公开(公告)号：US20170009995A1

公开(公告)日：2017-01-12

申请号：US15185596

申请日：2016-06-17

Applicant: ROLLS-ROYCE plc

Inventor： Frederic WITHAM ,  Steven P JONES ,  Jonathan M GREGORY ,  Timothy MINCHIN ,  David CLARKE ,  David STEELE

IPC: F23R3/28 ,  F23R3/14 ,  F02C3/00

CPC classification number: F23R3/286 ,  F02C3/00 ,  F23D11/24 ,  F23D11/383 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/30 ,  F23R2900/00012

Abstract: A fuel spray nozzle comprises a fuel passage (1) having at least one inlet and at least one outlet. The outlet is configured for accelerating fuel exiting the fuel passage into a jet. An air swirler (3) is arranged outboard of the fuel passage and converges to a single outlet chamber (5) adjacent the fuel passage outlet(s). The air swirler (3) can be nominally concentrically arranged but have some freedom to move axially or radially or change its angular position. The fuel passage outlets may be arranged symmetrically in an annular configuration. An air passage may be arranged axially within the annular array of fuel passage outlets.

Abstract translation: 燃料喷嘴包括具有至少一个入口和至少一个出口的燃料通道（1）。 出口构造成将从燃料通道排出的燃料加速成射流。 空气旋流器（3）布置在燃料通道的外侧并且会聚到与燃料通道出口相邻的单个出口室（5）。 空气旋流器（3）可以名义上同心地布置，但是具有沿轴向或径向移动或改变其角位置的一些自由度。 燃料通道出口可以对称地布置在环形构造中。 空气通道可以轴向布置在燃料通道出口的环形阵列内。

公开(公告)号：US20240085020A1

公开(公告)日：2024-03-14

申请号：US18226975

申请日：2023-07-27

Applicant: ROLLS-ROYCE plc

Inventor： Frederic WITHAM

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R2900/00012 ,  F23R2900/03043

Abstract: A combustor assembly for a gas turbine engine, the combustor assembly including: combustor wall defining combustion chamber and including opening periphery, the opening periphery defining first opening; sealing element including annular body, annular body extending around sealing element axis and extending through first opening, sealing element further including flange extending radially outward from annular body, flange slidingly coupling sealing element and combustor wall and forming seal or first partial seal between sealing element and combustor wall, annular body including outer and inner surface, inner surface defining second opening configured to receive fuel nozzle, wherein first total clearance between outer surface and opening periphery in first direction is greater than second total clearance between outer surface and opening periphery in second direction perpendicular to first direction such that sealing element is able to slide relative to combustor wall by greater extent in first direction than in second direction.

公开(公告)号：US20240053010A1

公开(公告)日：2024-02-15

申请号：US18226978

申请日：2023-07-27

Applicant: ROLLS-ROYCE plc

Inventor： Frederic WITHAM

IPC: F23R3/00 ,  F02C7/06

CPC classification number: F23R3/002 ,  F02C7/06 ,  F23R2900/00005

Abstract: A combustor assembly for gas turbine engine, combustor assembly including: combustor wall including interior surface and combustor wall opening, wherein interior surface partially defines combustion chamber, wherein combustor wall opening extends between combustion chamber and its exterior; sealing element disposed partially within combustor wall opening and includes air inlet, air outlet and air passageway, wherein air outlet exits into combustion chamber and delivers flow of air received from exterior of combustion chamber via air inlet and air passageway to combustion chamber; and fuel nozzle coupled to sealing element and configured to deliver fuel into combustion chamber, wherein combustor wall further includes first bearing surface and sealing element further includes second bearing surface, wherein first bearing surface is concave and forms part of first spherical surface such that first and second bearing surfaces are configured to move relative to each other about central point of first spherical surface.

公开(公告)号：US20240392966A1

公开(公告)日：2024-11-28

申请号：US18652134

申请日：2024-05-01

Applicant: ROLLS-ROYCE PLC

Inventor： Frederic WITHAM

IPC: F23R3/14 ,  B33Y10/00

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. The fuel inlet portion is configured to receive a flow of a fuel, with an inlet to the fuel stem portion being fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion being fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion comprises an outer air swirler and an inner air swirler, with the inner air swirler being positioned concentrically within the outer air swirler. The outer air swirler comprises a plurality of first vanes that are arranged in an annular array within an outer air swirler body and is configured to impose a first rotational flow component on an air flow entering the outer air swirler. The inner air swirler has a plurality of second vanes that are arranged in an annular array within an inner air swirler body and are configured to impose a second rotational flow component on an air flow entering the inner air swirler. The fuel stem portion passes radially inwardly through the outer air swirler to a region radially between the outer air swirler and the inner air swirler. The inner air swirler also comprises an annular fuel gallery that is formed on a radially outwardly facing surface such that the flow of fuel enters the fuel gallery before being atomised into the air flow passing through the inner air swirler, and then further atomised into the air flow passing through the outer air swirler.

