An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

A blower including a housing at least partially defining a chamber, a motor including a drive shaft defining a rotational axis, an impeller driven by the motor to generate an air flow in the chamber, and a coupler operably connected between the drive shaft and the impeller. The chamber may have an axial height which increases from a position proximate a back plate to a position spaced from the back plate. The chamber may have a non-circular cross-section proximate a chamber outlet, and a tube assembly in fluid communication with the chamber may have a tube inlet with a non-circular cross-section. The impeller may define two separate airflow paths each having an inlet and an outlet.

The component of the turbomachine comprises a body of the component, a bond layer covering a base surface of the body, and a top layer covering the bond layer and made of abradable ceramic material. The base surface of the component has patterned protrusions and, through two covering steps used for forming the bond layer and the top layer, also the top surface of the component has patterned protrusions. The pattern protrusions of the base surface may be obtained in different ways, for example casting, milling, grinding, electric discharge machining or additive manufacturing. The patterned protrusions belong to an abradable seal of the turbomachine, and may be shaped and sized to maintain specified clearances and to reduce flow of a working fluid within turbomachinery equipment and/or it's components.

Disclosed is a compressor including: a rotatably-mounted rotor disk including a slot in an outer circumference thereof; and a blade including a root member connected to fix to the slot of the rotor disk, an airfoil with a leading edge facing introduced air and a trailing edge, and a platform formed in between the root member and the airfoil to stably support the airfoil over the rotor disk, the blade further including first and second bumps being respectively formed on each end side of the platform to face the introduced air.

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 disclosed system includes an impeller for a ventilator. The impeller includes a hub or hub ring configured to rotate about an axis and a plurality of vanes attached to the hub or hub ring. Each vane of the impeller has a leading edge facing a pressure side of the ventilator along the axis, and a trailing edge facing a suction side of the ventilator along the axis. The leading edge of each vane has a corrugated shape characterized by a first wavelength and the trailing edge has a corrugated shape characterized by a second wavelength, with the first wavelength being longer than the second wavelength. The impeller may further include injection molded plastic, die-cast aluminum, stamped sheet metal, or laser cut sheet metal that is embossed. The impeller may further be assembled from separately manufactured pieces that are secured to one another using joining, welding, or by interlocking tabs.

A method of making a master cure tool for applying a texture to an aerodynamic surface includes the steps of: providing a foil which is metallic and has a textured surface; applying the foil to a forming surface of a rigid forming tool which is compound curved, and plastically deforming the foil to conform to the forming surface, so as to define a foil layer; annealing the foil layer using heat or a combination of heat and pressure; and bonding the foil layer to a support body, thereby defining the master cure tool.

A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.