公开(公告)号：US20190218939A1

公开(公告)日：2019-07-18

申请号：US16233683

申请日：2018-12-27

Applicant: ROLLS-ROYCE plc

Inventor： Simon M. RUSTON ,  Rong YANG

IPC: F01D25/28 ,  F01D25/12

CPC classification number: F01D25/28 ,  B33Y10/00 ,  B33Y80/00 ,  F01D25/12 ,  F02C7/32 ,  F05D2230/31 ,  F05D2240/90 ,  F05D2260/201 ,  G06F1/20

Abstract: A mount for a gas turbine engine unit. The mount comprises a unit interface for securing a unit to the mount. The unit interface comprises an internal cavity in communication with a cooling aperture to be overlaid by unit secured to the unit interface. The mount further comprises a structural framework for securing the mount to a gas turbine engine. The structural framework comprises an internal cooling conduit for delivering cooling airflow from an air source to the internal cavity of the unit interface.

公开(公告)号：US20180171876A1

公开(公告)日：2018-06-21

申请号：US15834868

申请日：2017-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Rong YANG ,  David Isles

IPC: F02C7/32 ,  F16M13/02 ,  B33Y80/00

Abstract: A mount structure for mounting an ancillary engine unit to a gas turbine engine is provided. The mount structure has plural elongate struts which each extend from a connector portion at one end of the strut to a fastening portion at the other end of the strut. The housing of the ancillary engine unit is formed of a first material having a first coefficient of thermal expansion, and the elongate struts are formed of a second material having a second coefficient of thermal expansion. Each elongate strut extends away from its connector portion in a direction which is crosswise to the direction of the hypothetical differential thermal strain at that connector portion. The mount structure further has a containment bracket which is configured to contain each connector portion.

公开(公告)号：US20190112986A1

公开(公告)日：2019-04-18

申请号：US16124559

申请日：2018-09-07

Applicant: ROLLS-ROYCE plc

Inventor： Simon M. RUSTON ,  Rong YANG ,  Matthew FOX ,  Aniket Anand KULARNI

IPC: F02C9/18 ,  F02C3/04

Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.

公开(公告)号：US20180010524A1

公开(公告)日：2018-01-11

申请号：US15622419

申请日：2017-06-14

Applicant: ROLLS-ROYCE PLC

Inventor： Richard PEACE ,  Rong YANG ,  Joshua LEE ,  Liam KELLY

IPC: F02C7/32 ,  F01D25/24

CPC classification number: F02C7/32 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2250/75 ,  Y02T50/671

Abstract: A mounting bracket for mounting an accessory to a gas turbine engine comprises a space frame structure. The space frame structure comprises a plurality of struts joined to one another at nodes.