公开(公告)号：US11466856B2

公开(公告)日：2022-10-11

申请号：US17317073

申请日：2021-05-11

Applicant: ROLLS-ROYCE plc

Inventor： Michael Yeandel

IPC: F23R3/20 ,  F02K3/10 ,  F23R3/28 ,  F02K3/11

Abstract: An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

公开(公告)号：US10428986B2

公开(公告)日：2019-10-01

申请号：US15642669

申请日：2017-07-06

Applicant: ROLLS-ROYCE plc

Inventor： Michael Yeandel

IPC: F16L27/11 ,  F16L27/02 ,  F16L27/10 ,  F16L27/111 ,  F16L51/02

Abstract: A gimbal expansion joint includes a first clevis adapted to be secured to one end of a first piece of ducting, a second clevis adapted to be secured to an end of a second piece of ducting, and a gimbal arrangement to which the first and second clevises are pivotably connected to form a universal joint between the ends of the pieces of ducting. A flexible duct extends between the first and second clevises to form a passage for fluid communication between the ends of the first and second pieces of ducting. The flexible duct has a respective flange at each end, each flange providing an axially-directed face across which a clamping load is applied to affix the flange to a corresponding axially-directed face of the respective clevis.

公开(公告)号：US12012900B2

公开(公告)日：2024-06-18

申请号：US18302096

申请日：2023-04-18

Applicant: ROLLS-ROYCE plc

Inventor： Matthew S. Cartwright ,  Michael Yeandel

IPC: F02C7/32 ,  F02C7/36

CPC classification number: F02C7/32 ,  F02C7/36

Abstract: Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

公开(公告)号：US11719112B2

公开(公告)日：2023-08-08

申请号：US17814021

申请日：2022-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Michael Yeandel

IPC: F02C7/32 ,  F01D9/06

CPC classification number: F01D9/06 ,  F02C7/32 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2260/60

Abstract: A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.