Air conduction system
The invention relates to an air conduction system for an aircraft engine with a primary flow channel and a branch channel, in which, in particular, the branch channel can be a secondary flow channel and/or a bleed air channel, wherein the branch channel branches off the primary flow channel at a connecting region, comprising a closing device arranged at or in the connecting region for separating the branch channel from the primary flow channel, wherein the closing device has at least one closing ring for closing the connecting region.
1. An air conduction system for an aircraft engine having an engine axis with a primary flow channel and a branch channel, wherein the branch channel is a secondary flow channel and/or a bleed air channel and wherein the branch channel branches off the primary flow channel at a connecting region, comprising:
a closing device arranged at or in the connecting region for separating the channel from the primary flow channel; the closing device having at least one closing ring for closing the connecting region and an actuator configured and arranged for displacing the closing ring;
wherein the closing ring is displaced by the actuator in an axial direction and in a circumferential direction.
2. The air conduction system according to claim 1 , wherein the closing ring is formed from at least two elements including a first element and a second element, which are joined to one another and are bent at least in the circumferential direction and are configured and arranged as sheet-metal-like annular elements.
3. The air conduction system according to claim 2 , wherein the first element of the closing ring is formed to be flat in an axial direction to enable sliding thereof in the axial direction.
4. The air conduction system according to claim 3 , wherein the first element, which is planar, is configured and arranged to glide over at least one radially inner sliding element fastened in the branch channel wherein the sliding element is a sliding block made of a polyimide.
5. The air conduction system according to claim 2 , wherein the second element of the closing ring is configured and arranged to be curved radially outward relative to the engine axis.
6. The air conduction system according to claim 2 , wherein the at least two elements are joined to each other at a ring front edge, which is a front edge of the closing ring in the axial direction and forms an angle.
7. The air conduction system according to claim 2 , wherein the at least two elements are joined through a reinforcement strut to form a hollow body.
8. The air conduction system according to claim 1 , wherein a drive of the actuator is arranged radially outside of the branch channel.
9. The air conduction system according to claim 1 , wherein a drive rod of the actuator is passed from radially outside of the branch channel through the branch channel and into an intermediate housing, which radially separates the primary flow channel and the branch channel from each other, and is pivotably connected to the closing ring by way of an adjusting lever of the actuator to displace the closing ring in the axial direction and in the circumferential direction.
10. The air conduction system according to claim 9 , wherein at least one guide lever of the closing device is pivotably connected to the intermediate housing to stabilize a sliding movement of the closing ring.
11. The aircraft engine with the primary flow channel and the branch channel, wherein the branch channel branches off the primary flow channel at the connecting region, comprising the air conduction system according to claim 1 .