Derby, United Kingdom
Derby, United Kingdom

Rolls-Royce Holdings plc is a British multinational public holding company that through its subsidiaries, designs, manufactures and distributes power systems. Rolls-Royce Holdings is headquartered in City of Westminster, London. It is the world’s second-largest maker of aircraft engines, and also has major businesses in the marine propulsion and energy sectors. Rolls-Royce was the world's 16th-largest defence contractor in 2011 and 2012 when measured by defence revenues. It had an announced order book of £71.6 billion as of January 2014.Rolls-Royce is listed on the London Stock Exchange and is a constituent of the FTSE 100 Index. As of June 2013, it had a market capitalisation of £22.22 billion, the 24th-largest of any company with a primary listing on the London Stock Exchange. Wikipedia.

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Patent
Rolls-Royce | Date: 2017-09-20

The invention relates to an apparatus, comprising: a fuel supply (102) for a turbine engine; a means (202) for maintaining a specified pressure in the fuel supply (102), the means (202) disposed within a body (302), the specified pressure at or greater than a critical pressure of a fuel of the fuel supply; and a plurality of fueling passages (204) fluidly coupling the means (202) for maintaining the specified pressure to a plurality of nozzle exits (214), wherein each of the fueling passages (204) has a corresponding inlet (309) and a corresponding one of the nozzle exits (214), the inlets (309) of the fueling passages (204) are positioned on a surface of a plate (306) within the body (302), the surface exposed to the means (202) for maintaining the specified pressure, each of the inlets (309) is positioned on the surface to receive a portion of fuel received from the means (202) for maintaining the specified pressure.


Patent
Rolls-Royce | Date: 2017-09-13

A system includes one or more synchronous generators mechanically coupled to an excitation system. The excitation system is configured to output an excitation signal to excite the synchronous generator to produce a voltage and a current at an output of the synchronous generator. During startup of the synchronous generator, the excitation system may also output pulses of the excitation signal to initiate synchronism of one or more non-rotating electric motors electrically coupled to the synchronous generator. In addition, the pulses may be output to urge rotation of the non-rotating electric motors into rotational electrical alignment with the synchronous generator and each other.


Patent
Rolls-Royce | Date: 2017-09-20

Described is a turbine arrangement of a gas turbine engine, the turbine comprising: a rotor comprising a disc which incorporates a plurality of circumferentially spaced turbine blades, each blade having an aerofoil extending for a platform and a root portion securing the blade to the disc, a lock plate located at an axial end of the root portion of the blade, the lock plate comprising: a plate body having an inward facing surface which is located adjacent the blade root and an outward facing surface, radially inner and outer edge portions, and first and second circumferential edges; a head located at the radially outer edge portion of the plate body; a foot portion located at the radially inner portion of the plate body; a projection extending from the outwardly facing surface away from the turbine blade root in use, the projection being located adjacent to the foot portion, wherein the foot portion and head portion are located within slots provided at least partially by the disc and turbine blade respectively.


Patent
Rolls-Royce | Date: 2017-09-13

A combustion staging system for fuel burners of a multi-stage combustor of a gas turbine engine is provided. The system has pilot and mains fuel manifolds respectively distributing fuel to pilot and mains stages of the burners. The system further has a plurality of check valves through which the mains manifold feeds fuel to the respective burners. The check valves are arranged to open when the fuel pressure within the mains manifold exceeds a predetermined fuel pressure relative to gas pressure in the combustor. The system further has a splitting unit which receives a metered fuel flow and controllably splits the received fuel flow into pilot and mains flows which are sent respectively to the pilot and mains fuel manifolds to perform staging control of the combustor. The splitting unit is operable to select the pilot manifold and to deselect the mains manifold for pilot-only operation in which there is a pilot supply to the combustor but no mains supply to the combustor from the burners. It is also operable to select both the pilot and mains manifolds for pilot and mains operation in which there are pilot and mains supplies to the combustor from the burners. The system further has a cooling flow recirculation line having a delivery section arranged to provide a cooling flow of fuel to the mains manifold when that manifold is deselected so that the deselected mains manifold remains primed with relatively cool fuel, and a return section arranged to collect the cooling flow from the mains manifold. The system further has a gas pressure sensor configured to measure gas pressure in the combustor, a speed sensor which measures a rotation speed of a rotor of the engine, and a control unit which, when the mains manifold is deselected for pilot-only operation, (i) compares the measured rotation speed with a predicted rotation speed for the metered fuel flow, and compares the measured gas pressure with a predicted gas pressure for the metered fuel flow, and (ii) is adapted to close off the recirculation line when the results of these comparisons are indicative of leakage of fuel from the cooling fuel flow into the combustor through one or more of the check valves.


