Rolls-Royce

A method (200) for scanning a plurality of components (102). The method (200) includes providing an imaging beam source (108), an imaging beam receiver (114), and a support platform (104). The support platform (104) is configured to rotate and/or revolve relative to the imaging beam source (108) and the imaging beam receiver (114) about one or more axes. The method (200) further includes disposing the plurality of components (102) on the support platform (104). The plurality of components (102) is positioned in a gap (118) between a first geometrical figure (120) and at least one second geometrical figure (122) in a configuration that reduces the variation in material thickness penetrated at different relative angles of rotation and/or revolution. The first geometrical figure (120) and the at least one second geometrical figure (122) are concentric.

A fuel system for a hydrogen fuelled gas turbine engine (201). The fuel system comprises a main hydrogen fuel line (206) configured to provide hydrogen fuel to a combustor (203) of the gas turbine engine (201) and a closed loop heat exchange fluid line (207) comprising a heat exchange fluid. The fuel system further comprises a first heat exchanger (208) configured to exchange heat between gas turbine engine compressor bleed air and heat exchange fluid in the heat exchange fluid line (207), a second heat exchanger (209) downstream of the first heat exchanger (208) in heat exchange fluid flow configured to exchange heat between the heated heat exchange fluid and hydrogen in the main hydrogen fuel line, and a third heat exchanger (215) downstream in main hydrogen fuel flow of the second heat exchanger (209) in main hydrogen fuel flow configured to exchange heat between a further engine fluid and heated hydrogen fuel.

A fuel system for a hydrogen fuelled gas turbine engine (201). The fuel system comprises a main hydrogen fuel line (206) configured to provide hydrogen fuel to a combustor (203) of the gas turbine engine (201) and a closed loop heat exchange fluid line (207) comprising a heat exchange fluid. The fuel system further comprises a first heat exchanger (208) configured to exchange heat between gas turbine engine compressor bleed air and heat exchange fluid in the heat exchange fluid line (207), a second heat exchanger (209) downstream of the first heat exchanger (208) in heat exchange fluid flow configured to exchange heat between the heated heat exchange fluid and hydrogen in the main hydrogen fuel line, and a third heat exchanger (215) downstream in main hydrogen fuel flow of the second heat exchanger (209) in main hydrogen fuel flow configured to exchange heat between a further engine fluid and heated hydrogen fuel.

A nosecone for a gas turbine engine includes a nosecone body substantially symmetrical around a central axis. The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side to an aft side of the nosecone body. The nosecone further includes an attachment assembly which attaches the nosecone body to the gas turbine engine. The nosecone includes a plurality of airstream protrusions attached to or integral with the nosecone body. A first airstream protrusion of the plurality of airstream protrusions is positioned upstream of a first fan blade to prepare an airstream flowing over the nosecone body for interaction with the first fan blade. The attachment assembly includes a plurality of attachment locations, and a first attachment location of the plurality of attachment locations is collocated with the first airstream protrusion of the plurality of airstream protrusions.

A nosecone (30) for a gas turbine engine (10) includes a nosecone body (31). The nosecone body is substantially symmetrical around a central axis (X-X). The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side of the nosecone body to an aft side of the nosecone body. The nosecone includes an attachment assembly (33). The attachment assembly is configured to attach the nosecone body to the gas turbine engine. At least one of the nosecone body or the attachment assembly comprises a tear-resistant fiber.

There is provided a flameholder (370) for a reheat assembly (300) of a gas turbine engine (10). The flameholder comprises a fuel atomizer (379A, 379B), an air passageway (375A, 375B) and a fuel passageway (374, 374A, 374B). The air passageway (375A, 375B) is configured to convey a flow of air (521A, 521B) to the fuel atomizer (379A, 379B). The fuel passageway (374, 374A, 374B) is configured to convey a flow of fuel (531A) to the fuel atomizer (379A, 379B). The fuel atomizer (379A, 379B) includes a mixing chamber (430) and a swirler (420).

There is provided a fluid flow machine (10) comprising: a casing structure (24), a turbomachine blade (311) disposed within the casing structure (24), and a sealing arrangement (330) coupled to the casing structure (24). The sealing arrangement (330) comprises (330) an abrasion portion (334) including a lattice structure (400). The abrasion portion (334) is configured to provide a seal with a tip (321) of the turbomachine blade (311). The abrasion portion (334) includes the lattice structure (400) having a lattice density that increases along a radial direction (42) of the machine (10).There is also provided a method (600) of manufacturing such a fluid flow machine (10).

There is provided a propulsion machine 10 comprising a fluid duct defined by a wall 42, 44 and a moveable member 34, 36. The propulsion machine 10 also comprises a mounting structure 92 coupled to the moveable member 34, 36, and an extendable structure 94 having a sealing surface 96 and a sensing arrangement 83. The extendable structure 94 is moveable relative to the mounting structure 92 to provide a seal between the sealing surface 96 and an opposing surface 43 of the wall 42. The sensing arrangement 83 is configured to generate one or more signals indicative of a position of the extendable structure 94 relative to the mounting structure 92.

The disclosure relates to apparatus for fuel and air injection into a combustion chamber of a gas turbine engine and to a gas turbine engine comprising such an apparatus. Example embodiments include an apparatus (200) for fuel and air injection into a combustion chamber (201) of a gas turbine engine (10), the apparatus (200) comprising: back panel (202) having front and back faces (203, 204), an aperture (205) configured to receive a fuel injector (206) and a plurality of air inlets (207) arranged around the aperture (205); a heatshield panel (208) having front and back faces (209, 210), the heatshield panel (208) having a central aperture (212) and an annular side wall (211) mounted against the front face of the back panel to form a cavity (213) between the back face of the heatshield panel and the front face of the back panel (202); and an annular swirler assembly (214) disposed in the cavity (213) between the back panel (202) and the heatshield panel (208), the annular swirler assembly (214) having a central passage (215) for flow of an air and fuel mixture into the combustion chamber (201) and a flange (216) engaged with first and second grooves (217a, 217b) in the back face (210) of the heatshield panel (208) and the front face (203) of the back panel (202) respectively.

The foregoing describes a power converter apparatus (200) with at least a first power converter (101-1) and a second power converter (101-2) connected in parallel, so as to each receive an AC voltage generated by an electrical machine (104) and output a DC voltage on a DC bus (105P, 105N). Each of first and second power converters (101-1, 101-2) is coupled to respective first and second winding arrangements (102-1, 102-2) for receiving the AC voltages, and the first winding arrangement is grounded by a first impedance (201-1) and the second winding arrangement is grounded by a second impedance (201-2). The first impedance (201-1) has an effective impedance value which is different to that of the second impedance (202-1) such, in use, a zero-sequence current between the first and second power converters at least partly cancels a common-mode voltage component.