United Technologies Corporation

Stephen M Antonellis

Frank Heydrich

Roger D Breunig

A rotor assembly for a gas turbine engine includes a rotor configured for rotation about an engine axis, the rotor including an aft surface including a rotor slot and a cover plate attached to the aft surface of the rotor, the cover plate including a tab received within the rotor slot and a cover plate slot aligned with the rotor slot. A lock assembly disposed within the rotor slot holds a position of the cover plate relative to the rotor. The lock assembly includes a key portion conforming to the rotor slot, a lock portion engageable with a surface of the rotor slot and a threaded member for holding the lock assembly within the rotor slot.

Turbine rotor cover plate lock

A turbine section having a seal cavity with effectively continuous flow surfaces is disclosed. Various construction details are developed which disclose a fluid cooled stator assembly having a plurality of ejectors for flowing cooling fluid into the seal cavity. In one embodiment, the ejectors (114) include a wall (132) which have circumferentially spaced mating edges (134, 136) arranged in a cascade type configuration. The arrangement of the walls provides an effectively continuous flow surface for the radially flowing annulus of cooling fluid within a seal cavity (108). In an alternate embodiment, an opening (152) between adjacent mating edges (154, 156) provides access to mechanical fasteners (162) which retain a sealing shroud (164) to a stator assembly (150).

Cooling fluid ejector

An active cooling mechanism for a turbine disk is disclosed. Various construction details are developed which disclose a turbine section having a rotor assembly, a disk with an attachment means, a radially movable heat shield disposed therebetween, and a cooling passage which directs cooling air over the forward surface and radially outer surface of the attachment means. During operation, rotational forces urge the heat shield radially outward to create a gap between the heat shield and the attachment means, the gap defining a portion of the cooling passage.

Active cooling of turbine rotor assembly

A rotor assembly (34) includes a disk (36) having an axially extending, unbroken annular spigot (38). The spigot (38) supports a plurality of radially extending lugs (42) which are juxtaposed with a corresponding plurality of dogs (14) integral with an annular sideplate (12). A smooth key (54) fits within the opening (44) formed between adjacent engaged dogs and lugs (14, 42) and is retained axially by a sheet metal retainer (46) received through a slot (52) disposed in the key (54).

Rotor assembly for a turbomachine

A rotor assembly 20 for a gas turbine engine 10 is disclosed. The rotor assembly includes a pair of axially spaced apart rotor disks such as the rotor disks 32 and 34. An inner air seal 50 extends axially between the adjacent rotor disks. A member 56 extends axially between the disks to join the disks together and is attached to the inner air seal at a mid span location to restrain the seal against outward movement.

Rotor assembly for a gas turbine engine

A turbine rotor assembly 10 for providing cooling air to a turbine blade 28 is disclosed. An annulus 24 is formed between the rotor disk 12 and a segmented sideplate 20 in which the segments have overlapping ends 22. A thin flexible metal strip 36 having overlapping ends 38 is disposed about the radially inward edge of the sideplate segments to seal the leakage flowpath between the overlapping ends 22 of the sideplate segments 20 as the sideplate segments expand and contract with the supporting disk 12.

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Woodbury, CT, United States of America

Stephen M Antonellis