A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.

The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.

The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.

An internal casing ferrule for a turbomachine, centered on a longitudinal central axis, which includes: a main body centered on this axis, with two ends, delimited by surfaces that are radially inner and outer relative to this axis; a thermal porous-structure insulation envelope having a volumetric porosity ≥50%, which includes: a lateral portion entirely covering the two ends; when viewed in section transversely to this axis, exterior and interior portions entirely covering, respectively, the radially outer and inner surfaces of the main body; and a protective envelope which at least partially covers the envelope and which includes, when viewed in section transversely to this axis, radially outer and inner protective portions, respectively covering, at least in part, the exterior and interior portions.

A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10). Thus, the clearance control system (12) can set the gap (14) between turbine blade tips (16) and ring segments (18) to be zero at steady state operation.

A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10). Thus, the clearance control system (12) can set the gap (14) between turbine blade tips (16) and ring segments (18) to be zero at steady state operation.

A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

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.