公开(公告)号：US20170045227A1

公开(公告)日：2017-02-16

申请号：US15217142

申请日：2016-07-22

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING ,  Paul A. HUCKER ,  Giuseppe RALLO

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A combustion chamber includes at least one annular wall which includes at least one box like structure and each box like structure includes an inner wall, outer wall, upstream end wall and downstream end wall. The inner wall is spaced radially from the outer wall and the outer wall has a plurality of apertures for the supply of coolant into the box like structure. The inner wall, the outer wall, the upstream end wall and the downstream end wall are integral. The upstream end of the annular wall has features to secure the annular wall to an upstream ring structure and a downstream end of the annular wall has features to mount the annular wall on a downstream ring structure. The inner wall has at least one slot extending through the full thickness of the inner wall to accommodate differential thermal expansion between the inner wall and the outer wall.

Abstract translation: 燃烧室包括至少一个包括至少一个盒状结构的环形壁，并且每个盒状结构包括内壁，外壁，上游端壁和下游端壁。 内壁与外壁径向间隔开，并且外壁具有多个用于将冷却剂供应到盒状结构中的孔。 内壁，外壁，上游端壁和下游端壁是一体的。 环形壁的上游端具有将环形壁固定到上游环结构的特征，并且环形壁的下游端具有将环形壁安装在下游环结构上的特征。 内壁具有延伸穿过内壁的整个厚度的至少一个槽，以适应内壁和外壁之间的不同的热膨胀。

公开(公告)号：US20250052425A1

公开(公告)日：2025-02-13

申请号：US18772375

申请日：2024-07-15

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING ,  Paul A. HUCKER ,  Iain MORGAN

IPC: F23R3/00

Abstract: The present disclosure relates to a combustor assembly for a gas turbine engine. The combustor assembly comprises a combustor liner, a combustor head, a cowl and a fastener. The combustor liner and the cowl define a cavity. The combustor liner has an integral lug that extends into the cavity from a wall of the combustor liner. The fastener extends into the combustor liner lug to fasten the combustor head to the combustor liner.

公开(公告)号：US20180036843A1

公开(公告)日：2018-02-08

申请号：US15642973

申请日：2017-07-06

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Eliot BURROWS

IPC: B23P15/00

CPC classification number: B23P15/008 ,  F23R3/002 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00017

Abstract: A method of assembling an annular combustion chamber assembly comprises positioning a plurality of first combustion chamber segments circumferentially side by side to form an annulus and removably securing the downstream end of each first combustion chamber segment to a first ring to form a first assembly. The method comprises positioning a plurality of second combustion chamber segments circumferentially side by side to form an annulus, removably securing the downstream end of each second combustion chamber segment to a second ring to form a second assembly. The method comprises removably securing the upstream end of each second combustion chamber segment of the second assembly to an annular upstream end wall. The method comprises inserting the second assembly into the first assembly and then removably securing the upstream end of each first combustion chamber segment of the first assembly to the annular upstream end wall to form the annular combustion chamber assembly.

公开(公告)号：US20170307221A1

公开(公告)日：2017-10-26

申请号：US15467603

申请日：2017-03-23

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Steven BALLANTYNE ,  Stephen C. HARDING

IPC: F23R3/46 ,  F23R3/60

Abstract: A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. A frame structure at the downstream end of each segment has multiple spaced radially extending holes. The downstream end of each segment has an axially upstream extending groove and the downstream ring structure has an annular axially upstream extending hook which locates in the groove of each segment. A portion of the downstream ring structure abuts the frame structure of each segment. The downstream ring structure has multiple holes through the portion abutting the frame structure and segment is removably secured to the downstream ring structure by multiple fasteners locating in the holes in the segments and the downstream ring structure.

公开(公告)号：US20220082055A1

公开(公告)日：2022-03-17

申请号：US17403081

申请日：2021-08-16

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Giuseppe RALLO ,  Iain MORGAN

IPC: F02C7/36 ,  F23R3/00

Abstract: A combustion chamber comprising a plurality of circumferentially arranged cassette segments coupled to a combustor head at one end and a wall section at the other end, each cassette segment extending the full length of the combustion chamber, and wherein the combustor head has an annular tongue structure on a mating surface, the tongue structure engages with a groove portion present in each of the cassettes so that when assembled the groove portions in the each of the plurality of cassette segments forms a substantially continuous groove.

