Rolls-Royce Corporation

Plastic Logic Limited

Hieta Technologies Limited

Arm Limited

Rolls-Royce North American Technologies Inc.

Synopsys, Inc.

Xention Limited

Other

Microsoft Technology Licensing, LLC

Kabushiki Kaisha Toshiba

Pivotal Software, Inc.

Rolls-Royce High Temperature Composites Inc.

Arc International

Arc International (UK) Limited

Seating Direct International Limited

Simon James Jones

Carl Martin Hayton

David Fisher

Duncan Barclay

Nick Sandham

Ben Watson

Anusha Nirmalananthan

Mark John Simms

Aaron D Sippel

David John Thomas

Daniel Kent Vetters

Steven Hillier

Peter Broadhead

Carl Norman Graham

Kar-Lik Kasim Wong

Paul Antony Davis

Andrew J Eifert

Aris Aristodemou

Andreas Due Engh-Halstvedt

Jeffrey Allen Walston

Bruce Edward Varney

David John Madge

Basil Hartzoulakis

John Ford

Derek Edward John

Aske Simon Christensen

Mushtaq Mulla

Richard John Hamlyn

Seamus Burns

Sharjil Siddique

Colin Copeland

Matthew D Tucker

Yazid Nemouchi

Robert Ceen

Ted Joseph Freeman

Daren Croxford

Jun Shi

Henning Sirringhaus

Roderick M Townes

Frode Heggelund

Joseph P Lamusga

Charles David Ellis

Robert G Hawking

Toni Viki Brkic

Leo Vivian Lewis

Ian Victor Devereux

Matthew John Androski

Joseph Gordon Doyle

Kevin Paul Self

Oskar Lars Flordal

Jatin Naik

Julian Glyn Balsdon

Drummond Watson Hislop

Colin Michael Humphreys

Michael Jacquinto

Niall Edward Hatfield

Rupert John Taylor

Therese Louise Stowell

Helen Jane Payne

Seow Chuan Lim

Wesley Thibault

John Mills

Henry Arthur James Stanley

Andrew Robert Jones

Anasha Nirmalananthan

Keith Robert Pullen

Joe Dominic Michael Tapply

Derek Roland Pollard

Carano Bandel

Hermann Hauser

Rene Cumplido

Kalyan Chakravarthy Dudala

Roger Goodall

Alvaro Perez-Shirley

Calum Smith

Kevin Long

Mark Simms

Ben Saunders

Julian Mason-Flucke

Rhys Manell

Nunzio Palumbo

David Thomas

The present invention is related to a multiple-inlet turbine casing () for a turbine rotor () which comprises a first fluid supply channel () configured to direct a first working fluid onto the turbine rotor () and a second fluid supply channel () configured to direct a second working fluid to impart torque on the turbine rotor () in the same direction as the direction in which torque is imparted on the turbine rotor () by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.

Turbine for use with at least two working fluids

A combined heat and power system comprises a shaft (), a compressor () coupled to the shaft to compress intake gas to form compressed gas; a recuperator () to heat the compressed gas to form heated compressed gas; a combustor () to combust a fuel and the heated compressed gas to form combustion gas; a turbine () coupled to the shaft to expand the combustion gas to form exhaust gas; a load () coupled to the shaft; an exhaust outlet () to expel the exhaust gas to a heater for heating a fluid based on heat from the exhaust gas; a recuperator channel () providing a path for the exhaust gas to flow from the turbine to the exhaust outlet through the recuperator; and a bypass channel () providing a path for the exhaust gas to flow from the turbine to the exhaust outlet bypassing the recuperator.

Combined heat and power system

A combined combustor and recuperator is formed with the recuperator surrounding the combustor. Cold gas conduits () through the recuperator follow along involute paths toward the combustor. Hot has conduits () through the recuperator follow counterflow paths along corresponding involute curves outward from the combustor. The openings () in the combustion chamber wall through which cold gas enters the combustion chamber may be directed to impart flow direct to the cold gas to support particular desired behaviour of the cold gas in the portions of the combustion chamber concerned, e.g. supporting a stable vortex flame, enhancing mixing, providing a protective barrier layer.

