A compressor stator vane unit includes multiple compressor stator vanes disposed at a certain interval in a circumferential direction; and an annular joint member connected with inner ends of the multiple compressor stator vanes; wherein the annular joint member constitutes an outer diameter side surface of a leakage fluid flow path provided in an inner diameter side of the joint member to communicate a high-pressure space with a low-pressure space respectively located downstream and upstream of the multiple compressor stator vanes in a fluid flow direction, and D/P is set to 0.05≤D/P≤0.2, wherein D is defined as a distance in an axial direction between an upstream end surface of the annular joint member and an upstream edge of the multiple compressor stator vanes in the fluid flow direction and P is defined as a pitch between the adjacent compressor stator vanes in the circumferential direction.

A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.

A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

Assembly in a turbine comprising: —at least one turbine ring made of a ceramic composite having a silicon carbide SiC matrix and fibers, the ring comprising a plurality of sectors (10) arranged circumferentially end to end, each of the ring sectors (10) comprises at least one circumferential edge (26, 28) provided with at least one slot (30a, 30b, 30c) opening circumferentially, —at least one sealing member being inserted for a first part into one of the slots (30a, 30b, 30c) of an edge of a first ring sector and for a second part into one of the slots (30a, 30b, 30c) of an edge of a second ring sector, circumferentially adjacent to the first ring sector, the assembly being characterized in that the sealing member is made of a ceramic matrix composite.

Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.

A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches the wheel space. The rotor members each include a deflector. The deflector is placed in correspondence with each spacer and deflects the ingested gas flow over the upper surface of the spacer, thus preventing it to heat up the roots of the blades.