Disclosed is a turbine apparatus. The turbine apparatus includes s stator, a rotor rotatably installed in the stator, and a sealing mechanism provided to prevent a working fluid from leaking between the stator and the rotor. The sealing mechanism is configured such that when the rotor is stopped, the sealing mechanism is brought into contact with the rotor, and when the rotor is rotated, the sealing mechanism is formed to be spaced from the rotor by a predetermined gap.

A seal assembly for a gas turbine engine includes a seal including a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core including one or more core plies arranged to establish an internal cavity. An overwrap has one or more overwrap plies arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion. A platform insert extends between portions of the core and the overwrap to establish the sealing portion. A method of fabricating a seal for a gas turbine engine is also disclosed.

A seal assembly for a gas turbine engine includes a seal including a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core including one or more core plies arranged to establish an internal cavity. An overwrap has one or more overwrap plies arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion. A platform insert extends between portions of the core and the overwrap to establish the sealing portion. A method of fabricating a seal for a gas turbine engine is also disclosed.

Disclosed is a blade, having: a blade root; a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body; a squealer pocket located in the blade tip; and a first wearable tip-rub-portion located radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end.

A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.

A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

An assembly is provided for rotational equipment. This rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially about an axial centerline in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the annular array. The spring elements include a first spring element. The first spring element connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. An axial end portion of the first seal shoe projects axially along the axial centerline, in a direction away from the first spring element, beyond the secondary seal assembly.

An assembly is provided for rotational equipment. This rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially about an axial centerline in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the annular array. The spring elements include a first spring element. The first spring element connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. An axial end portion of the first seal shoe projects axially along the axial centerline, in a direction away from the first spring element, beyond the secondary seal assembly.

Clearance control systems with electromagnetic actuators are disclosed. An example electromagnetically-actuated clearance control system for a gas turbine engine comprises an electromagnetic coil coupled to a first end of a facesheet, the electromagnetic coil to generate a magnetic field in response to a connection of a power supply, a ferromagnetic sheet coupled to a second end of the facesheet, the ferromagnetic sheet drawn radially-inward toward the electromagnetic coil when the magnetic field is generated, a first end of the ferromagnetic sheet coupled to a first compression spring and a second end of the ferromagnetic sheet coupled to a second compression spring, the first and second compression springs to compress in response to the ferromagnetic sheet being drawn radially-inward.