公开(公告)号：US20250043869A1

公开(公告)日：2025-02-06

申请号：US18770742

申请日：2024-07-12

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN ,  Robert C. PEARCE

IPC: F16K1/22 ,  F04D27/02

Abstract: A butterfly valve for a conduit defining a passage for a flow of a fluid therethrough in a flow direction. The butterfly valve includes a shaft rotatably mounted to the conduit and defining a longitudinal axis along its length. The butterfly valve includes a valve body coupled to the shaft, such that the valve body is rotatable along with the shaft about the longitudinal axis between a closed position and a fully open position. The valve body includes a first major surface, a second major surface opposite to the first major surface, a perimeter surface, a central plane, a first lobe, a second lobe, and a third lobe.

公开(公告)号：US20240200495A1

公开(公告)日：2024-06-20

申请号：US18539813

申请日：2023-12-14

Applicant: Rolls-Royce plc

Inventor： Zahid M. HUSSAIN ,  Vasileios Kyritsis

IPC: F02C7/18 ,  F02C9/18

CPC classification number: F02C7/18 ,  F02C9/18 ,  F05D2240/14 ,  F05D2260/213 ,  F05D2260/31 ,  F05D2260/606

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：US20200141274A1

公开(公告)日：2020-05-07

申请号：US16598369

申请日：2019-10-10

Applicant: ROLLS-ROYCE plc

Inventor： Emile RAYA ,  Lucian INGLEY ,  Zahid M. HUSSAIN

IPC: F01D25/14 ,  F02C7/12 ,  F02C7/32 ,  F02K3/06

Abstract: A gas turbine engine for an aircraft is provided. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes an aerodynamic cowl which surrounds the core casings. The engine further includes a propulsive fan located upstream of the engine core, the fan generating a core airflow which enters the core engine and a bypass airflow which enters a bypass duct surrounding the aerodynamic cowl. The engine further includes one or more engine accessories mounted in a space between the core casings and the aerodynamic cowl.

公开(公告)号：US20190338728A1

公开(公告)日：2019-11-07

申请号：US16374816

申请日：2019-04-04

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. HUSSAIN

IPC: F02K3/075

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：US20180283207A1

公开(公告)日：2018-10-04

申请号：US15936773

申请日：2018-03-27

Applicant: ROLLS-ROYCE plc

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

IPC: F01D21/14 ,  F01D25/24 ,  F16K17/164 ,  F16K1/22

Abstract: A pressure relief arrangement for a gas turbine engine comprises a panel and a plurality of pressure relief mechanisms provided in the panel. The mechanisms have a first configuration and a second configuration. In the first configuration the panel is sealed to prevent fluid flow through the panel in a thickness direction and in the second configuration the mechanisms are arranged so that a plurality of holes are provided in the panel so fluid can flow through the panel in a thickness direction.