公开(公告)号：US20200018168A1

公开(公告)日：2020-01-16

申请号：US16460020

申请日：2019-07-02

Applicant: ROLLS-ROYCE plc

Inventor： Anastasios KOVANIS

IPC: F01D5/14 ,  F02C3/04

Abstract: A fan unit for a turbofan engine includes a plurality of fan blades mounted to a fan disc unit and a plurality of vortex-generating elements each of which is arranged to generate a respective vortex extending axially between a respective pair of adjacent fan blades during rotation of the fan unit about its rotation axis. During operation of a turbofan engine comprising the fan unit, fan-wake-induced mechanical degradation of compressor blades in a compressor downstream of the fan unit is eliminated, or the rate at which such degradation occurs is reduced.

公开(公告)号：US20240360770A1

公开(公告)日：2024-10-31

申请号：US18636837

申请日：2024-04-16

Applicant: ROLLS-ROYCE plc

Inventor： Anastasios KOVANIS ,  Andrew Mekeresz

IPC: F01D11/00 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D11/008 ,  F01D5/14 ,  F01D5/30 ,  F05D2220/36

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid coupled to the coupling portion. The outer lid includes a leading edge, a trailing edge, and a main portion including an outer radial surface. The outer lid further includes a protruding portion connected to the main portion and extending radially outwardly from the main portion. The protruding portion is axially disposed between and spaced apart from the leading edge and the trailing edge. The protruding portion includes a protruding surface contiguous with and extending radially outwardly from the outer radial surface, such that the protruding surface is configured to redirect air drawn through the gas turbine engine.

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：US20180298912A1

公开(公告)日：2018-10-18

申请号：US15634244

申请日：2017-06-27

Applicant: ROLLS-ROYCE plc

Inventor： Christopher R. HALL ,  Anastasios KOVANIS ,  Anthony M. DICKENS ,  James V. TAYLOR

IPC: F04D29/32 ,  F04D29/54 ,  F04D29/38

Abstract: This disclosure concerns aerofoils for an axial flow compressor. The compressor has an array of aerofoils angularly spaced about its axis of rotation. The aerofoils have leading and trailing edges extending in a direction spanning a flow region defined between a radially inner rotor component and a radially outer casing. Each aerofoil has opposing pressure and suction surfaces extending between the leading and trailing edges and terminating at a free end of the aerofoil. Each aerofoil leans towards the pressure surface by an angle of between 10° and 80° in the vicinity of the aerofoil tip. The aggressive negative lean towards the tip may help reduce over-tip leakage flow in use.