A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root.

A gas turbine engine system comprises a rotor wheel, a plurality of blades, a lockwire and a locking key. The rotor wheel comprises a plurality of axial grooves extending through a periphery of the rotor wheel, and a plurality of posts formed between adjacent slots, each post having a circumferential slot. The blades are mounted in the axial grooves of the rotor wheel, each blade having a circumferential slot circumferentially aligned with the circumferential slots of the posts. The lockwire extends across the plurality of axial grooves of the rotor wheel within each of the circumferential slots of the posts and the blades from a first end to a second end to inhibit axial displacement of the blades within the grooves. The locking key is disposed between the first and second ends of the lockwire and provides support to at least one of the ends of the lockwire to prevent radially inward displacement.

A variable pitch fan for a gas turbine engine includes a fan blade defining a pitch axis and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment. A key is positioned at least partially in a key slot defined in a base of the trunnion mechanism, and further positioned adjacent to a support member of the disk segment. The key defines a first contact line between the key and the key slot and a second contact line between the key and the support member. The first and second contact lines respectively define a first contact reference line in a second contact reference line. The first and second contact reference lines define an angle with the pitch axis of the fan blade greater than zero degrees and less than ninety degrees.

A securing device for a turbine blade wherein the securing device prevents the turbine blade from moving radially and axially and includes a retaining piece that includes a projection which extends into a recess in the root of the turbine blade and which prevents the blade from moving axially.

An apparatus for axial locking of a bucket includes a depressed portion formed on an end portion of a male dovetail extending from a bucket and on an outer side of a seating groove of a female dovetail disposed on an outer circumferential surface of a rotor disk, and a locking member disposed in the depressed portion and configured to contact the male dovetail and the seating groove of the female dovetail to prevent the bucket mounted on the rotor disk from being separated in the axial direction.

There is provided a turbine including a rotor wheel including a plurality of dovetail grooves and at least one insertion groove, the dovetail grooves and the insertion groove arranged in a circumferential direction of the rotor wheel; a plurality of first buckets, each of the first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to a corresponding dovetail groove; at least one second bucket including a vane, a platform provided at a first end portion of the vane, and at least one protrusion portion provided at the platform and configured to be inserted into a corresponding insertion groove of the insertion groove; and a fixing member configured to be inserted through the protrusion portion and the rotor wheel and configured to restrict radial movement of the second bucket.

A fan for a gas turbine engine, the fan comprising a first set of fan blades each fan blade comprising a root and an axial retention feature provided on the root at a first position, and a second set of fan blades each fan blade comprising a root and an axial retention feature provided on the root at a second position. Relative to the respective blade on which the respective retention feature is provided, the first position is different to the second position.

The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot. The keyway restrains the first wedging body against movement in the axial direction. The first wedging body further has a first angled surface over which a correspondingly angled leading end surface of the root slides when the root is inserted in the slot to urge the leading end of the root radially outwardly.

An assembly for receiving in a radially extending bucket groove (31) of a turbine disc (22), the assembly including a turbine blade having an elongate body (26) of aerofoil cross-section, a root portion (24) at one end of the elongate body (26) and a tip at the other. The root portion (24) configured to be retained in the bucket groove (31). A heat shield (27) configured to be received between an end of the root portion (24) and a radially inner surface of the bucket groove (31) and to interlock with the root portion (24) in a manner which deters separation in a radial direction.