Abstract: A submersible well pump assembly includes a pump driven by a motor. The pump has a number of stages, each stage including a diffuser having an annular diffuser inlet with an annular outer wall. Diffuser passages lead downstream and inward from the diffuser inlet. An impeller has a circumferential outer edge adjacent the outer wall of the diffuser inlet. Notches are formed in the circumferential outer edge, defining a serrated configuration.

Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.

Abstract: A vacuum pump includes a housing with an inlet port, a rotor part in the housing, the rotor part including a recess part facing the inlet port, and a plurality of rotating blades, a rotating shaft overlapping the recess part, and a capping part overlapping the rotating shaft and covering the recess part.

Abstract: A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. The skin cavity may be defined by a hot-side surface and a cool-side surface with the hot-side surface between the cool-side surface and the external surface. A flat portion may be disposed on the hot-side surface and may, for example, define a wall-thickness check region. A protrusion may be disposed on the cool-side surface opposite the flat portion on the hot-side surface. The hot-side surface and the cool-side surface may tend to increase a heat transfer coefficient along the flat portion of the hot-side surface, which may also define a wall thickness check region.

Abstract: A bearing sleeve assembly includes a rigid inner element having a cylindrical inner diameter bore and an outer surface that is non-cylindrical. Also included is a rigid outer element spaced radially outwardly from the rigid inner element, the rigid outer element comprising a cylindrical member with a uniform cross-section that forms a ring with an inner-diameter surface and an outer-diameter surface, the outer element's inner-diameter surface and the non-cylindrical outer surface of the inner element defining a non-uniform annulus therebetween. Further included is an elastomeric core disposed between the rigid inner element and the rigid outer element within the non-uniform annulus, the elastomeric core having a first thickness at a first location and a second thickness at a second location, the first thickness being greater than the second thickness.

Abstract: A bi-directional contra-rotating circular rail bearing Y-shaped compound blade fluid energy collection multi-unit power generating windmill, the windmill comprising: a windmill remote automatic control system (1); a Y-shaped compound blade (2) from a combining of single blades; a circular rail windmill body (3) bearing the Y-shaped compound blade (2); a circular windmill rail (4) bearing the circular rail windmill body (3) for operation; a circular rail connection cable pulling vehicle (5) running on the circular cable pulling vehicle rail to pull the circular rail windmill using a stay cable (209); a hydraulic energy collection multi-unit power generating system (6) or pneumatic energy collection multi-unit power generating system (7); the Y-shaped compound blade (2) is born by three circles of the circular rail windmill body (3) arranged equidistant thereon; the circular rail windmill body (3) has six circles.

Abstract: A turbine blade airfoil including cooling circuits is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil, where the first pressure side cavity is configured to receive a coolant. The airfoil may also include at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, a trailing edge positioned between the pressure and a suction side, and a trailing edge cooling system positioned adjacent the trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may be configured to receive a portion of the coolant from the first pressure side cavity.

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.