A flow path component assembly includes a support structure. A flow path component has a plurality of segments that are arranged circumferentially about an axis and are mounted in the support structure by a carrier. At least one of the segments have a first wall axially spaced from a second wall. The first wall has first and second hooks spaced apart from one another in a circumferential direction. The second wall has third and fourth hooks spaced apart from one another in the circumferential direction. The first, second, third, and fourth hooks are in engagement with the carrier.

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

A ring-segment surface-side member is included in a ring segment disposed at a position opposite to a turbine blade on a stationary side of a gas turbine, serves as a part of a combustion gas flow path through which combustion gas flows, and is formed of a ceramic matrix composite. The ring-segment surface-side member includes: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

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.

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.

A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and mounted in a carrier. At least two of the plurality of segments have a first wall that extends radially outward from a base portion. The base portion has a radially inner side and a radially outer side. A heat shield abuts the radially outer side of the at least two segments. The heat shield is formed from a ceramic material.

A flow path component assembly includes a support structure. A flow path component has a plurality of segments that are arranged circumferentially about an axis and are mounted in the support structure by a carrier. At least one of the segments have a first wall axially spaced from a second wall. The first wall has first and second hooks spaced apart from one another in a circumferential direction. The second wall has third and fourth hooks spaced apart from one another in the circumferential direction. The first, second, third, and fourth hooks are in engagement with the carrier.

A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.