Rolls-Royce Patente

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A method of starting a liquid hydrogen fuelled gas turbine engine (103) of an aircraft propulsion system. The aircraft propulsion system comprises a hydrogen storage tank (104) configured to store liquid hydrogen, a liquid hydrogen pump (205) configured to pump hydrogen in at least a liquid state, a core combustor (203) configured to receive hydrogen fuel from the hydrogen fuel pump (205), and a hydrogen fuel vent (214) provided downstream of the liquid hydrogen pump (205), and configured to selectively vent hydrogen fuel. The method comprises, in a liquid priming step, flowing hydrogen from the hydrogen storage tank (104) through the liquid hydrogen pump (205) and venting hydrogen through the hydrogen fuel vent (214) until the hydrogen pump (205) is primed with liquid hydrogen, then, in a liquid pumping step, operating the liquid hydrogen pump (205) to pump liquid hydrogen to the core combustor (203) at a required flow rate and pressure for engine ignition in an engine ignition step.

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An engine system comprises a first fuel store, a second fuel store, an engine arranged to produce mechanical power by combustion or oxidation of a fuel in an engine, a fuel distribution system arranged to deliver fuel from the first and second fuel stores to the engine, the first fuel delivered at a first mass flow rate, the second fuel delivered at a second mass flow rate, the first and second mass flow rates contributing to a total mass flow rate of fuel to the engine, and a control system arranged to increase the relative fraction of the total mass flow rate of fuel represented by the second mass flow rate during a period of acceleration of the engine, in order to control a surge margin of the engine, wherein the second fuel is selected to have a higher specific energy than the first fuel and to release a greater mass of water per unit mass of fuel than the first fuel.

A fuel system for a gas turbine engine (103) comprises a fuel offtake (302) configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit (217), a burner (218) configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit (217), a heat exchanger (306) configured and arranged to transfer heat from exhaust gasses produced by the burner (218) to hydrogen fuel in the main fuel conduit (217), and an outlet baffle (306) positioned between the burner (218) and the heat exchanger (306). The outlet baffle (306) is configured to introduce turbulence to combustion gases entering the heat exchanger (306).

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A probe (100) for non-destructive testing of a component (50). The probe (100) includes a head (102) configured to transmit a signal or a wave to a surface (52) of the component (50) for non-destructive testing of the component (50). The head (102) includes a first head end (104) facing away from the component (50) and an opposing second head end (106) facing the component (50). The probe (100) further includes a tube (108) spaced apart from the head (102) and including a first tube end (110) distal to the head (102) and an opposing second tube end (112) proximal to the head (102). The tube (108) defines an internal passage (114) therein extending between the first tube end (110) and the second tube end (112). The probe (100) further includes a flexible actuator (116) disposed between the head (102) and the tube (108). The flexible actuator (116) is configured to be actuated between a non-actuated state (S1) and an actuated state (S2).

A system for inspecting a complex component, the system comprising: a flexible inspection device having a driver for controlling the motion of the flexible inspection device by manipulating the relative positions of a plurality of joints within the device, the flexible device having a sensor on its distal end; a feed mechanism for controlling the insertion or retraction of the flexible device into or from the complex component; a component driver for driving the movement of an aspect of the complex component from at least a first position to a second position; and a computer running a computer program, the computer interfacing with the flexible inspection device, the feed mechanism, and the component driver, so as to link the operation of the flexible inspection device, the feed mechanism and the component driver through a single program.

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An air-breathing turbojet engine (101) for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet (102) configured to compress inlet air by one or more shocks, a cooler (103) to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor (104) to compress the air further. A combustor (105) receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine (106) expands and is driven by combustion products, and a second turbine (107) expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner (109) receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

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A thermal management system (100) for a gas turbine engine (10) includes a plurality of inlet and outlet vanes (104, 106) extending from a bypass inner wall (110) towards an outer cowl (120), a plurality of first removable shims (144), a plurality of second removable shims (146), and a third removable shim (148). Each first removable shim (144) extends between and engages the outer cowl (120) and a corresponding inlet vane (104). Each second removable shim (146) extends between and engages the outer cowl (120) and a corresponding outlet vane (106). The third removable shim (148) extends between and engages a heat exchanger (108) and the outer cowl (120). Each of the plurality of first removable shims (144), each of the plurality of second removable shims (146), and the third removable shim (148) is removable for positionally adjusting the outer cowl (120) relative to the bypass inner wall (110).

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