A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

An aircraft turbine-engine module casing including an external module casing and at least one sealing ring intended to surround a movable impeller of the module and arranged radially towards the inside with respect to the external casing. The casing includes at least one capillary heat pipe, a first end which is fixed to the sealing ring, and a second end which, opposite to the first, is fixed to a casing element arranged radially towards the outside with respect to the ring.

An aircraft turbine-engine module casing including an external module casing and at least one sealing ring intended to surround a movable impeller of the module and arranged radially towards the inside with respect to the external casing. The casing includes at least one capillary heat pipe, a first end which is fixed to the sealing ring, and a second end which, opposite to the first, is fixed to a casing element arranged radially towards the outside with respect to the ring.

A flow guiding system for a rotary combustion engine, in particular an aircraft jet engine. The flow guiding system comprises a bypass region positioned radially around a core region, a flow scoop device for guiding a first airflow from the bypass region, at least one flow guiding device for decoupling the flow regime in a region containing a flammable fluid from a flow regime in a region with tip clearance control by at least partially guiding at least one airflow divided from the first airflow, a second airflow directed into the region containing flammable fluid, and/or a third airflow directed into a region away from the region containing flammable fluid.

A flow guiding system for a rotary combustion engine, in particular an aircraft jet engine. The flow guiding system comprises a bypass region positioned radially around a core region, a flow scoop device for guiding a first airflow from the bypass region, at least one flow guiding device for decoupling the flow regime in a region containing a flammable fluid from a flow regime in a region with tip clearance control by at least partially guiding at least one airflow divided from the first airflow, a second airflow directed into the region containing flammable fluid, and/or a third airflow directed into a region away from the region containing flammable fluid.

A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

A ring segment includes segment bodies arranged along a circumferential direction; a main cavity; first cooling channels inside the segment body to extend along an axial direction of a rotor and arrayed in the circumferential direction, and whose ends communicate with the main cavity on an upstream side thereof; a second cooling channel inside the segment body on an upstream side in a rotation direction of the rotor to extend along the axial direction, and whose first end communicates with the main cavity on the upstream side thereof; and third cooling channels to extend along the circumferential direction, in a predetermined region forming a part of a lateral end of the segment body on the upstream side and stretching from an end of the segment body on a downstream side in the combustion gas flow direction toward the upstream side, and whose first ends communicate with the second cooling channel.

A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.

The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.