A clearance-control-type seal structure including a plurality of arc-shaped grooves (23) formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings (11, 12) having fitting parts (11a, 12a) that are fitted into the grooves so as to leave a prescribed gap, that have extended parts (11b, 12b) that are exposed from the housing in the radial direction toward the inside and expand in the axial direction, and that, during operation, due to back pressure inside the grooves, receive a force that moves in the radial direction toward the inside. One extended part has a protruding part extending even further in the axial direction toward the upstream side, and the other extended part has formed in an outer circumferential surface of a downstream-side end part thereof a recessed part that corresponds to the protruding part.

A clearance-control-type seal structure including a plurality of arc-shaped grooves (23) formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings (11, 12) having fitting parts (11a, 12a) that are fitted into the grooves so as to leave a prescribed gap, that have extended parts (11b, 12b) that are exposed from the housing in the radial direction toward the inside and expand in the axial direction, and that, during operation, due to back pressure inside the grooves, receive a force that moves in the radial direction toward the inside. One extended part has a protruding part extending even further in the axial direction toward the upstream side, and the other extended part has formed in an outer circumferential surface of a downstream-side end part thereof a recessed part that corresponds to the protruding part.

A contra-flow strip for inhibiting leakage of a fluid between a rotating member and a stationary member includes, for example, a base supportable by the stationary member coaxially around the rotating member, and means, extending from the base coaxially towards the rotating member between a low pressure region and a high pressure region, for generating a contra flow of a portion of a tangential flow of fluid in the low pressure region to the high pressure region between the stationary member and the rotating member.

A tip shroud for a turbine blade of a gas turbine system includes a body coupled to a radial outer end of an airfoil of the turbine blade. The tip shroud may include at least one circumferentially extending tip rail. A first edge wall of the tip shroud extends axially and radially outwardly from the body along at least one of a leading circumferential-facing edge or a trailing circumferential-facing edge of the body and includes a circumferentially facing surface. Cooling passages are defined in the body and extend circumferentially therein to cool an area near the first edge wall. The tip shroud includes an exit surface adjacent the first edge wall, where the exit surface includes an exit opening through which at least one of cooling passages exits the body. The exit surface is angled relative to the circumferentially facing surface of the first edge wall in a range of 15° to 80°.

A seal structure includes: a first member and a second member disposed so as to face a combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage; a heat-resistant coating formed on at least one of a first end face and a second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side than the heat-resistant coating. When the first member and the second member move relatively toward each other, the contact part restricts the relative movement by coming in contact in a state where a clearance is left between the heat-resistant coating and the face facing the heat-resistant coating.

A seal structure includes: a first member and a second member disposed so as to face a combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage; a heat-resistant coating formed on at least one of a first end face and a second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side than the heat-resistant coating. When the first member and the second member move relatively toward each other, the contact part restricts the relative movement by coming in contact in a state where a clearance is left between the heat-resistant coating and the face facing the heat-resistant coating.

An apparatus is disclosed including a first article, a second article, and a third article disposed adjacent to one another, with the first article and the second article disposed between the third article and a gas path. The first article includes at least one first ceramic matrix composite ply defining a first cooperating feature. The second article includes at least one second ceramic matrix composite ply defining a second cooperating feature. The first cooperating feature and the second cooperating feature define a restricted flow path from the gas path to the third article, which includes a reduced volumetric flow rate of a gas from the gas path to the third article relative to a non-restricted flow path of a non-cooperating interface. A method for forming the apparatus includes forming and aligning the first cooperating feature and the second cooperating feature.

An air riding seal for a turbine in a gas turbine engine, where an annular piston is axial moveable within an annular piston chamber formed in a stator of the turbine and forms a seal with a surface on the rotor using pressurized air that forms a cushion in a pocket of the annular piston. A purge cavity is formed on the annular piston and is connected to a purge hole that extends through the annular piston to a lower pressure region around the annular piston or through the rotor to an opposite side. The annular piston is sealed also with inner and outer seals that can be a labyrinth seal to form an additional seal than the cushion of air in the pocket to prevent the face of the air riding seal from overheating.

An apparatus and method of cooling a tip of an airfoil for a gas turbine engine, includes a rib circumscribing the tip to define a tip plenum. A tip baffle partially divides the tip plenum, being spaced from the rib by a baffle slot. The rib includes a tip slot in fluid communication with the baffle slot to provide a flow of cooling fluid along the tip of the airfoil for exhausting out the tip slot.

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.