The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

The present invention provides an airfoil 110 with the squealer tip cooling system 50 for a turbine blade 100 at the blade tip 113, wherein the squealer tip cooling system 50 comprises a cooling passage 170 arranged within a squealer tip 117, wherein the cooling passage 170 at least partly extends toward a terminal end 74 of the squealer tip 117, and a pocket 172 at a lateral surface 75, 76 of the squealer tip 117, open externally and extending inwardly at least partly across the cooling passage 170. The pocket 172 intersects the cooling passage 170 and the pocket 172 comprises an impingement surface 70 facing the cooling passage 170, on which a cooling medium expelled through the cooling passage 170 impinges before being discharged externally through the pocket 172.

A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.

An airfoil for a gas turbine engine defining a radial direction and an axial direction, the airfoil including: a flared portion extending from a suction surface of the airfoil at an outer edge of the airfoil along the radial direction; and a plenum disposed at the outer edge of the airfoil, the plenum having a suction-side sidewall and a pressure-side sidewall, wherein the suction-side sidewall has a first sidewall portion adjacent to a second sidewall portion disposed outside of the first sidewall portion along the radial direction, wherein the first sidewall portion defines a first angle, wherein the second sidewall portion defines a second angle, and wherein the first angle is greater than the second angle.