A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.

An aerodynamic arm for an aircraft turbine engine casing includes a tubular outer shell having a generally elongate shape extending substantially along an axis. The shell has axial ends configured to be connected to a turbine engine casing. An electrically conductive core extends inside the shell and has ends configured to electrically connect to the ends of the shell. An insulating material occupies a space between the core and the shell.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

A gas turbine engine including a composite case having a conductive path therein, and a conductive case connected to the composite case. The conductive case is made of a conductive material. A fastener connects the composite case to the conductive case. The fastener is conductively connected to the conductive material of the conductive case and not directly conductively connected to the conductive path. At least one voltage discharge channeling assembly is connected to the fastener and to the conductive case. The at least one voltage discharge channeling assembly has a portion conductively connected to the conductive path. The at least one voltage discharge channeling assembly is conductively connected to the fastener. A method of assembling an engine casing in a gas turbine engine is also provided.

A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying, via a gas, a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and measuring a pressure of the gas. This process may be performed over time to determine a lifespan of the propellant grain.

A coaxial cable system includes an electric conductor to conduct electric power in a gas turbine engine. The system also includes a dielectric tape helically wound to contiguously surround the electric conductor and a flexible conduit disposed to surround and contiguously contact the dielectric tape. A dielectric liquid may be impregnated within the dielectric tape, and a flexible protective cover may concentrically disposed to surround the flexible conduit.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

A seal assembly for a gas turbine engine, having a seal formed of a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the seal and the seal seat each have a sealing surface which together define a sliding seal, and wherein at least the sealing surface of the seal seat is made of the same carbon material as the sealing surface of the seal.

A fan motor includes: a motor housing; a rotating shaft; a rotor; a stator disposed outside the rotor; an impeller having at least one blade and a hub; and an impeller cover surrounding an outer circumference of the impeller and defining an air suction inlet. The impeller cover includes: a shroud having an inner diameter that expands in an air flow direction; and a non-metallic coating layer coated on an inner circumferential surface of the shroud and having a lower strength than the blade. The non-metallic coating layer includes: a first area having a first thickness; a second area having a second thickness thinner than the first thickness and defining a stepped portion with the first area, thereby minimizing leakage flow caused by the pressure difference from a pressure-side surface to a suction-side surface of the blade to reduce flow path loss and improving efficiency of the fan motor.

The invention relates to a method for manufacturing a carrying casing (12) provided with a collar (18) for supporting at least one cartridge of abradable material for a turbomachine, said carrying casing (12) comprising at least one bare annular casing (16) and one block of honeycomb material (20) that comprises an outer face (22) configured to be secured to an inner face (24) of said bare annular casing (16), said block being covered with a skin (26), characterized in that it comprises successively: —a step in which the outer face (22) of the block (20) is secured to the inner face (24) of the bare annular casing (16), —a step in which the circularity of San inner face (32) of the block (20) is monitored and in which, if necessary, the inner face (32) of the block (20) is machined to round, —a step in which, simultaneously, said skin (26) is produced and is secured to said block (20).