公开(公告)号：US10801363B2

公开(公告)日：2020-10-13

申请号：US15935795

申请日：2018-03-26

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. Hussain ,  Oliver Taylor-Tibbott

IPC: B64D13/04 ,  F01D21/14 ,  F01D17/10 ,  F02C7/00 ,  F02C3/04

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：US12281710B2

公开(公告)日：2025-04-22

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：US10900370B2

公开(公告)日：2021-01-26

申请号：US16180652

申请日：2018-11-05

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. Hussain

IPC: F01D11/20 ,  F01D11/02 ,  F01D9/06 ,  F01D11/24 ,  F02C3/04 ,  F02C9/18 ,  F01D17/10 ,  F01D9/04

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：US10851669B2

公开(公告)日：2020-12-01

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 ,  F02K3/06 ,  F02C7/32

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：US20200256251A1

公开(公告)日：2020-08-13

申请号：US16782576

申请日：2020-02-05

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. Hussain

IPC: F02C7/14

Abstract: There is disclosed a gas turbine engine having a thermal management system, the gas turbine engine comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, and a fan located upstream of the engine core. The thermal management system comprises an oil tank; a heat exchanger; an oil coolant circuit that connects the oil tank and the heat exchanger; and an oil pump that pumps oil around the oil coolant circuit. The oil tank is located within the engine core, and the oil pump is electrically driven such that it is operable independently of the core shaft.

公开(公告)号：US11092074B2

公开(公告)日：2021-08-17

申请号：US16202631

申请日：2018-11-28

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. Hussain

IPC: F02C3/32 ,  F02C6/08 ,  F02C9/18 ,  F02C7/05 ,  F04D27/02 ,  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：US10859166B2

公开(公告)日：2020-12-08

申请号：US15936773

申请日：2018-03-27

Applicant: ROLLS-ROYCE plc

Inventor： Oliver C. Taylor-Tibbott ,  Zahid M. Hussain

IPC: B64D29/00 ,  F16K1/22 ,  F01D25/24 ,  F16K17/164 ,  F01D21/14

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.