Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Richard Peace

Paul Broughton

Robin Charles Kennea

Gary Alan Skinner

Michael Christopher Willmot

Oliver C Taylor-Tibbott

Robert Goulds

Philip Summerfield

Andrew J Eifert

Robert T Duge

Richard Andrew Young

Matthew Peter Fitt

Lucian Ingley

Paul K Johnson

Justin Sean Dalton

Rong Yang

Brian Richard Lace

Jason Watkiss

John Philip Richardson

Liam Kelly

Joshua Lee

John G Marshall

Adam Newman

Robin Kennea

Justin Dalton

Roberts Goulds

Gawain Charles Raydon Badcock

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

Propulsion system comprising a hydrogen-burning gas turbine engine

A propulsion system includes two gas turbine engines and an air-provisioning system. The air-provisioning system includes a first ejector, a second ejector, a plenum fluidically connected with the first ejector and the second ejector, and a first propulsor. The air-provisioning system is configured to bleed and mix air from each gas turbine engine in the ejectors so as to provide selectively a flow of plenum air from the plenum to the first propulsor at a desired pressure and a desired flow rate to power the first propulsor.

Air-provisioning system with ejectors

A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material; a second layer comprising a composite; and a third layer positioned between the first layer and the second layer, the third layer being configured to attenuate acoustic waves over a predetermined frequency range.

Fairings for power generation machines

An electric propulsion unit () for an aircraft is shown. A fan () produces a pressured airflow (P) by raising the pressure of an incident airflow (I). An electric machine () is arranged to drive the fan and is located within a casing (). A primary cooling circuit () is located within the casing, and includes the electric machine and a first pass of a fluid-fluid heat exchanger (), thereby placing the electric machine and the fluid-fluid heat exchanger in thermal communication. A secondary cooling circuit includes a second pass of the fluid-fluid heat exchanger and an air-fluid heat exchanger () located within the pressurised airflow produced by the fan, thereby placing the fluid-fluid heat exchanger and the air-fluid heat exchanger in thermal communication.

Cooling

A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material and defining a first surface and a second opposite surface, the first layer being configured to enable the fairing to be coupled to the power generation machine; and a second layer comprising a composite material and defining a first surface and a second opposite surface, the second layer being coupled to the first layer, the second surface of the second layer defining an external surface of the fairing.

A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor.

Gas turbine engine with compressor bleed valve including at least two open positions

A gas turbine engine has a nacelle providing an external skin of the engine, a casing structure radially inwards of the external skin and providing an outer surface of an air flow duct of the engine, and plural engine components located in the bay formed between the casing structure and the nacelle. The components are part of either a first set of components or a second set of components. The components of the first set are all the components from the bay which are potential ignition sources, and the components of the second set are all the remaining components from the bay. The engine further has a container located in the bay, the container being fireproof capable of withstanding the application of heat by a standard flame for 15 minutes and the container containing the components of the first set.

Gas turbine engine fireproofing

A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.

Gas turbine engine keel beam

A mounting bracket for mounting an accessory to a gas turbine engine, the mounting bracket including a space frame structure. The space frame structure including a plurality of struts joined to one another at nodes.

Mounting bracket

A gas turbine engine having a fire wall configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone. The gas turbine engine also has: (i) an actuator located in the first zone, (ii) an actuatable device that is located in the second zone, (iii) a bypass duct, (iv) an off-take device to extract cooling air from the bypass duct in the gas turbine engine and to supply the extracted cooling air into the elongate housing/shell, the off-take device having a first passage and a second passage, and (v) a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to actuate the actuatable device by transmitting a mechanical force to the actuatable device.

Gas turbine engine with a fire wall and an off-take device

An electrical raft assembly for a gas turbine engine is provided. The raft assembly comprises a rigid electrical raft formed of a rigid material that includes an electrical system comprising electrical conductors embedded in the rigid material. The raft assembly further comprises an engine component that is mounted to the electrical raft. The electrical raft includes one or more integral cooling passages which guide a coolant fluid through the raft to cool the engine component.

Electrical raft assembly

An electrical raftcomprising electrical conductorsembedded in a rigid material are provided to a gas turbine engine. The raftis used to transport electrical signals (which may be, for example power and/or control signals) around a gas turbine engine. The electrical rafthas an electrical connectorembedded therein which is used to connect the electrical raft to an electrical unit, such as an EEC of a gas turbine engine The electrical connectoris resiliently biased so as to ensure a reliable electrical connection.

Electrical connectors

A gas turbine enginecomprises at least one rigid raft assembly that has a fluid passagewayat least partially embedded therein. The fluid passagewayis at least a part of a fluid system. In addition to the fluid passageway, the rigid raft assemblyalso has at least a part of another system. For example, the rigid raft assembly may also include electrical conductors, which are part of an electrical system. The rigid raft assemblymay be lighter, easier to assemble, more robust and more compact than conventional solutions for providing systems to gas turbine engines.

Gas turbine engine systems

The present invention provides a gas turbine engine part which has a primary purpose in the engine which is structural and/or aerodynamic. The part is formed of rigid composite material, and has an electrical system comprising electrical conductors permanently embedded in the composite material. This provides advantages in terms of weight, complexity, and build time.

Gas turbine part having an electrical system embedded in composite material

An electrical assemblycomprising an electrical raftand an electronic unitis provided to a gas turbine engine. The electrical rafthas electrical conductorsembedded in a rigid material, which may be a rigid composite material. The electrical conductorsare in electrical contact with the electronic unit. When the electronic unitis installed, at least a partof it forms a part of a gas-washed surface of the engine. The electronic unitis then easily accessible from the engine, and potentially complex and/or heavy access doors/panels may not be required.

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Derby, United Kingdom

Richard Peace