Rolls-Royce Patente

There is provided a fuel management system (400A) for a gas turbine engine. The fuel management system comprises: a fuel tank (41) configured to store fuel for the gas turbine engine; a fuel supply line (410) configured to supply fuel from the fuel tank to a combustor (16) of the gas turbine engine; a reheat fuel supply line (412) configured to supply fuel from the fuel tank to a reheat of the gas turbine engine, the reheat fuel supply line extending from a reheat branching point (411) on the fuel supply line to the reheat; a fuel supply pump (451) disposed along the fuel supply line upstream of the reheat branching point; a reheat pump (460) disposed along the reheat fuel supply line, the reheat pump configured to pressurise fuel to a reheat delivery pressure for delivery to the reheat; and a reheat recirculation line (480) configured to recirculate fuel from the reheat fuel supply line to a location upstream of the fuel supply pump, the reheat recirculation line extending from a reheat recirculation branching point (471) on the reheat fuel supply line downstream of the reheat pump.

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A gas turbine engine for an aircraft comprises, in axial flow sequence, a heat exchanger module, and a core engine. The core engine comprises, in axial flow sequence, an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is rotationally connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is rotationally connected to the low-pressure turbine by a second shaft. The heat exchanger module is in fluid communication with the core engine by an inlet duct. The heat exchanger module comprises a central hub and a plurality of heat transfer elements extending radially outwardly from the central hub and spaced in a circumferential array, for transfer of heat energy from a first fluid contained within the heat transfer elements to an inlet airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further comprises a first electric machine. The first electric machine is rotationally connected to the first shaft, the first electric machine is positioned downstream of the heat exchanger module, the first electric machine has a maximum electrical power output of between 180kW and 500kW, the first electric machine has an axial length in the range of between 0.20m and 0.45m, and the first electric machine has a maximum diameter in the range of between 0.15m and 0.39m.

A method of electron beam welding comprising splitting the output of an electron beam welder into two components, a pre/post heat ring and a fusion spot by rastering between the pre/post heat ring and a fusion spot, applying the two outputs to a workpiece that is to be welded, traversing the two outputs along the desired weld path, and wherein the fusion spot lies within the pre/post heat ring and travels in tandem with and inside the pre/post heat ring. The pre/post heat ring may be annular. The fusion spot may be located at the centre of the pre/post heat ring. The output of the electron beam welder may comprise 1 to 100,000 discrete points. The beams may be deflected using the EB welder deflector coils. The time the electron beam spends on each discrete point may be identical.

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An inner cowl arrangement (110) for a gas turbine engine (10) includes a first hinge (124) and a second hinge (126) pivotally connecting a first cowl member (112) and a second cowl member (118), respectively, to a mounting structure (106). The inner cowl arrangement (110) further includes a latch (128) detachably securing the first and second cowl members (112, 118). At least one of the first hinge (124), the second hinge (126), and the latch (128) includes a pressure relief component (130) that deforms or breaks when an applied load (L) on the pressure relief component (130) due to a pressure (P1) within an engine core (11) is greater a normal operating load (N), causing at least one of the first cowl member (112) and the second cowl member (118) to move relative to the engine core (11), and forming an opening (132).

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