Rolls-Royce Patente

A gas turbine engine 108A comprises an engine core 201 having first 222 and second 224 engine core exhaust paths arranged to pass first and second portions respectively of the mass flow of the engine's core exhaust mass. A heat-exchange system comprises a recuperator system 230A-D disposed within the first engine core exhaust path and arranged to transfer heat from said first portion to a buffer fluid, and a heat exchanger arranged to transfer heat from the buffer fluid to fuel within a fuel path arranged to convey fuel to the engine's combustor 208. The engine provides for heat to be recovered from the engine's core exhaust flow to the engine's fuel supply, thus improving thermal efficiency, but without significantly impeding the engine core exhaust flow or presenting the significant fire or explosion risk associated with a recuperator arranged to heat fuel directly.

A combustor assembly (100) for a gas turbine engine includes a combustor shell (110) extending along a shell axis (111). The combustor shell (110) includes a shell wall (112) extending circumferentially around the shell axis (111) and a meter panel (116) connected to an upstream end (113) of the shell wall (112). The shell wall (112) and the meter panel (116) together define a combustion space (165) therebetween. The combustor assembly (100) further includes: a tile (120) disposed within the combustor shell (110) and including a tile flange portion (125) extending radially with respect to the shell axis (111); a heatshield (140) connected to the meter panel (116) and extending at least radially towards the tile (120); a fastener (150) connecting the tile flange portion (125) to the meter panel (116); and a compartment (160) thermally shielded from the combustion space (165). Either the heatshield (140) and the tile (120) together form the compartment (160) or the tile (120) alone forms the compartment (160). The fastener (150) is spaced apart from the combustion space (165) and at least partially disposed within the compartment (160).

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A blower system (400) for supplying pressurized air to an airframe of an aircraft comprises: an air inlet (422) for receiving air from an air source; an air outlet (426) for supplying pressurized air to an airframe; a blower compressor (420) in fluid communication with the air inlet and the air outlet, the blower compressor comprising a first rotor (420a) and a second rotor (420b), wherein the first and second rotors are independently rotatable in order to compress air received from the air inlet and deliver the compressed air to the air outlet; a variable transmission (430) comprising a first output (436) for driving the first rotor, a second output (438) for driving the second rotor, and first, second and third inputs (432, 434, 435); and first and second electrical machines (464, 465), each comprising an electric rotor and an electric stator, wherein: the first input of the variable transmission is configured to be mechanically coupled to a spool (440) of a gas turbine engine (10); the second input of the transmission is mechanically coupled to the electric rotor of the first electrical machine; the third input of the transmission is mechanically coupled to the electric rotor of the second electrical machine; and the electric stators of the first and second electrical machines are electrically connected to an electrical power management system (466) configured to control the supply of electrical power to the first and second electrical machines in order to control the speed of the first and second outputs of the variable transmission.

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A feed mechanism for inserting and/or retracting a flexible robotic arm from an area, the feed mechanism comprising a housing, a passageway that extends about a central longitudinal axis through the length of the housing, a drive portion and a rotational portion, the drive portion not being fixedly connected within the housing and having at least a pair of drive wheels coupled to a drive motor, the drive wheels are connected to a mounting frame with the mounting frame being connected to pivotable linkages with at least one of the linkages being connected to a spring, such that the expansion or contraction of the spring allows the drive wheels to move relative to the longitudinal axis, and the rotational portion being coupled to a motor, the rotational motor having a gear system that connects to the drive portion and causes a rotation of the drive portion about the central longitudinal axis within the housing.

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An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 42 ≤ R ≤ 25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

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There is provided a dynamic sealing assembly for a rotary machine 400, comprising a primary sandwich plate 710, a secondary sandwich plate 720 and a bristle pack 730. The primary sandwich plate 710 comprises a plurality of primary vane openings 712, and the secondary sandwich plate 720 comprises a plurality of secondary vane openings 722. The bristle pack 730 comprises a plurality of bristles and is disposed between the primary sandwich plate and the secondary sandwich plate. Each of the plurality of primary vane openings 712 overlies and aligns with a respective secondary vane opening 722 to form a vane channel 715A, 715C, 7150 for receiving a vane 515A-515E along a longitudinal axis 703 of the dynamic sealing assembly 700. The bristle pack 730 is configured to: provide a brush seal between each vane 515A-515E received within the respective vane channels 715A, 715C, 7150 and the dynamic sealing assembly 700; and allow relative movement between the dynamic sealing assembly 700 and the vane 515A-515E received within each vane channel 715A, 715C, 7150 along the longitudinal axis 703.

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Disclosed is a fuel system for a gas turbine engine having a core exhaust and a combustion section. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and an air feed to drive the driving turbine, the air feed being fluidly connectable to the core exhaust of the gas turbine engine. Also disclosed is a fuel system comprising: a fuel pump for fluid communication with a fuel reservoir; a fuel line from the fuel pump for fluid communication with the combustion section of the gas turbine engine; and an air feed to a heat exchanger, the air feed being fluidly connectable to the core exhaust of the gas turbine engine, wherein the fuel line is in thermal communication with the air feed within a heat exchanger.

An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 300, 400, 500, 600, 700 configured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine 19, wherein a rearward movement of the turbine 19 or a shaft 26 in a shaft break event directly actuates the pressure equalisation apparatus 300, 400, 500, 600, 700 to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

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