公开(公告)号：US11067276B2

公开(公告)日：2021-07-20

申请号：US16355111

申请日：2019-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Paul A Hucker ,  Stephen C Harding ,  Iain Morgan

IPC: F23R3/00 ,  H01T13/08 ,  F23R3/06 ,  F02C7/266 ,  F02C7/264

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：US09957811B2

公开(公告)日：2018-05-01

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: F01D5/00 ,  F01D5/18 ,  F01D9/06 ,  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.

公开(公告)号：US11293640B2

公开(公告)日：2022-04-05

申请号：US16819354

申请日：2020-03-16

Applicant: ROLLS-ROYCE plc

Inventor： Paul A Hucker ,  Iain Morgan ,  Alan P Geary

IPC: F23R3/28 ,  F23R3/00 ,  B33Y80/00

Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

公开(公告)号：US10816212B2

公开(公告)日：2020-10-27

申请号：US15467603

申请日：2017-03-23

Applicant: ROLLS-ROYCE plc

Inventor： Paul A Hucker ,  Steven Ballantyne ,  Stephen C Harding

IPC: F23R3/60 ,  F23R3/46 ,  F23R3/50 ,  F23R3/00

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：US10655857B2

公开(公告)日：2020-05-19

申请号：US15637209

申请日：2017-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C Harding ,  Paul A Hucker

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

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. The upstream end of each combustion chamber segment includes 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.