Combustion chamber and heat exchanger

A method for transporting items in a system including plural structures of different designs, plural robots connected in a wireless network for transporting the plural structures, and a control system connected in the wireless network. The method includes: receiving, by the control system, a transport request indicating a structure to be transported from a current location to a new location and determining, by the control system, based on the transport request, a number of robots to assign to the transport request. The method further includes: coordinating, by the control system, a lift operation by the number of robots of the structure, wherein during the lift operation each robot engages with a lifting location associated with the structure, and coordinating, by the control system, transport, by the number of robots, of the structure to the new location.

System and method for transporting inventory items in logistic facilities

A heat exchanger component comprises a core portion with alternating first and second heat exchanging channels. A first ducting portion comprises first ducting channels for transfer a first fluid between a first fluid inlet/outlet and the first heat exchanging channels of the core portion, and second ducting channels for transfer of second fluid between a second fluid inlet/outlet and the second heat exchanging channels of the core portion. The first ducting channels direct the first fluid around the turn of at least 45 degrees and the second ducting channels direct the second fluid around a turn of at least 90 degrees. The first and second ducting channels are interleaved.

Heat exchanger

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Keystoned blade track

An apparatus () includes an internal combustion engine () and an inverted Brayton cycle heat engine (). Hot exhaust gas from the internal combustion engine () contains water. The hot exhaust gas drives the inverted Brayton cycle heat engine. A condenser () in a fluid path of the exhaust gas between an inverted-Brayton-cycle turbine and an inverted-Brayton-cycle compressor condenses at least some of the water from the exhaust gas to form condensed water. This condensed water follows a recirculation path () so as to be re-introduced as a working fluid into one or more of the heat engines described above, or further heat engines, e.g. the condensed water is heated by the exhaust gas using a steam-generating heat exchanger () to generate steam which drives a steam turbine ().

Inverted brayton cycle heat engine

A radial flow turbine heat engine includes a compressor, a recuperator, a combustor and a turbine. A compressor outlet manifold collects compressed gas from the compressor through a plurality of compressor outlets. A turbine inlet manifold supplies combustion gas to the turbine through a plurality of turbine inlets. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft of the turbine to provide a flow path for compressed gas through the recuperator located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine. Furthermore, a flow path for the combustion gas is provided to the turbine inlets which are radially inward with respect to the rotation axis of the shaft compared to flow paths for the compressed gas within the compressor outlet manifold proximal to those turbine inlets.

Radial flow turbine heat engine

A fluid-fillable cushion comprises upper and lower layers, a first chamber and a second chamber and a discrete pressure distributing unit situated between the upper and lower layers, said pressure distributing unit providing a fluid connection between at least the first chamber and the second chamber. Such a cushion reduces leaks and allows controlled pressure equalisation between the chambers. Also disclosed is a process for making such cushions and seating products comprising such cushions.

Cushion

An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.

Dual walled component for a gas turbine engine

A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

Full hoop blade track with flanged segments

A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.

Sealing attachment for a gas turbine engine

Methods, systems, and computer readable media for backing up and restore a deployment on a cloud computing platform are described. A deployment on a cloud computing platform includes a set of virtual machines and corresponding disks. A deployment may include multiple subunits designated as deployment jobs. A respective job specification file specifies respective resources used by each deployment job. The resources include various scripts specifying actions to take before, during, and after a backup. A backup orchestrator, upon receiving a backup request for the deployment, executes the scripts in a pre-specified sequence ordered by script type. When a particular type of scripts executes, the corresponding script for each deployment job, if specified in the specification file to correspond to that type, executes. When all scripts of a particular type finish execution, scripts having a next type execute. Accordingly, the operations of backing up multiple deployment jobs are synchronized and orchestrated.

Backup and restore framework for distributed computing systems

A method for the manufacture of a component having an internal cavity is described. The method comprises; defining an external geometry of the component, defining a core geometry of the component; and using an additive layer manufacturing (ALM) method, building the component from a plurality of layers laid on a first plane. The core geometry is advantageously designed to suit manufacture of the component using an ALM method which involves local melting of powder in a powder bed to form the layers, permitting easy removal of excess powder from the internal cavity.

Manufacture of component with cavity

Growing community of inventors

London, United Kingdom

Simon James Jones