公开(公告)号：US20180195728A1

公开(公告)日：2018-07-12

申请号：US15862780

申请日：2018-01-05

Applicant: ROLLS-ROYCE plc

Inventor： Mike OJ CARUSO ,  Frederic WITHAM ,  Jonathan M. GREGORY ,  Steven BALLANTYNE ,  James W. MONTGOMERY

IPC: F23R3/28 ,  F23R3/38 ,  F23R3/34 ,  F23R3/20 ,  F02C7/22 ,  F23D11/38 ,  F23D11/10 ,  F02C9/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F02C7/222 ,  F02C9/28 ,  F23D11/107 ,  F23D11/383 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/20 ,  F23R3/283 ,  F23R3/30 ,  F23R3/343 ,  F23R3/38

Abstract: A fuel injector comprises one or more elongate fuel passages (802) having an elongate axis extending from an upstream inlet end to a downstream outlet end. One or more outlets (803) are provided at the outlet end and extend obliquely with respect to the elongate axis. The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defining a first annular cavity (804) between the inner skin and outer skin. The inner skin and the outer skin converge adjacent the one or more outlets (803) to form a nose (808). A bridge is arranged within the fuel passage (802) and upstream of the nose (808), the bridge comprising a plurality of arms (811) extending radially from a centre (812) to a wall of the fuel passage (802), the centre (812) arranged in axial alignment with a centre of the nose (808).

公开(公告)号：US20180283693A1

公开(公告)日：2018-10-04

申请号：US15923570

申请日：2018-03-16

Applicant: ROLLS-ROYCE PLC

Inventor： Ian M. GARRY ,  Mark GLOVER ,  Richard MELLOR ,  Frederic WITHAM

IPC: F23R3/28 ,  F23R3/34 ,  F02C7/228 ,  F02C7/22

Abstract: A fuel injector provided for gas turbine engine has a nozzle including pilot fuel and mains fuel discharge orifice's for respectively spraying pilot and mains fuel flows into a combustor of the engine. The injector further has a feed arm extending to the nozzle for feeding fuel to the pilot and mains discharge orifices from pilot and mains supplies respectively. The nozzle and the feed arm contain one or more pilot passages for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages for flow of the mains fuel flow from the mains supply to the mains discharge orifice. The nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages. The pilot and the mains passages intertwine repeatedly, and are both smoothly curved as they intertwine around each other.

公开(公告)号：US20180195726A1

公开(公告)日：2018-07-12

申请号：US15862724

申请日：2018-01-05

Applicant: ROLLS-ROYCE plc

Inventor： Frederic WITHAM ,  Steven BALLANTYNE ,  Jonathan M. GREGORY ,  Mike OJ CARUSO ,  Stephen C. HARDING

IPC: F23R3/28 ,  F23R3/38 ,  F23R3/34 ,  F23R3/20 ,  F23R3/14 ,  F02C7/22 ,  F23D11/38 ,  F23D11/10 ,  F02C9/28

Abstract: A fuel injector comprises an elongate fuel passage (31) having an elongate axis (31a) extending from an upstream inlet end to a downstream outlet end. A plurality of outlets (33) is arranged at the outlet end, each outlet extends obliquely with respect to the elongate axis (31a). The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defines a first annular cavity (34) between the inner skin and an outer skin. The inner skin and the outer skin meet adjacently upstream of the one or more outlets to close an end of the first annular cavity (34). The injector has a nose section (32) at a downstream end, the nose section (32) being convergent and fluted. The flutes (38) are arranged between the outlets (33) and extend towards the downstream end of the nose section (32) whereby to guide an air stream (A) passing over the injector (30) to form single jet at the downstream end of the nose section (32).

公开(公告)号：US20170067641A1

公开(公告)日：2017-03-09

申请号：US15245035

申请日：2016-08-23

Applicant: ROLLS-ROYCE plc

Inventor： Frederic WITHAM ,  Pierre HILT ,  Steven P. JONES ,  Jonathan M. GREGORY ,  Timothy MINCHIN

IPC: F23R3/58 ,  F02C3/04

Abstract: An annular air swirler configured to receive a fuel injector in a central bore. The swirler has one or more annular channels, defined by radially facing channel walls and having an inlet for receiving compressed air and an axially distal outlet. The channel walls converge inwardly towards the outlet and swirl vanes extend between opposing faces of the walls. The swirler turns incoming air to create a vortex at the channel outlet. An annular cooling apparatus associated with the air swirler is arranged axially adjacently downstream of the channel outlet(s), and includes a skirt portion radially spaced from a converging portion of the outermost channel wall defining a converging portion of a bowed coolant channel. A radially outwardly extending wall connects with the outermost channel wall and, with a face of the skirt portion, defines a radially outwardly extending portion of the bowed coolant channel adapted for increased heat exchange.

Abstract translation: 环形空气旋流器，其构造成在中心孔中接收燃料喷射器。 旋流器具有由径向面对的通道壁限定的一个或多个环形通道，并且具有用于接收压缩空气和轴向远端出口的入口。 通道壁向内朝向出口汇合，并且涡流叶片在壁的相对面之间延伸。 旋流器使进入的空气在通道出口处产生涡流。 与空气旋流器相关联的环形冷却装置在通道出口的下游轴向相邻地布置，并且包括与限定弯曲冷却剂通道的会聚部分的最外通道壁的会聚部分径向间隔开的裙部。 径向向外延伸的壁与最外面的通道壁连接，并且裙部的一个表面限定了适合于增加热交换的弯曲冷却剂通道的径向向外延伸的部分。