公开(公告)号：US20240392967A1

公开(公告)日：2024-11-28

申请号：US18652159

申请日：2024-05-01

Applicant: ROLLS-ROYCE plc

Inventor： Karpaga Vipran KANNAN ,  Joseph R. HARDY ,  Ryan L. ROGERS ,  Andrés E. LEIVA GONZALEZ ,  Shahrokh SHAHPAR

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/34

Abstract: A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. An inlet to the fuel stem portion is fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion is fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion has a cross-sectional profile that is generally dolioform shaped along an axis parallel to the engine's longitudinal axis, and has a first end and a second end. The first end of the fuel/air swirler portion has an air inlet face, and the second end of the fuel/air swirler portion has a fuel/air mixture outlet face. The first end comprises a rim portion enclosing the air inlet face in which the rim portion has a rim portion radius (rrim) normal to an outer circumference of the inlet face.

公开(公告)号：US20190120139A1

公开(公告)日：2019-04-25

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: F02C3/04 ,  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：US20230024238A1

公开(公告)日：2023-01-26

申请号：US17847699

申请日：2022-06-23

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh SHAHPAR

IPC: F01D5/14

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：US20180108177A1

公开(公告)日：2018-04-19

申请号：US15787199

申请日：2017-10-18

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh SHAHPAR

IPC: G06T17/30

CPC classification number: G06T17/30 ,  G06F17/5018 ,  G06F17/5095 ,  G06T17/205

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; parameterising 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：US20160290225A1

公开(公告)日：2016-10-06

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: F02C3/04 ,  F23R3/00

CPC classification number: F02C3/04 ,  F23R3/002 ,  F23R3/10 ,  F23R3/26

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.

Abstract translation: 燃烧设备包括具有环形上游壁结构的环形燃烧室。 环形外壳环绕并与环形燃烧室隔开，环形内壳在环形燃烧室内并与其隔开。 O形环形罩被设置在环形上游壁结构的上游，压缩机出口导叶的一级位于环形罩的上游。 预扩散器从压缩机出口导叶的阶段沿下游方向延伸，预扩散器位于整流罩的上游。 压缩机出口导叶的阶段连接到外壳和内壳。 外整流罩从外壳径向向内延伸，使得环形外壳，外整流罩和预扩散器限定环形外腔，并且外整流罩与整流罩间隔开，或内整流罩从内壳径向向外延伸，使得环形内壳，内整流罩和预 -diffuser定义一个环形内腔，内部整流罩与整流罩隔开。

公开(公告)号：US20190323355A1

公开(公告)日：2019-10-24

申请号：US16393137

申请日：2019-04-24

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh SHAHPAR ,  John COULL ,  Matthew SYMES

IPC: 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：US20180073370A1

公开(公告)日：2018-03-15

申请号：US15683339

申请日：2017-08-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin MOTTRAM ,  David J. HUNT ,  Haidong LI ,  Shahrokh SHAHPAR ,  Stefano CALONI

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/20 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/314 ,  F05D2250/52 ,  F05D2260/202

Abstract: A blade includes a root and an elongate portion extending to a tip, the elongate portion having an aerofoil-shaped cross-section. The aerofoil has leading and trailing edges, and suction and pressure sides. The tip includes a squealer defining a gutter at the tip, the squealer extending from the trailing edge along the entirety of a first of the suction and pressure sides, around the leading edge and partly along a second of the suction and pressure sides leaving a gap between the trailing edge and an end of the wall. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exits into the gutter. The main trailing edge cooling channel includes a bend just downstream of the exit, the exit displaced from a camber line of the blade elongated portion towards the second side.

公开(公告)号：US20170017741A1

公开(公告)日：2017-01-19

申请号：US15202832

申请日：2016-07-06

Applicant: ROLLS-ROYCE plc

Inventor： Chi Wan LIM ,  Xiaofeng YIN ,  Tianyou ZHANG ,  Yi SU ,  Chi-Keong GOH ,  Shahrokh SHAHPAR ,  Alejandro MORENO

IPC: G06F17/50

CPC classification number: G06F17/5018 ,  G06T17/20

Abstract: A computational engineering modelling tool having a point generation module arranged to read geometry data representing a domain to be modelled. The point generation module also generates point data for the domain having multiple boundary points located on a boundary of the domain and multiple further points spaced from the boundary within the domain. A point mutation module processes the point generation module output and generates automatically a plurality of alternative point data definitions for the domain in which the location of at least one point differs between each of the alternative point definitions. A blocking module discretizes the domain by creating multiple geometric blocks over the domain using a computational geometric operator wherein each point represents a vertex of at least one block. The blocking module outputs a discretized computational model of the domain and the tool scores the model according to a geometric attribute of the blocks.

Abstract translation: 一种计算工程建模工具，其具有布置成读取表示要建模的域的几何数据的点生成模块。 点生成模块还生成具有位于域的边界上的多个边界点的域的点数据，以及与域内的边界间隔开的多个另外的点。 点突变模块处理点生成模块输出并自动生成针对至少一个点的位置在每个替代点定义之间不同的域的多个备选点数据定义。 阻塞模块通过使用计算几何算子在域上创建多个几何块来离散域，其中每个点表示至少一个块的顶点。 阻塞模块输出域的离散计算模型，并且工具根据块的几何属性对模型进行评分。