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: 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: 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 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: 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: 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: 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: 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.

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: A shroud supports one of an inner and an outer trunnion on a variable vane. The shroud is provided by a first and a second axial half. Each of the axial halves is provided by a plurality of circumferentially spaced segments. Circumferential edges are defined on each of the plurality of circumferentially spaced segments. Edges between adjacent ones of the circumferentially spaced segments on the first half are circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of the second half, such that no direct leakage path exists across an axial width of the shroud.

Abstract: A housing for a fan or blower, in particular an axial fan, includes a wall ring (2) having an inlet nozzle section (3), an outer diffuser (6) having an inlet flow opening (7) and an outlet flow opening (8), and a holder for an electric motor (9) of the fan. The holder is arranged in an inner space of the housing. The outer diffuser (6) is formed by at least two partial ring sections that are connected to the outer circumferential surface via mechanical connection elements. The holder includes several struts (14) that are fastened to an inner circumferential surface of the outer diffuser (6) by one end, are circumferentially spaced apart, and are fastened in the edge region of the inlet flow opening (7). The struts can be installed by their other end to a motor flange (16) of the motor housing (17) of the electric motor (9).

Abstract: A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.

Abstract: A ventilation assembly having a main housing that can be pre-installed in a wall or ceiling aperture. A fan assembly can be inserted through the aperture and releasably mounted within the main housing. The fan assembly can be removed from the main housing and replaced without removing the main housing from the wall or ceiling. An accessory component can be releasably mounted to the fan assembly either through the aperture when the fan assembly is mounted or prior to installation of the fan assembly.

Abstract: A method of optimizing the power recovered by a wind turbine by reducing the mechanical impact on the structure is disclosed. A first angle of inclination of the blades allowing the recovered power to be optimized is determined. The aerodynamic force produced on the nacelle when the blades are directed with a first angle is determined. A second angle of inclination of the blades allowing obtaining an aerodynamic force setpoint value is then determined by inverting the aerodynamic force model and using a wind velocity measurement, a rotor velocity measurement and the aerodynamic force setpoint value. Finally, the blades are directed to the second angle.

Abstract: A compressor control device includes an inlet guide vane opening degree control unit configured to control an opening degree of an inlet guide vane. The inlet guide vane opening degree control unit includes an inlet guide vane opening degree command value calculation unit configured to calculate an inlet guide vane opening degree command value based on an outlet pressure detection value and a plurality of inlet guide vane opening degree correction units each configured to correct the inlet guide vane opening degree command value based on the post-merger pressure detection value and a corresponding inlet flow rate detection value for each of a plurality of upstream-most compressor bodies.

Abstract: A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform.