A fan blade capable of cooling an enclosed space is disclosed, comprising: a leading edge; a trailing edge; a top side; a bottom side; and a plurality of passageways wherein each of the passageways narrows within the fan blade. The plurality of passageways may narrow at any point within the interior of the fan blade and may be shaped in any way to ensure that a narrowing occurs. The plurality of passageways may also be in thermal communication with the rest of the fan blade. The fan blades may be used as part of a fan having a hub and a plurality of fan blades. Also disclosed, is a method of cooling a room comprising rotating a fan, the fan comprising: a plurality of fan blades, each fan blade having a plurality of passageways, wherein each of the passageways narrows within the fan blade.

An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.

A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Nozzle used for spraying a liquid substance towards a compressor of a gas turbine engine, comprising an elongated body having an end for ejecting the liquid substance, a conduit for the liquid substance internal to the elongated body and extending up to the end, a recess located at the end, wherein the conduit ends in the recess; wherein the recess opens towards the lateral surface of the elongated body, typically a cylindrical body, and the conduit is tangential to the bottom of the recess.

A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes an airfoil and a tip to discourage air leakage over the tip of the turbine blade. The turbine blade is designed considering weight and strength to include a lightening hole.

A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

A main-body casing having an inlet port or an outlet port, a rotatable rotor shaft, and a rotor coupled to the rotor shaft are provided. A recess portion opened toward the inlet port is formed in the rotor and a fastening portion (a first shaft portion and a second shaft portion) of the rotor shaft is exposed to the recess portion. A cover portion, which is fastened to the fastening portion by a cover-portion fixing bolt and covers at least a part of the recess portion, is formed having a container shape and has a reinforcing portion located in a periphery of the fastening portion that prevents deflection by increasing rigidity. The cover portion also has a contact-pressure generating portion which is pressed by fastening to the fastening portion in a fastening direction and causes a contact pressure to be generated in the fastening direction.

A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.