.

8. The aircraft of claim 1 , wherein the gas turbine engine comprises a central axis, wherein the intake is slidable with respect to the nacelle in and against the axial direction.

9. The aircraft of claim 1 , wherein the components of the gas turbine engine located radially inside the nacelle comprise a fan and an engine core located downstream of the fan.

10. A gas turbine engine comprising:

an intake, a nacelle, and gas turbine engine components located radially inside the nacelle;

wherein the intake of the gas turbine engine is configured to be mounted to an aircraft structure in a manner such that a position of the intake is adjustable;

wherein the nacelle and the gas turbine engine components located radially inside the nacelle are configured to be rigidly mounted to the aircraft structure;

wherein the intake is movable between a stowed position in which the intake is located adjacent the nacelle and a deployed position in which the intake is located at an axial distance to the nacelle during in-flight operation, wherein in the deployed position, an axial gap is present between the nacelle and the intake;

an actuating mechanism that comprises at least one actuator and a sliding mechanism, wherein the actuating mechanism is configured to move the intake relative to the aircraft structure;

wherein an external portion of the intake is connected to the sliding mechanism and wherein the sliding mechanism is movable in the forward and rearward axial direction via the actuator;

wherein the actuator and the sliding mechanism are attached to an internal portion of the aircraft structure externally of the intake and nacelle;

wherein the aircraft structure is a fuselage of the aircraft.

11. A method for adjusting an input of air flowing into a gas turbine engine attached to an aircraft, the method comprising:

connecting an intake of the gas turbine engine to an aircraft structure in a manner that allows the intake to be moved from one position to another;

connecting a nacelle and gas turbine engine components located radially inside the nacelle in a rigid manner to the aircraft structure;

adjusting an axial distance between the intake and the nacelle by moving the intake relative to the aircraft structure between a stowed position in which the intake is located adjacent the nacelle and a deployed position in which the intake is located at an axial distance to the nacelle during in-flight operation, wherein in the deployed position an axial gap is present between the nacelle and the intake;

providing an actuating mechanism that comprises at least one actuator and a sliding mechanism, wherein the actuating mechanism is configured to move the intake relative to the aircraft structure;

providing that an external portion of the intake is connected to the sliding mechanism and wherein the sliding mechanism is movable in the forward and rearward axial direction via the actuator;

providing that the actuator and the sliding mechanism are attached to an internal portion of the aircraft structure externally of the intake and nacelle;

providing that the aircraft structure is a fuselage of the aircraft.

12. The method of claim 11 , wherein the intake is moved in the deployed position at lower speeds and moved into the stowed position at higher speeds of the aircraft.