Rolls-royce Corporation

Rollys-royce Plc

Zahid Muhammad Hussain

Christopher T J Sheaf

Brian Handley

Andrew J Mullender

Oliver C Taylor-Tibbott

Michael Georg Kozuch

Peter Ireland

David G MacManus

Vasileios Kyritsis

Kevin M Britchford

Lucian Ingley

Jonathan G Bird

Nityabh Mishra

Emile Raya

Hugh D Thomas

Robert C Pearce

Kyritsis Vasileios

Hugh Thomas

Christopher Sheaf

Michael Kozuch

Oliver Taylor-Tibbot

Andrew Mullender

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.

Butterfly valve

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.

Thermal management system for a gas turbine engine

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

Condition determination of a gas turbine engine

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.

Bleed ejector

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.

Louvre offtake arrangement

A tip clearance control (TCC) systemis provided to control the gapbetween the tips of turbine bladesof a gas turbine engineand the casingwithin which they rotate. The inletto the TCC system is provided in a bifurcation panelthat extends across a bypass ductof the gas turbine engine. The inlet is provided on a first major surfaceof the bifurcation panelthat is defined such that the direction (R) that points through the bifurcation panel from the first major surfaceto a second major surfacecorresponds to the fan rotation direction. This provides a particularly effective and/or efficient TCC system

Gas turbine engine offtake

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.

Gas turbine engine

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.

Cooling of gas turbine engine accessories using air inlet located on a keel beam

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.

There is disclosed a cooling arrangement for a turbine casing () of a gas turbine engine (). The cooling arrangement comprises a first cooling duct () that is at least partly within a second cooling duct (). The first cooling duct is for a first cooling fluid flow and the second cooling duct is for a second cooling fluid flow which flows around the first cooling duct.

Cooling arrangement for a turbine casing of a gas turbine engine

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.

Convergent-divergent nozzle

A fluidfoil includes a selectively fluid chargeable capillary and a flexible body adjacent the capillary, the shape of the flexible body being adjustable in use via controlling the degree to which the capillary is charged and therefore the forces that the capillary exerts on the flexible body.

Fluidfoil

A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet. Also a second stage of flow area modulation between the first stage and the outlet. The pressure can be equalized between the first and second stages. There is also an arrangement comprising a plurality of bleed valves and a controller to control the flow areas of at least one of the first and second stages of each bleed valve.

Bleed valve

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

Ventilation inlet

A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

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Derby, United Kingdom

Zahid Muhammad Hussain