An electric fan for producing thrust to propel an aircraft is disclosed. The electric fan comprises a stator, a fan rotor rotatably mounted relative to the stator and an electric motor mounted to the stator and drivingly engaged with the fan rotor to cause rotation of the fan rotor relative to the stator. The fan rotor comprises an annular body defining a flow passage therethrough and a plurality of fan blades disposed in the flow passage and mounted for common rotation with the annular body about a fan rotation axis. The electric motor has a motor rotation axis that differs from the fan rotation axis.

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.

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.

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.

An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.

The present disclosure relates to and envisages a compressed air generation system. The compressed air generation system includes a multistage reciprocating compressor for providing compressed air at a high pressure. A combi-cooler assembly includes a pair of intercoolers and a radiator assembly is configured to dissipate heat recovered by the cooling fluid from first reciprocating compression stage, second reciprocating compression stage, third reciprocating compression stage and crankcase assembly of the radiator circuit. The system is a stand-alone unit.

Disclosed in the present application is a blade and an axial flow impeller using same. The blade comprises a blade tip, a blade root, a leading edge, a trailing edge, an upper surface and a lower surface. The upper surface and lower surface are disposed opposite each other; the blade tip, the blade root, the leading edge and the trailing edge surround the upper surface and the lower surface, and connect the upper surface and the lower surface. The blade is rotatable about a rotation axis, the rotation axis being perpendicular to a normal plane. The blade tip comprises a blade tip base part and a blade tip trailing part, the blade tip base part being close to the leading edge, and the blade tip trailing part being close to the trailing edge and being bent upwards relative to the blade tip base part. An angle of attack of a chord of the blade tip trailing part is greater than an angle of attack of a chord of the blade tip base part, wherein the angle of attack is an acute included angle between the chord and the normal plane. The blade of the present application can provide a large air volume, and has higher static pressure and higher efficiency.

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.

A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a tip component removably connected to the blade body, the tip component formed of a second material that is different than the first material.