Aspects of the disclosure are directed to a seal comprising: a shoe, and at least two beams coupled to the shoe, where a first width associated with the beams exceeds a second width associated with the shoe in a reference direction. Aspects of the disclosure are directed to an engine comprising: a compressor section, a turbine section, and a floating, non-contact seal that includes: a shoe, and at least two beams coupled to the shoe, where the beams extend past an edge of a flowpath surface associated with the shoe in a reference direction.

A non-contact seal assembly for sealing a gap between relatively rotatable components in a gas turbine engine is presented. The non-contact seal assembly includes a primary seal having a radially movable seal shoe, a mid-plate, an aft secondary seal radially movable along with the seal shoe, a forward secondary seal and a U-shaped seal carrier for holding the components together using pins. The seal shoe includes a plurality of seal shoe segments. The aft secondary seal includes a plurality of aft secondary seal segments. Each aft secondary seal segment is attached to each seal shoe segment. Each aft secondary seal segment includes at least a notch at outer radial side to receive the pin for accommodating radial movement of the seal shoe segment.

A seal assembly, including: a seal, the seal having; a support ring, a shoe, and a beam extending between the shoe and the support ring, wherein the shoe moves relative to the support ring via the beam; a spacer and a second seal; a seal ring; a carrier ring, the second seal being located adjacent to one end of the shoe and the seal ring being located adjacent to an opposite end of the shoe and the carrier ring extends from the seal ring to the spacer, the carrier ring being adjacent to the support ring of the seal; and a wear resistant coating located between a surface of the seal ring and an opposite end of the shoe.

An interstage seal for a turbine of a gas turbine engine, the interstage seal having a seal carrier with an axial extending seal tooth movable with a stator of the engine, and a rotor with a seal surface that forms the interstage seal with the seal tooth, where a magnetic force produced by two magnets and a gas force produced by a gas pressure acting on the seal carrier forms a balancing force to maintain a close clearance of the seal without the seal tooth contacting the rotor seal surfaces during engine operation. In other embodiments, two pairs of magnets produce first and second magnetic forces that balance the seal in the engine.

A seal assembly includes a seal arc segment that has first and second seal supports. A carriage has first and second support members. The first support member supports the seal arc segment in a first ramped interface and the second support member supports the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. First and second opposed springs bias the seal arc segment toward a circumferential default position.

A sealing arrangement includes a stationary component, a first slot is defined between an outer wall and a first inner wall, a second slot is defined between the outer wall and a second inner wall. A rotating component moves in a circumferential direction relative to the stationary component. The rotating component includes a tip rail. A floating seal positioned between the stationary component and the rotating component. The floating seal includes an axial member having a first arm extending into the first slot and a second arm extending into the second slot. The floating seal includes a first radial member and a second radial member that extends from the axial member. A plurality of magnets coupled to the stationary component, the rotating component, and the floating seal. The plurality of magnets is arranged such that the floating seal is contained between the stationary component and the rotating component.

A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.

A steam turbine includes a rotary shaft, a blade provided on an outer peripheral surface of the rotary shaft, a casing covering the rotary shaft and the blade from an outer peripheral side, a vane provided on an inner peripheral surface of the casing, and a seal device including a seal ring provided between the outer peripheral surface and the vane and a position adjusting portion configured to adjust a position of the seal ring in a radial direction. A seal clearance adjusting method includes a measurement step of measuring a length of the seal ring in the radial direction from a predetermined reference position as a reference length, a preparation step of preparing an unused seal ring, and an adjustment step of adjusting a length of the unused seal ring from the reference position to be the reference length by the position adjusting portion.

Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.

During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.