A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.

A centrifugal fan is formed from an impeller installed within a casing. The impeller is formed from two plates that are interconnected by a plurality of blades. A duct extends through each blade. At each of its ends, the duct opens at one of the plates. Air enters the fan from through a central opening formed in one of the plates, moves to a medial zone between the plates, and exits the fan at the medial zone's unwalled periphery. Air also crosses the fan by way of the ducts formed within each blade.

The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (24) extending opposite the pressure-side walls (16) and suction-side walls (14), the outer skin (24) and the wall of the facing blade (12) being separated by an air gap (30), a series of reinforcements (25) formed in the closed wall (22) and leading into the outer skin (24), and a series of through-openings formed in the reinforcements (25), the heights of impact (h) between said through-openings and the pressure-side wall (16) or the facing suction-side wall (14) being greater than the air gap (30).

A compression inner core cowl for a jet engine can have a concave annular section of the core cowl. The concave section can begin within the expanse of an outer fan cowl and extend aft of the fan cowl toward the tail cone, defining an annular bypass section between the fan cowling and the core cowling. The concave geometry of the core cowling reduces the strength of supersonic shock waves generated at the corners of the cowlings adjacent a supersonic airflow stream to increase overall efficiency of the engine.

A thrust reverser for an aircraft includes a jetpipe and a thrust reverser door. The thrust reverser door has an aft end, a forward end, and an interior surface facing radially inward. The interior surface defines a continuous profile with a downstream nozzle portion directly adjacent to the aft end, a concave portion directly adjacent to the downstream nozzle portion, and a convex portion directly adjacent to the forward end and adjacent to the concave portion.

A heat dissipation fan including a hub and a plurality of heat dissipation blades is provided. The heat dissipation blades are arranged around the periphery of the hub. Each of the heat dissipation blades includes a curved surface body and a flow guiding portion. The curved surface body has a pressure bearing surface and a negative pressing surface opposite to the pressure bearing surface. The flow guiding portion is connected to the curved surface body. The flow guiding portion has a concave surface and a convex surface opposite to the concave surface, wherein the concave surface is recessed in the pressure bearing surface and the convex surface protrudes outward from the negative pressing surface.

A damped turbine blade assembly for a gas turbine engine is disclosed. The damped turbine blade assembly includes a damper positioned within a first small slot of a first turbine blade and a second large slot of the second turbine blade. A portion of the damper can slidably mate with the second large slot providing a radial and angular connection between the first turbine blade and second turbine blade while allowing movement in a direction tangent to a radial of a center axis of the gas turbine engine. The tangential movement is resisted by friction between the damper contacting the second large slot and provides friction damping against vibrations felt by the turbine blades during operation of the gas turbine engine. The damper can be shaped and/or pre-stressed to control the normal force component of the friction between the damper and the second large slot.

A jet noise suppressor and an airplane are provided. The jet noise suppressor includes a nozzle with a front end, a back end, an interior surface, and an exterior surface, a plurality of struts, and a plurality of vents. Each strut includes a base and a distal end with the base of each strut coupled to the interior surface of the nozzle, and each vent corresponds to a respective strut and is formed within the interior surface of the nozzle between the front end of the nozzle and the base of the respective strut.

A fan includes a fan frame, an impeller, and at least a supporting member. The fan frame includes a bottom plate and a cover plate spaced from the bottom plate. The bottom plate and the cover plate together define a first accommodating space. The cover plate has an air inlet disposed in an axial direction. A side of the fan frame is provided with at least an air outlet. The impeller is disposed in the first accommodating space and includes a hub and a plurality of blades. A cross-sectional area of the hub increases gradually along a direction from the cover plate to the bottom plate. The blades are disposed around the periphery of the hub. The supporting member is disposed between the bottom plate and the cover plate for supporting the cover plate.

Airfoils, shells, and spars are provided. The airfoils include a shell having a first channel and a first engagement element arranged along the first channel and a spar having a second channel and a second engagement element arranged along the second channel and the spar defines an inner cavity. A connector is configured to be installed between and connect the shell and the spar to allow for thermal growth of the shell relative to the spar. The connector has first and second engageable portions connected by a link. The first engageable portion is configured to engage with the shell and the second engageable portion is configured to engage with the spar. When assembled, an outer cavity is formed between the spar and the shell, and the first and second engagement elements and the first and second engageable portions are configured to define an axial flow path through the outer cavity.