公开(公告)号：US20180298912A1

公开(公告)日：2018-10-18

申请号：US15634244

申请日：2017-06-27

申请人： ROLLS-ROYCE plc

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

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

摘要： 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.

公开(公告)号：US20200018168A1

公开(公告)日：2020-01-16

申请号：US16460020

申请日：2019-07-02

申请人： ROLLS-ROYCE plc

发明人： Anastasios KOVANIS

IPC分类号： F01D5/14 ,  F02C3/04

摘要： 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

申请人： ROLLS-ROYCE plc

发明人： Anastasios KOVANIS ,  Andrew Mekeresz

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

CPC分类号： F01D11/008 ,  F01D5/14 ,  F01D5/30 ,  F05D2220/36

摘要： 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.