Abstract: A bearing housing, or integrated turbocharger housing, with the oil, and optionally air and water galleries, included as as-cast features, thereby avoiding the problems, design limitations and expense associated with conventional post-casting machining. The method of casting preferably uses lost foam casting, or a technique similar to lost foam casting but in which a ceramic shell is formed on the foam form prior to metal casting, but can use any of a variety of casting techniques or a combination of two or more techniques.

Abstract: A ventilator includes an opening formed on a bottom surface, a rectangular frame provided with a flange, a volute provided with a fan motor inside, and a connector connected to an air outlet of the volute. Four side surfaces of the frame excluding the top surface and the bottom surface tilt towards the outer lower side in a direction from the top surface to the bottom surface, and the opening area of the bottom surface is larger than that of the top surface. The ventilator saves packaging and installation costs, and further facilitates installation between the roof and the ceiling.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Abstract: A ceiling fan including a retention system and method of redundantly retaining a ceiling fan can include a ceiling fan motor assembly including a hollow motor shaft at least partially surrounded by a motor housing. A retainer plate is provided at the bottom of the motor housing including an opening. A retainer rod extends through the opening in the retainer plate and secures to the retainer plate. A support cable couples to the retainer rod to suspend the retainer plate from a structure, wherein the retainer plate is configured to redundantly retainer the ceiling fan.

Abstract: Stator vane assembly includes plurality of vanes arranged in circumferential array, radially proximal mounting portion, radially distal mounting portion, and first latching mechanism. Each of plurality of vanes extends radially between radially proximal mounting portion and radially distal mounting portion, with each of plurality of vanes being pivotally mounted between radially proximal mounting portion and radially distal mounting portion. Plurality of vanes is movable between first arrangement allowing gas to flow across vanes, and second arrangement blocking gas flow across vanes. Pivot axis of each of plurality of vanes is offset from the line of aerodynamic center of pressure of vane towards trailing edge of vane, and first latching mechanism holds plurality of vanes in first arrangement. Upon receipt of signal, first latching mechanism releases plurality of vanes so that gas flow through vane assembly causes plurality of vanes to move from first arrangement to second arrangement.

Abstract: A turbine blade including an airfoil (31) extending above a platform (32) and a root (33) extending below the platform, the root of the blade having the form of a radially extending arm (34), being produced from composite material and including at least one cylindrical face (34). The direction of the generatrices which are oriented in the direction of the platform to allow a clamping piece (5) to slide towards the latter on the cylindrical face under the action of centrifugal force. The arm includes, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1). The root (33) is located entirely on the side of the protuberance with respect to the face.

Abstract: A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free tip end. The airfoil section is formed of a metal-based material with a polymeric overcoat on at least one of the leading edge, trailing edge, first side and second side. The airfoil section includes an abrasive tip at the free tip end. The abrasive tip has a composition selected with respect to heat-induced delamination of the polymeric overcoat from frictional heat generated during rubbing of the abrasive tip.

Abstract: An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.

Abstract: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.

Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element, which is arranged in a flow duct, and a leading edge and a trailing edge, which are joined to each other through a pressure side and a suction side, wherein, a new and novel profile section of the blade or vane element is provided.

Abstract: The present invention relates to an intelligent wind turbine generator, which comprises a first blade module, a second blade module, a power generating module, and a control module. The second blade module is disposed at the first blade module. The power generating module is connected with the first and second blade modules. The control module is connected with the power generating module, the first blade module, and the second blade module. The first and second blade modules rotate, driving the power generating module to generate power. The control module detects a voltage value generated by the power generating module and judges if the voltage value is greater or lower than a predetermined value. The control module controls whether the first and second blade modules overlap or not. The intelligent wind turbine generator is able to switch automatically the blade number of the wind turbine generator.

Abstract: An electric propulsion device includes a duct having a cylindrical shape and that includes a stator. A rim includes a rotor rotatable relative to the duct, and a plurality of fins. A bracket supports the duct so as to allow the duct to turn about a turning axis that intersects with the rotation axis of the rim, and a turning actuator that integrally turns the duct and the rim. The turning actuator is fixed to the bracket, and the duct is turnable relative to the bracket.

Abstract: A method of forming an impeller for a torque converter is provided. The method includes providing an impeller shell including a back axial surface for facing away from an interior of the torque converter, providing an impeller hub including an outer circumferential surface and forming a weld joining the impeller shell and the impeller hub. The weld is contiguous with the back axial surface of the impeller shell. The weld is also contiguous with the outer circumferential surface of the impeller hub. The weld includes a root where the impeller shell and the impeller hub meet the weld. The method also includes machining the root. An impeller for a torque converter is also provided.

Abstract: Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system.

Abstract: A system and a method for adjusting an angle of at least one stator vane of a low pressure compressor (LPC) of a two spool gas turbine engine is disclosed. Variable stator vanes are rotatably coupled to a stationary case in one of the stages of the LPC. An actuator is coupled to at least one of the variable stator vanes for imparting rotation of the stator vane about a radius of the case. Various coupling or linkage arrangements may be made so that rotation of one vane results in rotation of the other vanes disposed along the case. The controller includes the stored constraints, the ability to estimate operating condition, and the ability to estimate optimum targets.

Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.

Abstract: Centrifugal pump sealing surfaces are described. A multi-stage centrifugal pump includes an impeller between a first diffuser and a second diffuser, a plurality of sealing surfaces formed by at least one diffuser inlet ring of the first diffuser interspersed between at least two concentric balance rings of the impeller, and at least one annular diffuser exit skirt of the second diffuser interspersed between at least two concentric annular skirts of the impeller. A multi-stage centrifugal pump includes an impeller including a plurality of concentric annular impeller sealing surfaces mated to a plurality of concentric annular diffuser sealing surfaces, the diffuser sealing surfaces extending toward the impeller from a diffuser stacked adjacent to the impeller, wherein the impeller sealing surfaces and the diffuser sealing surfaces interlock to form a plurality of tight clearances and a tortuous leak path for well fluid lifted by the centrifugal pump.

Abstract: What is described is a system for pumping lubricant to a component of a gas turbine engine. The system includes a fan gear coupled to a fan shaft of the gas turbine engine and configured to rotate in a forward direction and in a reverse direction based at least partially on a direction of wind relative to a fan of the gas turbine engine. The system also includes a first pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the forward direction. The system also includes a second pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the reverse direction.

Abstract: A part made of a ceramic material, including a portion forming a base and a portion forming a wall, wherein the base consists of a low-porosity ceramic material and the wall is obtained by powder sintering and includes an envelope and a core, the core being within the envelope, the porosity of the core being higher than that of the base and increasing the further it is from the base.

Abstract: There is proposed a bladed rotor for a turbo-machine, the rotor having a rotational axis and including a hub defining a plurality of circumferentially spaced-apart slots around its periphery. Each slot slideably receives a root portion of a respective rotor blade, the root portion of each blade defining a radially inwardly open retaining groove within which a respective region of a retaining ring locates to retain the blades in said slots. The retaining ring also engages within a plurality of radially inwardly open hub grooves formed around the hub. The retaining ring engages each said hub groove such that a radial gap is defined between the retaining ring and a radially outermost region of each hub groove.