Rolls-Royce Patente

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

There is disclosed a reheat assembly (100) for a gas turbine engine, the reheat assembly comprising; a jetpipe casing (102,310) defining a reheat core section (104) configured to duct a core flow of air and a reheat bypass section (106) configured to duct a bypass flow of air. The reheat bypass section is disposed radially outward of the reheat core section, and the reheat core section and the reheat bypass section are at least partially separated by a support duct (110). An integrated flameholder (130,230) is mounted to the jetpipe casing, and a fuel pipe (132) is configured to convey fuel to the integrated flameholder. The integrated flameholder comprises a flameholder body (140) extending radially inward from the jetpipe casing through the reheat bypass section and into the reheat core section to promote a wake-stabilised region (142) downstream of the flameholder body; and an integrated atomiser (150) configured to atomise fuel provided to the integrated flameholder and to discharge the atomised fuel into the wake stabilised region.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A hydrogen-fuelled aircraft 200 comprises a fuselage 218, wings 216A, 216B and a plurality of cylindrical elongate hydrogen storage tanks 212A-I mounted on the exterior of the fuselage and disposed vertically above a plane 210 containing the wing-tips of the aircraft. An aerodynamic fairing 214 forms a continuous air-washed surface of the aircraft together with a lower portion of the fuselage 218. The hydrogen storage tanks extend generally parallel to the fuselage and are contained between the fairing and the fuselage. The aircraft 200 provides for storage of a large volume of compressed hydrogen without compromising the volume of usable space within the fuselage. The aircraft is able to carry out flight missions comparable in range and payload to those of an equivalent conventionally-fuelled aircraft.

An aircraft propulsion system comprises first and second engines (100, 200) and first (134) and second electrical machines coupled to the first and second engines respectively. The first electrical machine is arranged to be driven by electrical power in order to at least partially drive the first engine. The second electrical machine is arranged to be driven by the second engine to generate electrical power. An electrical network (31) allows transmission of electrical power between the electrical machines. A controller (25) is arranged to selectively reduce fuel flow to the first engine and provide electrical power from the second electrical machine to the first electrical machine to drive the first electrical machine, based on expected properties of contrails formed in an exhaust plume of the first engine and/or the second engine. The system allows the formation of contrails by the engines to be managed in order to mitigate climatewarming effects of the contrails.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Electrical power systems and methods of operating electrical power systems are provided. In one aspect, an electrical power system comprises first and second electrical machines, each comprising a permanent magnet rotor and a stator comprising a plurality of electrically isolated polyphase winding sets; and a control and health monitoring system configured to detect rotor demagnetization of the first and/or second electrical machine by: supplying electrical power to each polyphase winding set of the plurality of polyphase windings sets of the first electrical machine; stopping the supply of electrical power to a first polyphase winding set of the first electrical machine; measuring a first voltage across the first polyphase winding set of the first electrical machine; supplying electrical power to each polyphase winding set of the plurality of polyphase windings sets of the second electrical machine; stopping the supply of electrical power to a first polyphase winding set of the second electrical machine; measuring a second voltage across the first polyphase winding set of the second electrical machine; determining first and second magnetic flux linkage indicators based on the first and second voltages; and determining whether the permanent magnet rotor of the first and/or second electrical machine is demagnetized based on the whether a ratio of the first and second magnetic flux linkage indicators passes a threshold.

A fuel system for a gas turbine engine (103) configured to combust hydrogen fuel. The fuel system comprises a main fuel conduit (226), a fuel pump (224) configured to operate on hydrogen within the fuel conduit (224) to provide pressurised fuel to a core combustor (236) of the gas turbine engine (103), an auxiliary combustor (228) downstream in fuel flow of the fuel pump (224), and configured to combust a portion of fuel diverted from the main fuel conduit (224) and to heat a remainder of fuel in the main fuel conduit (224), and a fuel turbine (234) downstream in fuel flow of the auxiliary combustor (228). The fuel turbine (234) is configured to be driven by the heated fuel from the auxiliary combustor (228) and configured to power the fuel pump (224). The fuel system comprises a turbine inlet valve (247) provided upstream in hydrogen fuel flow of the fuel turbine (234) and configured to control mass flow rate and I or pressure of fuel flowing into the fue turbine (234).I. A method of operation is also described.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A method (300) for manufacturing a composite component (50) includes providing a tool (100) switchable between a deposition configuration (105) and a flange-forming configuration (107). The tool (100) includes a first portion (110) including a first deposition surface (111), a second portion (120) including a second deposition surface (121) and a pre-form support surface (122), and a flange-forming block (130) including a curved surface (131). The method (300) further includes depositing a composite material at least partially on each of the first deposition surface (111) and the second deposition surface (121) in the deposition configuration (105) to provide a composite pre-form (140). The method (300) further includes moving the second portion (120) relative to the first portion (110) to transition the tool (100) to the flange-forming configuration (107), which causes the composite pre-form (140) to at least partially engage each of the pre-form support surface (122) and the curved surface (131). The curved surface (131) defines a radius (51R) of a flange (51) of the composite component (50).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A cleaning system (100) for cleaning gas paths (210) in an engine core (211) of a gas turbine engine (200) is provided. The cleaning system (100) includes a source (102) of an engine cleaning liquid (104); an engine cleaning mist forming unit (106) that vapourises the engine cleaning liquid (104) to form an engine cleaning mist (114) and delivers the engine cleaning mist (114) into the engine core (211) of the gas turbine engine (200); at least one delivery device (108) configured to deliver the engine cleaning liquid (104) to the engine cleaning mist forming unit (106); a pump (110) configured to draw the engine cleaning mist (114) through the engine core (211) to clean the gas paths (210) within the engine core (211); and a mist collecting arrangement (112) including a condensing chamber (116). The mist collecting arrangement (112) is configured to collect the engine cleaning mist (114) that has passed through the engine core (211) and condense the collected engine cleaning mist (114) in the condensing chamber (116). A method (600) of cleaning an engine core (210) of a gas turbine engine (200), and a gas turbine engine (200), are also described.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …