One embodiment includes a fuel injector. The fuel injector assembly comprises a conduit for conveying fuel from a fuel inlet to a nozzle. The conduit is located in a support, with the conduit, the nozzle, and the support being a single unitary piece. A thermally compliant feature is located at the nozzle which allows the fuel injector to adjust for differential thermal expansion.

A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.

An intertial particle seperator (IPS) including an intake air duct, a scavenge duct that shares an interior common wall with the intake air duct, a clean air duct, and a splitter. The splitter is configured to split a flow of intake air into a flow of scavenge air to pass through the scavenge duct and a flow of clean air to pass through the clean air duct. The IPS also includes a plurality of valleys on the intake air duct. The plurality of valleys includes a plurality of troughs and peaks along the interior common wall. In addition, each trough of the plurality of valleys extends along a direction of the flow of intake air.

A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158; 402) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).

A pump side part for use with a centrifugal slurry pump for pumping a fluid mixture containing particulate matter, the pump side part comprising a main body having a main axis, the main body including a side wall section which extends laterally with respect to the main axis and has opposite facing first and second sides, a plurality of formations on a surface of the second side including an inner formation and an outer formation in spaced relation to the inner formation, the formations being configured so that in use the formations generate a flow of the fluid mixture across the surface which detaches from the surface the particulate matter adjacent thereto.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4) that forms a wave (W) having a specific three-dimensional waveform.

An acoustic panel is provided that includes a perforated first skin, a second skin and a core. The core is between and connected to the perforated first skin and the second skin. The core includes a plurality of chambers, a first corrugated structure and a second corrugated structure. The chambers includes a first chamber. The first chamber extends from the perforated first skin, through the first corrugated structure and the second corrugated structure, to the second skin.

A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along a leading edge and a trailing edge. The blade also includes a first corrugated surface extending from the trailing edge to the leading edge on an outer surface of the concave pressure side outer wall, and/or a second corrugated surface extending from the trailing edge to the leading edge on an outer surface of the convex suction side outer wall. The blade acts to reduce flow velocity losses associated with wake mixing by accelerating the mixing process from the source of the wake to minimize inflated unsteady mixing that occurs within a downstream blade row.

A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant, the airfoil body having an outer surface and an inner surface facing the radially extending chamber. A first corrugated surface is on at least a portion of the outer surface of the airfoil body; and a first rib partitions the radially extending chamber, the first rib including a first side and an opposing second side. A second corrugated surface is on at least a portion of at least one of the first and second sides of the first rib.

The disclosure relates to a ceramic matrix composite (CMC) aerofoil. Example embodiments include an aerofoil comprising first and second tubular CMC cores (302, 303) extending along a longitudinal axis of the aerofoil; and an outer CMC layer surrounding the first and second tubular CMC cores (302, 303) and defining an outer shape of the aerofoil having leading and trailing edges, wherein fibres within a wall of the second tubular CMC core extend to the trailing edge of the aerofoil.