A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

A compressor has: a rotor and a stator having vanes, a vane of the vanes having an airfoil extending from a root proximate an inner hub to a radially outer tip, the airfoil having a leading edge, a trailing edge, and a chord extending between the leading edge and the trailing edge to define a chord length, the airfoil having a pressure side surface and a suction side surface, and a fillet disposed at the leading edge of the root of the airfoil and extending between the pressure side surface and the inner hub, the fillet having a radial height being maximum at the leading edge, the radial height decreasing from the leading edge to blend smoothly into a remainder of the airfoil, the fillet extending downstream from the leading edge a chord-wise distance of less than 50% of a chord length of the airfoil on the pressure side surface.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.

A serial axial fan includes a first axial fan, a second axial fan, and a rectifying portion. The second axial fan is on one side in the axial direction with respect to the first axial fan and is connected in series to the first axial fan with the rectifying portion interposed therebetween. The rectifying portion includes a chassis with a cylindrical shape surrounding the central axis, a rectifying blade portion extending to a radially inner side from a radially inner surface of the chassis, and an air feeding space on the radially inner side of the rectifying blade portion. The rectifying blade portion extends at least in the axial direction and is inclined relative to another side in the circumferential direction from another side in the axial direction toward the one side in the axial direction.

An air circulator includes a blower unit that is provided with an airflow opening on a front side of the blower unit. A grill is provided in the airflow opening, and is provided with airflow guide blades in a spiral manner. The air circulator also includes a controller that achieves a rhythm air in which weak wind and strong wind are switched over by controlling a rotational speed of a motor of the blower unit. The grill is provided with plural airflow guide blades in a spiral manner. Inner end portions of the airflow guide blades closer to the center of the spiral of the airflow guide blades are protruded from outer end portions if the airflow guide blades in an airflow direction.

A turbofan engine is provided. The turbofan engine includes a fan having a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a radius and a longitudinal axis; and an inlet pre-swirl vane located upstream of the plurality of fan blades and defining a chord, the inlet pre-swirl vane coupled to the nacelle, wherein the inlet pre-swirl vane is angled at a first angle with respect to the radius of the nacelle, and wherein the chord of the inlet pre-swirl vane is angled at a second angle with respect to the longitudinal axis of the nacelle.

A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.

The air moving device includes a rotor and a stator. The quantity of the rotor blades is not less than 5 and not greater than 12. The average blade angle of rotor blades is not less than 45 degrees and is not greater than 64 degrees. The ratio of the hub diameter to the rotor diameter is not less than 0.4 and not greater than 0.79. The quantity of the stator blades is not less than 6 and not greater than 23. The average blade angle of stator blades is not less than 45 degrees and not greater than 70 degrees. The ratio of the total thickness of the air moving device to the rotor diameter is not less than 0.76 and not greater than 1.7. The ratio of the stator axial thickness to the rotor axial thickness is not less than 0.28 and not greater than 0.65.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

An air circulator includes a blower unit that is provided with an airflow opening on a front side of the blower unit. A grill is provided in the airflow opening, and is provided with airflow guide blades in a spiral manner Each of the airflow guide blades is convex toward an airflow direction between its inner end portion and its outer end portion to form the grill three-dimensionally. The grill further includes a circular ring that intersects with the airflow guide blades.