An impeller including a hub surface and a plurality of blades protruding from the hub surface. Each of the plurality of blades has a pressure surface located on a leading side of the rotation direction and a suction surface located on a trailing side of the rotation direction. Each of the plurality of blades is provided with a plurality of first concave surfaces at a boundary between the pressure surface and the hub surface, and one second concave surface at a boundary between the suction surface and the hub surface. At least two different first concave surfaces having different concave radii in cross section are included in the plurality of first concave surfaces. A first concave radius that is the largest among the different concave radii is identical to a second concave radius that is a concave radius of the second concave surface in cross section.

An impeller includes a base plate, a hub protruding from the base plate, and a number of blades connected to the base plate and extending from a lateral surface of the hub toward an edge of the base plate. Opposite sides of each of the blades are a working surface and a non-working surface. The base plate is divided into a plurality of sub-plates by the plurality of blades. Each of the sub-plates is located between two adjacent blades and connected to the non-working surface of one of the two adjacent blades and the working surface of the other one of the two adjacent blades. A distance from an edge of each of the sub-plates to a center of rotation of the impeller is varied.

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

A seal assembly includes a rotating seal runner having an outer radial surface, and one or more rotationally stationary seal rings located radially outboard of the seal runner. Each seal ring has an inner radial surface, with the inner radial surface and the outer radial surface defining a sealing interface therebetween. An axially extending shape of the inner radial surface is selected utilizing a predicted shape of the outer radial surface at a selected operating condition of the seal assembly.

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 turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow. A platform extends laterally outward relative to the airfoil body and terminates at at least one slash face. A cooling circuit is within the platform and is in fluid communication with a source of the coolant flow. Cooling passage(s) are in the platform and in fluid communication with the cooling circuit. The cooling passage(s) extend in a non-linear configuration from the cooling circuit to exit through the at least one slash face of the platform, providing improved cooling compared to linear cooling passages.

A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity, and establishes at least one surface depression along an external surface contour. The external wall includes at least one cooling passage having an outlet port established along the at least one surface depression. A method of fabricating a gas turbine engine component is also disclosed.

A rotor for an aircraft engine, has: a hub extending circumferentially about a central axis, the hub having a bore, a gaspath-facing surface located radially outwardly of the bore relative to the central axis, a first face extending from the bore to the gaspath-facing surface, and a second face opposite the first face and extending from the bore to the gaspath-facing surface; blades circumferentially distributed about the central axis, the blades protruding away from the gaspath-facing surface of the hub; and a crack mitigator located on the first face, the crack mitigator extending circumferentially relative to the central axis, the crack mitigator extending axially from a baseline surface of the first face.

Provided is a water pump which may be easily manufactured and a manufacturing method thereof, the water pump including: a motor housing having a concave container shape; a lower casing including a first side wall protruding downward for a lower end of the first side wall to be in contact with an upper end of the motor housing; and an upper casing fitted to the outside of the lower casing, and including a second side wall protruding downward for a lower end of the second side wall to be in contact with the upper end of the motor housing, wherein the upper end of the motor housing, the lower end of the first side wall, and the lower end of the second side wall are simultaneously fusion-coupled with one another.

A turbine nozzle includes a plurality of blades arranged so as to form a tapered flow passage between each two adjacent blades. A suction surface of each blade includes a curved surface, and a throat of the flow passage is formed between the curved surface of one blade and a trailing edge of the other blade of the two adjacent blades at a throat position. An upstream end of the curved surface is positioned upstream of the throat position, and a downstream end of the curved surface is positioned downstream of the throat position.