Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.

Platforms for airfoils in gas turbine engines are provided. The platforms include an aero-structure defining a gaspath surface and a non-gaspath surface, a first securing element arranged to receive a locking pin and secure the aero-structure to a rotor disk, and a first securing element structure extending between the non-gaspath surface and the first securing element, wherein the first securing element structure comprises at least two legs defining a hollow space between the two legs and the non-gaspath surface.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

A rotor for a permanent magnet machine includes first and second axially successive rotor sections each including permanent magnets generating magnetic field having a pole pitch. The rotor includes a first coupling system for connecting the first rotor section to a shaft and a second coupling system for connecting the second rotor section to the shaft or to the first rotor section. The second rotor section is rotatable with respect to the first rotor section by an angle corresponding to the pole pitch in response to releasing the second coupling system so as to set the stator flux-linkages generated by the first and second rotor sections to be substantially zeroes. Thereafter, the permanent magnets do not substantially induce voltages on the stator windings even if the rotor is rotating during for example an internal fault of stator windings.

A method to repair a peripheral portion of a body including: removing a damaged portion from a peripheral region of the body; mounting a replacement ring to the body after removal of the damaged portion; forming an interior groove between the inner surface of the replacement ring and the peripheral surface of the body, wherein the groove is between ridges; welding the replacement ring to the body, wherein weld material is applied only within end grooves, and leaving a void in said center section after the welding of the replacement ring to the body.

A reinforced component in accordance with various embodiments includes a metal lug configured to be attached to a secondary component. The reinforced component further includes a composite material integrally formed around the metal lug and configured to be retained in place relative to the secondary component via an attachment between the metal lug and the secondary component.

A blade fastening assembly and a gas turbine including the same are proposed. The blade fastening assembly includes a fastening key having a threaded hole, a rotor disk including a disk slot into which a root member is inserted, the rotor disk having a first groove with a shape corresponding to a portion of the fastening key, a first portion of a second groove adjacent to the first groove, and a pin groove connected with the first groove, a platform having a second portion of the second groove formed in communication with the first portion of the second groove and the first groove and forming a shape corresponding to a remaining portion of the fastening key in a state of being inserted into the disk slot, and a fastening pin inserted into the threaded hole and the pin groove.

A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

In one embodiment, a hub for a fan of a gas turbine engine is provided. The hub having: a plurality of attachment features located on an outer circumferential surface of the hub, wherein at least some of the plurality attachment features extend radially away from the outer circumferential surface and are axially aligned with each other and at least some of the plurality of attachment features extending radially away from the outer circumferential surface and are off set from each other, and wherein the plurality of attachment features have an opening configured to receive a portion of a pin; and wherein at least some of the plurality of attachment features are located on a forward leading edge of the hub.