公开(公告)号：US10006372B2

公开(公告)日：2018-06-26

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 ,  F01D17/10 ,  F02K3/075 ,  F02C7/042 ,  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.

公开(公告)号：US12188433B2

公开(公告)日：2025-01-07

申请号：US18539813

申请日：2023-12-14

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M Hussain ,  Vasileios Kyritsis

IPC: F02C7/18 ,  F02K3/115

Abstract: A thermal management system for a gas turbine engine includes a plurality of inlet and outlet vanes extending from a bypass inner wall towards an outer cowl, a plurality of first removable shims, a plurality of second removable shims, and a third removable shim. Each first removable shim extends between and engages the outer cowl and a corresponding inlet vane. Each second removable shim extends between and engages the outer cowl and a corresponding outlet vane. The third removable shim extends between and engages a heat exchanger and the outer cowl. Each of the plurality of first removable shims, each of the plurality of second removable shims, and the third removable shim is removable for positionally adjusting the outer cowl relative to the bypass inner wall.

公开(公告)号：US11466587B2

公开(公告)日：2022-10-11

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：US11073108B2

公开(公告)日：2021-07-27

申请号：US16374816

申请日：2019-04-04

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M Hussain

IPC: F02K3/075 ,  F02K1/12

Abstract: A louvre offtake arrangement for a gas turbine engine includes a first duct, where a primary flow flows; a second duct, defining an offtake, connected to the first duct at an inlet; and a plurality of louvres arranged at the inlet. At least one louvre protrudes from the second duct into the first duct to divert part of the primary flow towards the second duct.

公开(公告)号：US10436148B2

公开(公告)日：2019-10-08

申请号：US15079797

申请日：2016-03-24

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M Hussain

IPC: F02K1/18 ,  F02K1/06 ,  F02K1/08

Abstract: A convergent-divergent nozzle arranged to convey fluid from an upstream zone to a downstream zone via a throat aperture, wherein the nozzle includes an assembly movable to vary the size of the throat aperture of the nozzle, thereby regulating the flow of fluid to the downstream zone.