A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

System for selectively contacting a cleaning composition with a surface of a turbine engine component is presented. The system includes a cleaning apparatus and a manifold assembly. The cleaning apparatus includes an upper portion and a lower portion defining a cleaning chamber configured to allow selective contact between the cleaning composition and a surface of the first portion of the turbine engine component. The upper portion includes a plurality of fill holes in fluid communication with the cleaning chamber, and the lower portion includes a plurality of drain holes in fluid communication with the cleaning chamber. The manifold assembly is configured to selectively circulate the cleaning composition from a reservoir to the cleaning chamber via the plurality of fill holes, and recirculate the cleaning composition from the cleaning chamber to the reservoir via the plurality of drain holes. Methods for selectively cleaning a turbine engine component is also presented.

In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.

Disclosed is a turbo machine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbo machine comprises circuits (C1, C2) for pressurising these seals.

The invention relates to a wheel of a turbine engine comprising a plurality of radially extending vanes, one radially internal or external end of which is connected to an annular platform carrying annular lips (42, 44) extending from said platform in a direction opposite the vane in order to sealingly cooperate with a radially facing abradable material (28). According to the invention, the wheel comprises at least one lip (42, 44) having a concave curved upstream face and a convex curved downstream face or having a convex curved upstream face and a concave curved downstream face.

The invention relates to a turbine wheel (34) comprising a plurality of vanes connected to an annular platform (24) carrying annular lips (36, 38). According to the invention, one of the upstream lip (38) and the downstream lip (36) is of a first type or of a second type, with the first type corresponding to one lip (36) having the upstream face (36a) which is concave curved and the downstream face (36b) which is convex curved and the second type corresponding to a lip (38) having the upstream (38a) and downstream (38b) faces which are substantially flat and mutually parallel.

A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.

A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti-movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track.

A turbine blade disposed along a radial direction of a turbine includes: an airfoil portion positioned in a fluid flow passage of the turbine; and a shroud portion positioned on an inner side or an outer side of the airfoil portion in the radial direction, and having an opening with which an end portion of the airfoil portion is to be engaged. A clearance is formed between a wall surface forming the opening of the shroud portion and an outer peripheral surface of the end portion of the airfoil portion. The wall surface of the shroud portion and the outer peripheral surface of the airfoil portion are joined to each other. At least one of the shroud portion or the airfoil portion has a cooling hole formed thereon, the cooling hole having an opening into the clearance and being configured to supply the clearance with a cooling fluid.

A rotor blade system includes a blade root, a blade neck adjoining the blade root, an airfoil adjoining the blade neck, a radially outer partition wall, an axially forward partition wall and an axially rearward partition wall, connected to the radially outer partition wall such that the partition walls surround the blade neck on three sides, the partition walls projecting beyond the blade neck in the circumferential direction, and further including a blade root protection plate designed to be arranged on the blade root. It is provided that the blade root protection plate have at least one sealing portion that extends in the axial direction from the forward partition wall to the rearward partition wall and whose radially outer side is disposed opposite the radially outer partition wall when the blade root protection plate is arranged on the blade root.