A fan blade device includes a plurality of main fan blades and extension fan blades. Each main fan blade includes a main fan blade body arranged obliquely, a plurality of first protrusions, and at least one engaging groove. Each extension fan blade includes an extension fan blade body arranged obliquely and having a top surface that is contiguously flush with a top surface of the main fan blade body of a respective main fan blade, a plurality of second protrusions respectively abutting against the first protrusions of the respective main fan blade, and at least one engaging piece engaging the at least one engaging groove of the respective main fan blade.

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.

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%.

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 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.

A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.

Provided is an axial fan including: a rotor blade having a rotation axis along an air-blowing direction; and a casing, wherein the casing includes: an outer frame portion housing the rotor blade; a cylindrical base portion located on the rotation axis; and a fixed blade provided between an inner peripheral surface of the outer frame portion and an outer peripheral surface of the base portion and downstream of the rotor blade in the air-blowing direction, the fixed blade includes a wind receiving surface, and the wind receiving surface in a first cross section, along the air-blowing direction, of the fixed blade has a smaller blade curvature than the wind receiving surface in a second cross section of the fixed blade along a cutting plane line at a position moved in a rotation direction of the rotor blade from a cutting plane line of the first cross section.

Provided is an axial fan including: a motor; and an impeller for sending air in an air-blowing direction, wherein the impeller includes: a base covering the motor; and plural blades mounted on an outer peripheral surface of the base, a wind receiving surface of the blade includes a concave portion recessed toward a downstream side in the air-blowing direction, a bottom point of the concave portion is located downstream in the air-blowing direction relative to a first imaginary line perpendicular to the air-blowing direction, the first imaginary line being drawn in a radial direction from a joint position of the blade where the wind receiving surface and the outer peripheral surface of the base merge, and the bottom point is displaced from inward to outward in the radial direction, in going from upstream to downstream in the air-blowing direction, until reaching a radially central part of the blade.

A propeller fan includes a hub rotatable about an axis, and a plurality of blades extending radially outward from an outer peripheral surface of the hub. A ring surrounds the plurality of blades and is connected to each blade tip. A maximum camber location is on a camber line where a distance from a chord line to the camber line in an arc-shaped cross section of each blade about the axis is maximum. An axial height is from a trailing edge to the camber line in a direction along the axis. Each blade has a first portion provided inside in the radial direction of rotation and whose axial height at the maximum camber location is substantially constant, and a second portion provided outside in the radial direction of rotation and whose axial height at the maximum camber location increases toward the blade tip.