Rolls-Royce Patente

A fuel delivery system comprises a pump, a fuel metering device located downstream of the pump, and a fuel spill loop from the fuel metering device to a discharge point at a location upstream of the pump. The fuel metering device regulates the fuel flow to a combustor and directs surplus fuel delivered by the pump through the fuel spill loop. The system further includes a means for controlling one or more of the pressure and volume of the fuel flow delivered to the fuel metering device independently of the engine operating conditions to thereby control the temperature of the fuel.

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A method of controlling at least a part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling rotation of a low pressure compressor using a first electrical machine to increase angular velocity of the low pressure compressor; and controlling rotation of a high pressure compressor using a second electrical machine to restrict angular velocity of the high pressure compressor while the angular velocity of the low pressure compressor is increased.

A vane assembly (200) includes an aerofoil (201) having a leading edge (210), a trailing edge (220), a pressure surface (230) and a suction surface (240). The aerofoil (201) includes a blade member (250) forming the trailing edge (220), at least a portion of the pressure surface (230) and at least a portion of the suction surface (240). The blade member (250) is formed of a first material. The aerofoil (201) further includes a spar (260) at least partly enclosed by the blade member (250) and forming at least a portion of the leading edge (210). The spar (260) further forms at least one cooling channel (270) and supports at least a portion of an interior surface (255a, 255b) of the blade member (250). The spar (260) is formed of a second material different from the first material. The second material has a greater impact resistance than the first material.

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A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment (24) and a carrier (26). The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

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The present disclosure concerns machine tools and more specifically compensation of variations which may occur within a multi-axis machine tool during a cutting process. An example embodiment includes a method of machining a workpiece using a machine tool (100) comprising a machining head (101) and a workpiece holder (108) moveable relative to each another the method comprising: performing a first machining operation on a workpiece (106) mounted to the workpiece holder (108) according to a first programmed series of movements of the machining head (101) relative to the workpiece holder (108), the first machining operation having a first maximum machining tolerance; performing a second machining operation on the workpiece (106) according to a second programmed series of movements of the machining head (101) relative to the workpiece holder (108), the second machining operation having a second maximum machining tolerance; performing a measurement operation to determine a position of an artefact (202) on the machine tool (100); calculating an offset relative to a corresponding previously stored position of the artefact (202); and applying the offset to the second programmed series of movements prior to performing the second machining operation, wherein the second maximum machining tolerance is smaller than the first maximum machining tolerance.

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A method (100, 100a, 100b) of calibrating an engine core (11) of a gas turbine engine (10), wherein the engine core (11) comprises a turbine (19), combustion equipment (16), a compressor (14), and a core shaft (26) connecting the turbine (19) to the compressor (19), the core shaft (26) arranged to drive a propulsive fan (23) of the gas turbine engine (10), the method (100, 100a, 100b) comprising: providing (102) a resistance load (62) on the core shaft (26), the resistance load (62) arranged to replicate the load of a propulsive fan (23); driving (104) the engine core (11); measuring (106) a performance parameter or the engine core (11); measuring (108) a thrust generated by the engine core (11); and determining (112) power rating data of the engine core (11), providing a correlation between the performance parameter and the thrust.

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A computer-implemented method comprising: controlling input of at least a portion of a first training data set into a first machine learning algorithm, the first training data set including: data quantifying damage to a first compressor; and data quantifying a first operating parameter of the first compressor; executing the first machine learning algorithm; receiving data quantifying the first operating parameter as an output of the first machine learning algorithm; and training the first machine learning algorithm using: the received data output from the first machine learning algorithm; and data quantifying the first operating parameter of the first compressor, the trained first machine learning algorithm being configured to enable determination of operability of a second compressor of a gas turbine engine.

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Control systems and methods for controlling an engine. The control system (202, 300) includes a computation module (204, 306) and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, which provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor (210, 324); and a first network interface device (330). The computation module includes a second processor (208, 320) with higher processing power than the first processor, and a second network interface device (322). The control system also includes a sensor (318) configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator (316) operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

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