公开(公告)号：US20250012198A1

公开(公告)日：2025-01-09

申请号：US18742421

申请日：2024-06-13

Applicant: Rolls-Royce plc

Inventor： Anastasios KOVANIS ,  Andrew MEKERESZ

IPC: F01D11/00

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid. The outer lid includes a leading edge, a trailing edge, a pair of longitudinal edges, and an outer radial surface. Each longitudinal edge includes a first edge portion and a second edge portion. At least one longitudinal edge includes a recessed portion that extends at least axially between the first edge portion and the second edge portion, such that the recessed portion connects the first edge portion to the second edge portion. The recessed portion further extends circumferentially inwards from each of the first edge portion and the second edge portion towards the other longitudinal edge.

公开(公告)号：US20250084768A1

公开(公告)日：2025-03-13

申请号：US18808248

申请日：2024-08-19

Applicant: ROLLS-ROYCE plc

Inventor： Andrew MEKERESZ ,  Anastasios KOVANIS ,  John J. BOLGER ,  Benedict R PHELPS

IPC: F01D11/00

Abstract: An annulus filler of a gas turbine engine includes an outer lid including a leading edge, a trailing edge, a first longitudinal edge, a second longitudinal edge, and an outer radial surface. The outer radial surface includes a first nominal surface portion and a second nominal surface portion. The outer radial surface further includes a protruding surface portion extending radially outwardly from each of the first nominal surface portion and the second nominal surface portion and a recessed surface portion extending radially inwardly from each of the first nominal surface portion and the second nominal surface portion. Each of the protruding surface portion and the recessed surface portion is configured to redirect an air drawn through the gas turbine engine.

公开(公告)号：US20200011188A1

公开(公告)日：2020-01-09

申请号：US16437343

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Andrew MEKERESZ

IPC: F01D5/30

Abstract: A blade for a gas turbine engine that includes a blade root having an asymmetric lobe.