Patent
Rolls-Royce | Date: 2017-09-27

An axial flux permanent magnet machine comprising a pair of axially spaced first components. A second component positioned axially between and equidistant from the first components. Either the pair of first components or the second component is arranged to rotate about a shaft. A translation mechanism coupled to each of the first components. The translation mechanism configured to translate the first components axially away from the second component. Also a method of controlling an axial flux permanent magnet machine.


Patent
Rolls-Royce | Date: 2017-09-20

The present invention provides a sensor system for measuring a parameter (e.g. volume, temperature or pressure) of a target, the system comprising a diaphragm, a sensor for measuring the axial spacing between the sensor and the diaphragm, and an axially adjustable mount. The mount has a first axial end for mounting the diaphragm which is axially movable relative to the sensor and an opposing, second axial end which is axially fixed relative to the sensor. The diaphragm and mount define a chamber for receiving the target or for being received within the target. In use, the axial spacing between the first axial end and the second axial end of the mount and thus the axial spacing between the diaphragm and sensor varies as a result of a change in the parameter differential across the diaphragm.


Patent
Rolls-Royce | Date: 2017-09-27

A propulsion system is described that includes an electrical bus, a generator configured to provide electrical power to the electrical bus, a plurality of propulsors configured to provide thrust by simultaneously being driven by the electrical power at the electrical bus, and a controller. The controller is configured to synchronize a rotational speed of an individual propulsor from the plurality of propulsors with a rotational speed of the generator after the individual propulsor has become unsynchronized with the rotational speed of the generator by controlling at least one of a rotational speed of the generator, a nozzle area of the individual propulsor, or a pitch angle of the individual propulsor.


Patent
Rolls-Royce | Date: 2017-09-20

A stainless steel alloy comprising essentially of 19 to 22 percent by weight chromium, 8.5 to 10.5 percent by weight nickel, 5.25 to 5.75 percent by weight silicon, 0.25 to 2.0 percent by weight carbon, 4.0 to 10.5 percent by weight molybdenum, 0.3 to 0.5 percent by weight titanium, 0.1 to 0.5 by weight percent nitrogen and the balance iron plus impurities. The impurities may consist of 0 to 0.2 percent by weight cobalt, 0 to 0.5 percent by weight manganese, 0 to 0.3 percent by weight molybdenum, 0 to 0.03 percent by weight phosphor, 0 to 0.03 percent by weight sulphur, 0 to 0.1 percent by weight nitrogen.


A combustion chamber system comprises a pilot fuel manifold (34), a main fuel manifold (36), pilot fuel nozzles (66) and main fuel nozzles (68). Each pilot nozzle (66) is connected to the pilot manifold (34) and each main nozzle (68) is connected to the main manifold (36). A greater total amount of fuel is supplied to the pilot nozzles (66) than to the main nozzles (68) and a greater amount of fuel is supplied to pilot nozzles (66) at, or in, a first region of the combustion chamber (30) than to pilot fuel nozzles (66) at, or in, a second region of the combustion chamber (30) and a greater amount of fuel is supplied to the main nozzles (68) at, or in, the first region than to the main nozzles (68) at, or in, the second region to improve combustion efficiency, weak extinction and relight of the combustion chamber in a first mode of operation. A greater total amount of fuel is supplied to the main nozzles (68) than to the pilot nozzles (66) in a second mode of operation.


A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.

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