A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.

An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90°.

An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

A coating method includes depositing a slurry including a coarsely particulate ceramic and a finely particulate ceramic on a base material configured with an oxide-based ceramics matrix composite such that a proportion of coarse particles decreases towards a surface of the base material; forming a bond coating by performing a heat treatment on the base material on which the slurry has been deposited; and forming a top coating by thermally spraying a ceramic onto the bond coating. The oxide-based ceramics matrix composite is an alumina silica type oxide-based ceramics matrix composite. The coarsely particulate ceramic and the finely particulate ceramic are alumina-based powder.

An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

The present invention relates to a rotor blade arrangement for a turbomachine, with a rotor blade which has a sealing tip radially on the outside, and with a seal arrangement, wherein the seal arrangement forms a radially inwardly open cavity, in which the sealing tip is arranged, to which end the seal arrangement has a first sealing element, namely a first seal carrier with a first run-in coating, and a second sealing element, wherein the first run-in coating delimits the cavity radially on the outside, and the second sealing element delimits the cavity in an axial direction, and wherein the first and the second sealing element are assembled.

An assembly for a turbomachine turbine includes a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.

An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

The invention relates to an assembly for a turbomachine, comprising a stator (1) and a rotor (2) rotatable relative to the stator (1) about an axis, the rotor (2) comprising blades each ×comprising a vane (3) connected to a radially inner platform (5), a block of abradable material (6) extending radially inwardly from the radially inner platform (5) the stator (1) having a shroud comprising an annular area (9), at least one lug (12) extending radially outwardly from said annular area (9), the radially outer end of the lug (12) cooperating with the block of abradable material (6).