公开(公告)号：US10968749B2

公开(公告)日：2021-04-06

申请号：US16393137

申请日：2019-04-24

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh Shahpar ,  John Coull ,  Matthew Symes

IPC: F01D5/00 ,  F01D5/14 ,  F01D9/04

Abstract: A combustion chamber arrangement includes an annular combustion chamber, a plurality of lean burn fuel injectors and a stage of turbine nozzle guide vanes. The stage of turbine nozzle guide vanes is arranged at the downstream end of the annular combustion chamber and includes a plurality of circumferentially spaced vanes extending between and being secured to an annular inner wall and an annular outer wall. The annular inner wall has an outer surface which has a plurality of outer surface portions and each portion is positioned between a pair of circumferentially adjacent vanes and the annular outer wall has an inner surface which has a plurality of inner surface portions and each portion is positioned between a pair of circumferentially adjacent vanes.

公开(公告)号：US10297080B2

公开(公告)日：2019-05-21

申请号：US15787199

申请日：2017-10-18

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh Shahpar

IPC: G06F17/11 ,  G06T17/30 ,  G06F17/50 ,  G06T17/20

Abstract: A computer-implemented method of optimizing an automatically meshable shape is provided. The method includes the steps of: providing a continuous boundary of the automatically meshable shape, the continuous boundary being defined by a spline formed by two or more spline segments, wherein each segment has a terminal point at each end of the segment; parameterizing shape properties of the segments such that selected ones of the shape properties can be varied under operation of an optimization algorithm; linking each segment to its immediately adjacent segments such that the terminal points of the segment remain coincident with the terminal points of its immediately adjacent segments under operation of the optimization algorithm; and using the optimization algorithm to vary selected ones of the shape properties of the segments, whereby the spline defines an adjusted boundary that remains continuous so that the shape remains automatically meshable.

公开(公告)号：US11175042B2

公开(公告)日：2021-11-16

申请号：US16229093

申请日：2018-12-21

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Armit ,  Emmanuel Aurifeille ,  Shahrokh Shahpar ,  Paul Denman ,  Christopher Ford

IPC: F23R3/10 ,  F23R3/26 ,  F23R3/00

Abstract: Combustion equipment includes annular combustion chamber having an annular upstream wall structure. Annular outer casing surrounds and is spaced from annular combustion chamber and annular inner casing is within and spaced from annular combustion chamber. Ogee shaped annular cowl is positioned upstream of annular upstream wall structure and a stage of compressor outlet guide vanes is positioned upstream of annular cowl. Pre-diffuser extends in downstream direction from stage of compressor outlet guide vanes, pre-diffuser is positioned upstream of cowl. Stage of compressor outlet guide vanes is connected to outer and inner casing. Outer fairing extends radially inwardly from outer casing such that annular outer casing, outer fairing and pre-diffuser define annular outer cavity and outer fairing is spaced from cowl or inner fairing extends radially outwardly from inner casing such that annular inner casing, inner fairing and pre-diffuser define an annular inner cavity and inner fairing is spaced from cowl.

公开(公告)号：US12098651B2

公开(公告)日：2024-09-24

申请号：US17847699

申请日：2022-06-23

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh Shahpar

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F05D2230/10 ,  F05D2240/305 ,  F05D2240/306

Abstract: A method for shaping an aerofoil by: (a) defining an aerofoil having a nominal shape, the nominal shape defined by; a leading edge, a trailing edge, a root and a tip, a span extending from the root to the tip, a pressure surface and a suction surface extending from the leading edge to the trailing edge; a nominal camber line extending from the leading edge to the trailing edge; (b) defining an edge region on one of the pressure and/or suction surface which extends distance of at least 0.1% but no more than 10% of the camber line length from one of the leading edge or the trailing edge of the aerofoil; and (c) adapting the shape of the pressure and/or suction surface within the edge region such that the edge region of the aerofoil achieves an asymmetric profile with respect to the nominal camber line.

公开(公告)号：US10208664B2

公开(公告)日：2019-02-19

申请号：US15061150

申请日：2016-03-04

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Armit ,  Emmanuel Aurifeille ,  Shahrokh Shahpar ,  Paul Denman ,  Christopher Ford

IPC: F23R3/10 ,  F23R3/04 ,  F02C3/04 ,  F23R3/26 ,  F23R3/00

Abstract: Combustion equipment includes annular combustion chamber having an annular upstream wall structure. Annular outer casing surrounds and is spaced from annular combustion chamber and annular inner casing is within and spaced from annular combustion chamber. Ogee shaped annular cowl is positioned upstream of annular upstream wall structure and a stage of compressor outlet guide vanes is positioned upstream of annular cowl. Pre-diffuser extends in downstream direction from stage of compressor outlet guide vanes, pre-diffuser is positioned upstream of cowl. Stage of compressor outlet guide vanes is connected to outer and inner casing. Outer fairing extends radially inwardly from outer casing such that annular outer casing, outer fairing and pre-diffuser define annular outer cavity and outer fairing is spaced from cowl or inner fairing extends radially outwardly from inner casing such that annular inner casing, inner fairing and pre-diffuser define an annular inner cavity and inner fairing is spaced from cowl.