A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.

An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.

A non-contact seal assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. A first of the spring elements includes a first mount, a second mount and a spring beam. The spring beam extends a length longitudinally along a centerline from the first mount to the second mount. The spring beam includes opposing first and second surfaces. The first surface is disposed a first distance from the centerline, and the second surface is disposed a second distance from the centerline. The first distance and the second distance change as the spring beam extends longitudinally along the centerline to provide at least a portion of the spring beam with a tapered geometry. The portion of the spring beam has a longitudinal length that is at least about five percent of the length of the spring beam.

According to an embodiment, a rotor blade cover section is integrated with the rotor blades at leading ends thereof. A plurality of sealing fins is disposed at the rotor blade cover section, the sealing fins forming a predetermined clearance relative to an inner peripheral portion of the nozzle outer ring. An annular solid particle trapping space is disposed at the inner peripheral portion of the nozzle outer ring, the solid particle trapping space communicating with an inlet of a steam leak and trapping solid particles that flow in with steam. In the sealing structure, the nozzle outer ring has a through hole through which the solid particles are to be discharged from the solid particle trapping space toward a downstream stage of the steam turbine.

According to an embodiment, a rotor blade cover section is integrated with the rotor blades at leading ends thereof. A plurality of sealing fins is disposed at the rotor blade cover section, the sealing fins forming a predetermined clearance relative to an inner peripheral portion of the nozzle outer ring. An annular solid particle trapping space is disposed at the inner peripheral portion of the nozzle outer ring, the solid particle trapping space communicating with an inlet of a steam leak and trapping solid particles that flow in with steam. In the sealing structure, the nozzle outer ring has a through hole through which the solid particles are to be discharged from the solid particle trapping space toward a downstream stage of the steam turbine.

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 blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.

A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.

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 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.