A cooling system includes a fan and a system component. The fan includes a plurality of fan blades and configured to rotate in a fan direction. The system component is located downstream of the fan, and includes a cutout for passing of airflow from the fan, and a bridge spanning the cutout. The bridge includes a center section and at least one arm section extending from the center section to an edge of the cutout along a curved path offset towards the fan direction.

In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.

A method of designing a turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, providing a fan section including a plurality of fan blades, providing a low pressure turbine driving the plurality of fan blades through a gear train, providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle, providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and providing a fan variable area nozzle in communication with the fan bypass flow path and defining a fan nozzle exit area between the fan nacelle and the core nacelle.

A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.

A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.

An apparatus includes a pipeline-transport compressor configured to receive, in use, a product stream from a pipeline. The cooler unit is configured to receive, in use, a cooler air intake from the pipeline-transport compressor. This is done in such a way that removal of the cooler air intake by the cooler unit, in use, moves the cool air across the cooler bundles and out through the cooler unit, and cools the pipeline-transport compressor. An air exhaust power generation unit is configured to generate, in use, electric power in response to the cooler unit, in use, urging, at least in part, the cooler air intake toward, at least in part, the air exhaust power generation unit.

A component is provided for a turbine engine. The component can include an airfoil defining a surface, and an energy absorbing composite positioned on the surface of the airfoil or within the airfoil. The energy absorbing composite includes a shear thickening fluid distributed through a matrix.

A fan wheel with a hub is centrally supported with respect to a drive and coaxially rotatable with the hub between stops relative to the hub. The fan wheel having fan blades extending radially from the hub are rotatable about their axes in a range delimited by the stops. Overlaying the rotational support between the stops of the hub, a rotational support between the hub and the drive is provided including a planetary drive in operative arrangement with an adjustment control ring of the driven hub. The fan blades are rotatable in the hub about their blade axes, and adjustment of the blade angles of the fan blades via drive connections to the adjustment control ring, which connections operate in a manner superimposed on one another starting from the drive of the fan wheel.

A cooling fan and an electronic device are provided. The cooling fan comprises a plurality of blades disposed in a circumferential direction of a rotating shaft. The plurality of blades includes a first blade and a second blade. A windward surface of the first blade includes a first alignment part and a first offset part. The first alignment part is aligned with a windward surface of the second blade, and the first offset part and the windward surface of the second blade are arranged in a staggered manner.