Abstract: An annulus filler element (40) for a rotor of a turbomachine, the annulus filler element (40) comprising: a lid portion (42) having a radially outwardly facing surface for forming an inner wall of a flow annulus of the rotor between adjacent blades (102) and a radially inwardly facing surface; and a nose cone attachment portion (52) integrally formed with the lid portion (42) for connection with a nose cone (122) of the turbomachine.

Abstract: The invention provides an arrangement for mounting a nose cone 32 on a gas turbine engine. The nose cone 32 has an inwardly tapering flange 64 which defines an inclined contact surface 68. A nose cone support ring 36, mounted in use to a flange 38 on the front of the fan disc 34, has an outer rim 42. An inwardly extending part 50 of the support ring 36 defines an inclined contact surface 54. A plurality of spaced radial openings 44 are provided through the rim 42 each having a countersunk opening 46. A fastening arrangement 70, associated in use with each opening 44, comprises a bolt 72 with a countersunk head. A Vee block 76 locates on each bolt 72, with a mounting nut 78 below it. In use, the nose cone 32 is brought up against the support ring 36. Appropriate rotation of the bolts 72 will cause the nuts 78 and hence Vee blocks 76 to move radially outwardly.

Abstract: An annulus filler element (40) for a rotor of a turbomachine, the annulus filler element (40) comprising: a lid portion (42) having a radially outwardly facing surface for forming an inner wall of a flow annulus of the rotor between adjacent blades (102) and a radially inwardly facing surface; and a nose cone attachment portion (52) integrally formed with the lid portion (42) for connection with a nose cone (122) of the turbomachine.

Abstract: The invention provides an arrangement for mounting a nose cone 32 on a gas turbine engine. The nose cone 32 has an inwardly tapering flange 64 which defines an inclined contact surface 68. A nose cone support ring 36, mounted in use to a flange 38 on the front of the fan disc 34, has an outer rim 42. An inwardly extending part 50 of the support ring 36 defines an inclined contact surface 54. A plurality of spaced radial openings 44 are provided through the rim 42 each having a countersunk opening 46. A fastening arrangement 70, associated in use with each opening 44, comprises a bolt 72 with a countersunk head. A Vee block 76 locates on each bolt 72, with a mounting nut 78 below it. In use, the nose cone 32 is brought up against the support ring 36. Appropriate rotation of the bolts 72 will cause the nuts 78 and hence Vee blocks 76 to move radially outwardly.

Abstract: A gas turbine engine nose cone (44) comprises a spinner (46) and a fairing (48). The spinner (46) has a conical upstream portion (50) and a cylindrical base portion (52). The fairing (48) is frustoconical and surrounds the base portion (52) of the spinner (46). The outer surface (68) of the fairing (48) forms a continuation of the outer surface (56) of the conical upstream portion (50) of the spinner (46). A fibrous material (86) extends around the upstream end (82) of the fairing (48). The outer surface (68) of the fairing (48) has a skin (80) to protect the fairing (48) from erosion. The skin (80) extends around the upstream end (82) of the fairing (48) and is infiltrated into the fibrous material (86) to form a composite material and to bond the skin (80) to the upstream end (82) of the fairing (48).

Abstract: A gas turbine engine nose cone (44) comprises a spinner (46) and a fairing (48). The spinner (46) has a conical upstream portion (50) and a cylindrical base portion (52). The fairing (48) is frustoconical and surrounds the base portion (52) of the spinner (46). The outer surface (68) of the fairing (48) forms a continuation of the outer surface (56) of the conical upstream portion (50) of the spinner (46). A fibrous material (86) extends around the upstream end (82) of the fairing (48). The outer surface (68) of the fairing (48) has a skin (80) to protect the fairing (48) from erosion. The skin (80) extends around the upstream end (82) of the fairing (48) and is infiltrated into the fibrous material (86) to form a composite material and to bond the skin (80) to the upstream end (82) of the fairing (48).

Abstract: A gas turbine engine nose cone (44) comprises a spinner (46) and a fairing (48). The spinner (46) has a conical upstream portion (50) and a cylindrical base portion (52). The fairing (48) is frustoconical and surrounds the base portion (52) of the spinner (46). The outer surface (68) of the fairing (48) forms a continuation of the outer surface (56) of the conical upstream portion (50) of the spinner (46). The outer surface (68) of the fairing (48) has a skin (80) to protect the fairing (48) from erosion and a protective member (86) extends around the upstream end (82) of the fairing (48) to retain the skin (80) on the upstream end (82) of the fairing (48).

Abstract: A gas turbine engine nose cone (44) comprises a spinner (46) and a fairing (48). The spinner (46) has a conical upstream portion (50) and a cylindrical base portion (52). The fairing (48) is frustoconical and surrounds the base portion (52) of the spinner (46). The outer surface (68) of the fairing (48) forms a continuation of the outer surface (56) of the conical upstream portion (50) of the spinner (46). The outer surface (68) of the fairing (48) has a skin (80) to protect the fairing (48) from erosion and a protective member (86) extends around the upstream end (82) of the fairing (48) to retain the skin (80) on the upstream end (82) of the fairing (48).