公开(公告)号：US20180274386A1

公开(公告)日：2018-09-27

申请号：US15935795

申请日：2018-03-26

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN ,  Oliver TAYLOR-TIBBOTT

IPC: F01D21/14

CPC classification number: F01D21/14 ,  F01D17/105 ,  F02C3/04 ,  F02C7/00 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2260/30 ,  F05D2260/606 ,  Y02T50/672

Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount spaced from the door. An expandable structure is connected to the door and to the mount such that when the door hinges open the expandable structure expands.

公开(公告)号：US20250003825A1

公开(公告)日：2025-01-02

申请号：US18741159

申请日：2024-06-12

Applicant: ROLLS-ROYCE PLC

Inventor： Zahid M. HUSSAIN ,  Peter T. Ireland ,  David Bacci

IPC: G01M3/24 ,  G01M15/14 ,  G01S5/22

Abstract: A pressurised fluid duct failure event characterising method including: monitoring acoustic signals; detecting a failure event occurrence based on an acoustic signal exceeding a first failure threshold, and identifying a failure marker; estimating, for each acoustic signal, a failure detection time, based on the failure marker and a rate of change in sound pressure level for each acoustic signal; determining an acoustic weighted position for acoustic sensors; determining an estimate of a region containing the failure event as a first sub-volume of the duct based on the acoustic weighted position and a predetermined relationship between sound pressure level and regions of the duct; calculating, for each acoustic signal, one or more spectral characteristics; and determining at least one failure characteristic based on a comparison between the one or more spectral characteristics, the estimate of the region containing the failure event, and one or more predefined failure event parameters.

公开(公告)号：US20190178161A1

公开(公告)日：2019-06-13

申请号：US16202631

申请日：2018-11-28

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN

IPC: F02C3/32 ,  F02C6/08 ,  F01D25/32

Abstract: A bleed valve system comprises a duct, featuring a central longitudinal axis and allowing a main flow of fluid to pass from a first environment at a first static pressure to a second environment at a second static pressure along a bleed direction, a valve comprising a valve member arranged within the duct between the first and second environments and movable to partially obstruct the duct and deviate the main flow of fluid to direct at least a part of it towards a portion of an internal wall of the duct; and an ejector, arranged within the duct, downstream of the valve member and offset from the central longitudinal axis in correspondence of said portion of the internal wall, adapted to supply an additional flow of fluid within the duct to accelerate the main flow of fluid and reduce the second static pressure.

公开(公告)号：US20190170008A1

公开(公告)日：2019-06-06

申请号：US16180652

申请日：2018-11-05

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN

IPC: F01D11/02 ,  F02C3/04 ,  F02C9/18

Abstract: A tip clearance control (TCC) system 100 is provided to control the gap 176 between the tips of turbine blades 172 of a gas turbine engine 10 and the casing 174 within which they rotate. The inlet 120 to the TCC system is provided in a bifurcation panel 110 that extends across a bypass duct 22 of the gas turbine engine 10. The inlet is provided on a first major surface 112 of the bifurcation panel 110 that is defined such that the direction (R) that points through the bifurcation panel from the first major surface 112 to a second major surface 114 corresponds to the fan rotation direction. This provides a particularly effective and/or efficient TCC system 100.

公开(公告)号：US20200300111A1

公开(公告)日：2020-09-24

申请号：US16807532

申请日：2020-03-03

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN ,  Hugh D. THOMAS

IPC: F01D21/00

Abstract: Disclosed herein is a method of automatically determining an operating condition of at least part of a gas turbine engine 10 for an aircraft, the method comprising: measuring one or more gas pressure waves by a gas pressure detector 401, wherein the gas pressure detector 401 is located in the gas turbine engine 10; and automatically determining, by a computing system, an operating condition of at least part of a gas turbine engine 10 in dependence on an output signal of the gas pressure detector 401.

公开(公告)号：US20190323433A1

公开(公告)日：2019-10-24

申请号：US16379915

申请日：2019-04-10

Applicant: ROLLS-ROYCE plc

Inventor： Clare L. BEWICK ,  Zahid M. HUSSAIN ,  David P. SCOTHERN ,  John R. MASON

IPC: F02C7/18 ,  F02C3/06

Abstract: A gas turbine engine (10) comprising: an engine core (11), comprising a compressor (14, 15); an outer casing (25A) separating the engine core (11) from a bypass airflow; a compressor bleed valve (50) in communication with the compressor (14, 15) and configured to release bleed air from the compressor (14, 15); a bleed air duct (51) connected to the compressor bleed valve (50) and configured to eject the bleed air released by the compressor bleed valve (50) into an airflow at a location radially inward of the outer casing (25A).

