Rolls-Royce Patente

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A system (100) for measuring loading on a test specimen (102). The system (100) includes the test specimen (102) arranged between a first loading bar (104) and a second loading bar (106). The system (100) further includes a first loading unit (112) and a second loading unit (116) configured to apply a first load (114) and a second load (118) to the first and second loading bars (104, 106), respectively. The system (100) further includes a first clamp (120) and a second clamp (130) configured to hold the first and second loading bars (104, 106) against the first and second loads (114, 118), respectively. The system (100) further includes a clamp actuating unit (140) configured to selectively release at least the first clamp (120). The clamp actuating unit (140) further includes a controller (150) configured to electrically actuate at least one first electromechanical transducer (142) from a retained state (P1) to a released state (P2) to release the first clamp (120), such that the first loading bar (104) applies a first loading wave (122) to the test specimen (102).

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Reconfigurable permanent magnet electrical machines and aircraft power and propulsion systems comprising such electrical machines are described. In one aspect, an aircraft power and propulsion system comprises: a gas turbine engine; a permanent magnet electrical machine comprising a rotor drivingly coupled to a spool of the gas turbine engine, and a stator comprising windings controllably switchable between a star configuration and a delta configuration; a DC electrical network; an AC:DC power electronics converter, an AC side of which is connected to terminals of the stator windings of the electrical machine and a DC side of which is connected to the DC electrical network; and a control system. The control system is configured to monitor at least one operating condition of the power and propulsion system and to control the switching of the stator windings between the star configuration and the delta configuration based on the at least one operating condition.

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Apparatus for supporting at least a part of an engine, the engine comprising: an engine stand configured to support at least a part of an engine; an accelerometer coupled to the engine stand and configured to: measure acceleration of the engine stand, and generate accelerometer data; and a first processor configured to receive the accelerometer data from the accelerometer.

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A fault detector (50) for a control system (1) that includes a controller (60), a solenoid driver (70), a current sensor (90) and a solenoid (80). The solenoid driver (70) provides a current to the solenoid (80) in response to a control signal provided by the controller (60) to the solenoid driver (70) and the current sensor (90) measures the current provided by the solenoid driver (70) to the solenoid (80) to determine a current measurement (40). At any moment, the control signal corresponds to one of a demanded zero current, a demanded first current magnitude or a demanded second current magnitude. The fault detector (50) detects a fault based upon a comparison of the current measurement (40) to an expected current range, wherein the expected current range is dependent upon which of the demanded zero current, demanded first current magnitude or the demanded second current magnitude the control system corresponds to at that moment.

A fuel system for a hydrogen fuelled gas turbine engine (201) comprises a tank (104) configured to store hydrogen, a pump (216) configured to provide pressurised hydrogen at an outlet thereof, and a pre-heater (218) configured to heat at least a portion of pressurised hydrogen fuel downstream of the pump (216). A preheater return offtake (226) is configured to return at least a portion of hydrogen fuel heated by the preheater (218) to the tank (104).

Electrical power systems for distributing electrical power in arrangements comprising one or more gas turbine engines 101 are described. One such electrical power system comprises: one or more rotary electric machines 111-113, each mechanically coupled to a gas turbine engine spool; a set of converter circuits 203 connected to the one or more rotary electric machines 111-113 for conversion between alternating current (ac) and direct current (dc), wherein the one or more rotary electric machines 111-113 and the set of converter circuits 203 are arranged to output a number R ≥ 2 of dc power channels 206-209, each dc power channel 206-209 having a respective index r = (1, ..., R); and a group of N dc load channels 400-1200 connected to the R dc power channels 206-209 by a switching arrangement 410-1210, wherein N > R and each dc load channel 400-1200 has a respective index n = (1, ..., N). The switching arrangement 410-1210 is operable to connect a number Q ≥ 1 of the N load channels 400-1200 to at least two different power channels of the R power channels 206-209. The system further comprises a controller configured to control the operation of the switching arrangement 410-1210 to control which of the power channels 206-209 the N load channels 400-1200 receive electrical power from.

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A hydrogen-fuelled aircraft power system (300) incorporates a gas turbine engine (301) and a fuel cell (302), in which air supply and cooling of the fuel cell (302) is integrated with the gas turbine engine (301) to improve overall efficiency of the power system (300). The system may be part of a turbofan, turboprop or electric propulsion system for an aircraft.

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