公开(公告)号：US20180031242A1

公开(公告)日：2018-02-01

申请号：US15637209

申请日：2017-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING ,  Paul A. HUCKER

IPC: F23R3/20 ,  F23R3/60 ,  F23R3/44 ,  F23R3/46 ,  F23R3/08 ,  F23R3/00

CPC classification number: F23R3/20 ,  F23R3/002 ,  F23R3/08 ,  F23R3/44 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00005

Abstract: A gas turbine engine combustion chamber comprises upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. The upstream end of each combustion chamber segment comprises a surface having a plurality of circumferentially spaced radially extending holes and the upstream ring structure having a plurality of circumferentially spaced holes extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment. Each combustion chamber segment being removably secured to the upstream ring structure by a plurality of fasteners locatable in the holes in the combustion chamber segment and corresponding holes in the upstream ring structure.

公开(公告)号：US20160097285A1

公开(公告)日：2016-04-07

申请号：US14858490

申请日：2015-09-18

Applicant: ROLLS-ROYCE PLC

Inventor： Stephen C. HARDING ,  Paul A. HUCKER ,  Nicholas WORTH

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture has a metering portion and a diffusing portion arranged in flow series and each metering portion is elongate and the width is greater than the length of the metering portion. The metering portion of each aperture has a U-shaped bend. The diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a rectangular shape in the second surface of the wall. Each inlet has an elongate shape in the first surface of the wall and the inlet in the wall is arranged substantially diagonally with respect to the outlet in the wall.

Abstract translation: 冷却的燃气涡轮发动机部件包括壁，该壁具有从第一表面延伸到第二表面的多个喷射冷却孔。 每个孔具有在第一表面中的入口和在第二表面中的出口。 每个孔具有流量系列布置的计量部分和扩散部分，每个计量部分是细长的，并且该宽度大于计量部分的长度。 每个孔的计量部分具有U形弯曲部。 每个孔的扩散部分以与第二表面成一定角度布置。 每个出口在壁的第二表面中具有矩形形状。 每个入口在壁的第一表面中具有细长形状，并且壁中的入口相对于壁中的出口基本上对角地布置。

公开(公告)号：US20200277868A1

公开(公告)日：2020-09-03

申请号：US16786037

申请日：2020-02-10

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Quentin BORLON

IPC: F01D9/02 ,  F01D15/02 ,  F23R3/42

Abstract: A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.

公开(公告)号：US20190293294A1

公开(公告)日：2019-09-26

申请号：US16355111

申请日：2019-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Iain MORGAN

IPC: F23R3/60 ,  F02C7/266 ,  F23R3/00 ,  F23R3/08

Abstract: An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.

公开(公告)号：US20160123156A1

公开(公告)日：2016-05-05

申请号：US14872511

申请日：2015-10-01

Applicant: ROLLS-ROYCE PLC

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Alan P. GEARY

IPC: F01D5/18 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D5/188 ,  F01D9/065 ,  F05B2260/202 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043

Abstract: A cooled gas turbine engine component comprises a wall having first and second surfaces. The second surface has a plurality of recesses and each recess has a planar upstream end surface arranged so that it hangs over the upstream end of the recess. Each recess has a depth equal to the required depth plus the thickness of the thermal barrier coating to be deposited. The wall has a plurality of angled effusion cooling apertures extending from the first surface towards the second surface. Each effusion cooling aperture has an inlet in the first surface and an outlet in the end surface of a corresponding one of the recesses in the second surface. Each recess has smoothly curved transitions from the end surface and side surfaces to the second surface. Blocking of the effusion cooling apertures by thermal barrier coating is reduced.

Abstract translation: 冷却的燃气涡轮发动机部件包括具有第一和第二表面的壁。 第二表面具有多个凹部，并且每个凹部具有布置成使其悬挂在凹部的上游端上的平坦的上游端面。 每个凹槽的深度等于所要求的深度加上待沉积的热障涂层的厚度。 壁具有从第一表面朝向第二表面延伸的多个倾斜的积水冷却孔。 每个排出冷却孔在第一表面中具有入口，在第二表面中的相应的一个凹部的端面中具有出口。 每个凹部具有从端表面和侧表面到第二表面的平滑弯曲过渡。 通过热障涂层阻挡积液冷却孔。