公开(公告)号：US20180111183A1

公开(公告)日：2018-04-26

申请号：US15789173

申请日：2017-10-20

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN ,  Oliver C. TAYLOR-TIBBOTT

IPC: B21D53/84 ,  F04D27/00 ,  B23K9/00

CPC classification number: B21D53/84 ,  B21D13/10 ,  B21D31/04 ,  B21D47/00 ,  B21D51/10 ,  B23K9/0026 ,  B23P15/00 ,  F02C6/08 ,  F04D27/009 ,  F23R2900/00018

Abstract: A method of manufacturing an annular component comprises providing an annular shell to form the outer wall of the component and a plurality of flat annular rings wherein a radially inner edge of each ring is shaped to correspond to a cross-section of the shell at a different position along its length. The method comprises attaching each ring to the ring(s) adjacent to it at a plurality of circumferentially spaced discrete positions. The method comprises deforming each flat annular ring into a corrugated three-dimensional shape, wherein the corrugations extend out of the flat plane and comprise radially defined peaks and troughs. The method comprises locating the shell within the plurality of attached, deformed annular rings. The method comprises attaching the plurality of attached, deformed annular rings to the shell to form the component, so that the plurality of attached, deformed annular rings provide structural reinforcement to the shell.

公开(公告)号：US20250003826A1

公开(公告)日：2025-01-02

申请号：US18741216

申请日：2024-06-12

Applicant: ROLLS-ROYCE PLC

Inventor： Zahid M. HUSSAIN ,  Peter T. Ireland ,  David Bacci

IPC: G01M3/24 ,  G01M15/14 ,  G01S5/22

Abstract: A pressurised fluid duct failure event location determination method including: monitoring acoustic signals; detecting a failure event occurrence based on an acoustic signal of those exceeding a first failure threshold, and identifying a failure marker; estimating, for each acoustic signal, a failure detection time; determining an acoustic weighted position for acoustic sensors based on the respective failure detection time for each acoustic signal and the position of each microphone; determining an estimate of a region containing the failure event as a first sub-volume of the duct based on the acoustic weighted position and a predetermined relationship between sound pressure level and regions of the duct; discretising the first sub-volume of the duct into a first three-dimensional grid having voxels according to a first grid mesh size; and determining a first estimate of the failure event location using a time-domain beamforming algorithm applied to the acoustic signals and the first sub-volume.

公开(公告)号：US20240059420A1

公开(公告)日：2024-02-22

申请号：US18359361

申请日：2023-07-26

Applicant: ROLLS-ROYCE plc

Inventor： Oliver C. TAYLOR-TIBBOTT ,  Zahid M. HUSSAIN ,  Ainhoa AGUADO SAN MILLAN

IPC: B64D33/02 ,  F02C7/04 ,  F02C7/18

CPC classification number: B64D33/02 ,  F02C7/04 ,  F02C7/18

Abstract: An inlet assembly includes a web extending between a first end and a second end along a first axis. The web includes first and second major surfaces. The inlet assembly includes a load transfer flange at least partially disposed around the web and configured to be fixedly coupled to a gas turbine engine. The inlet assembly includes first vanes spaced apart from each other at least along the first axis. Each first vane extends between the first major surface of the web and the load transfer flange. The inlet assembly includes second vanes spaced apart from each other at least along the first axis. Each second vane extends between the second major surface of the web and the load transfer flange.

公开(公告)号：US20160010558A1

公开(公告)日：2016-01-14

申请号：US14748787

申请日：2015-06-24

Applicant: ROLLS-ROYCE PLC

Inventor： Zahid M. HUSSAIN ,  Nityabh MISHRA ,  Peter T. IRELAND

IPC: F02C7/25 ,  F02K3/075 ,  F02C9/18

CPC classification number: F02C7/25 ,  F01D17/105 ,  F02C7/042 ,  F02C9/18 ,  F02K3/075

Abstract: A ventilation inlet including a conduit (104) arranged to convey flow from a first flow zone to a second flow zone. The conduit has a mouth region (106) presenting to the first flow zone an entrance aperture to receive the flow therefrom. The conduit has a baffle (114) spanning a portion of the conduit to define a throat region (116), the throat region being narrower than the entrance aperture. The throat region (116) is movable along the conduit (104) to control the flow through the ventilation inlet.

Abstract translation: 通风入口，其包括布置成将流从第一流动区域输送到第二流动区域的导管（104）。 导管具有向第一流动区域呈现入口孔口的口部区域（106），用于接收来自其的流体。 导管具有跨过管道的一部分以限定喉部区域（116）的挡板（114），所述喉部区域比入口孔窄。 喉部区域116可沿导管104移动以控制通过通气入口的流动。