Abstract: A support device supports an inner member of a fixed body including the inner member and an outer member, the inner member being arranged around a rotating body and divided into upper and lower sections and the outer member being arranged in at least a part around the inner member and divided into upper and lower sections.

Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Abstract: A method of correcting surge control parameters that includes providing a dynamic compressor having a compressor, driver, surge valve, and control system. The control system establishes surge control parameters such as surge detection lines, surge limit lines, and then detects the onset of a surge in the dynamic compressor. When the surge is detected the control system measures variables of the dynamic compressor such as fluid pressure, fluid speed, power, speed and valve position and based on these variables the control system automatically corrects the surge control parameters based on these variables at the time of the onset of the surge is detected. Advisory information is provided by control system to user for corrective actions to prevent surge.

Abstract: A convergent-divergent nozzle arranged to convey fluid from an upstream zone to a downstream zone via a throat aperture, wherein the nozzle includes an assembly movable to vary the size of the throat aperture of the nozzle, thereby regulating the flow of fluid to the downstream zone.

Abstract: A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.

Abstract: An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.

Abstract: A gas turbine engine includes a turbine section having static turbine vane rings and turbine wheel assemblies. The vane rings are arranged to direct combustion products toward blades included in the turbine wheel assemblies to cause the turbine wheel assemblies to rotate.

Abstract: A centrifugal fan includes: a housing; an impeller which is mounted in the housing; a hub which is provided in the impeller and is rotated by a driving force of a motor; and a plurality of blades which radially extend at the hub. Each of the plurality of blades is formed to have a shape curved from a leading edge to a trailing edge in a rotational direction of the impeller in each of the plurality of blades. A farthest point from a plane connecting the leading edge and the trailing edge is defined as a peak portion. The peak portion is placed closer to the leading edge than the trailing edge.

Abstract: A wind generator system with a plurality of lightweight, surface area adjustable airfoil/sail blades. Each blade is triangular or wedge shape with a narrow inner edge and a wide outer edge. Each blade includes an inner frame connected to a rigid mast that extends radially from a hub assembly. Each blade includes a curved outer skin layer that extends over the inner frame and configured into air foil shape with a large curved leading edge and a thin trailing edge. The outer skin layer is secured along its leading edge and removeably attached along its trailing edge to the inner frame. Advertising is printed on the outer skin of at least one blade that is visible. Coupled to the outer skin layer is a first linear actuator that when activated, causes the outer skin layer to fold or unfold thereby changing the blade's surface area. The internal frame may include a second linear actuator and a telescopic mast over which the blade slides to increase or decrease the sweep area of the blades.

Abstract: A vacuum pump system for evacuating at least five volumes comprising a turbomolecular pump and a forevacuum pump arranged to pump an output of the turbomolecular pump arrangement to atmosphere. The turbomolecular pump has at least five pumping stages separated by rotor blades. Not more than three pumping stages have pumping speeds in excess of ? of the highest pumping speed when under vacuum and/or a pumping port cross section in excess of ? of the highest pumping port cross section, and at least two pumping stages have pumping speeds less than ¼ of the highest pumping speed when under vacuum and/or a pumping port cross section of less than ¼ of the biggest pumping port cross section. The ratio of pressures between the pumping stage with the highest pressure and the pumping stage with the lowest pressure is at least 100000:1 when under vacuum.

Abstract: A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.

Abstract: A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

Abstract: In some embodiments, an airfoil comprises a proximal end; a distal end opposite said proximal end; a distal portion extending adjacent said distal end; an edge extending between said proximal end and said distal end; and a surface extending between said proximal end and said distal end, said edge and said surface defining a sweep and a cahedral through said distal portion, wherein the distal portion extends over an acoustically active portion of the airfoil.

Abstract: A fan frame body with bypass structure and a fan thereof. The fan includes a first fan, a second fan and a bypass structure. The second fan has a second frame body correspondingly serially connected with a first frame body of the first fan, whereby a first flow way of the first frame body communicates with a second flow way of the second frame body. The bypass structure is disposed in the first flow way or the second flow way. The bypass structure defines a bypass flow way on a circumference of the first flow way or the second flow way. By means of the bypass structure, without increasing the size of the fan and without increasing the consumed power of the fan, the air volume of the fan can be enhanced.

Abstract: A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion with a plurality of fuel outlets arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one outlet arranged to supply fuel to the element.

Abstract: Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load.

Abstract: A method of manufacturing an aerofoil blade includes the steps of providing: an aerofoil sub-assembly having a pair of aerofoil skins, wherein at least one of the skins is formed to have on its outer face an outer primary relief feature formed proud of the adjacent region of the outer face and an outer secondary relief feature projecting from the outer primary relief feature; arranging the aerofoil sub-assembly in a cavity die mould; and performing a hot forming process to form an internal cavity between the respective aerofoil skins by inflating the sub-assembly to conform the outer faces of the respective skins to the cavity die mould, whereby in conforming the respective outer faces of the skins to the cavity die mould, the outer primary and secondary relief features are transferred to the inner face of the respective skin to form respectively inner primary and secondary relief features.

Abstract: The invention provides an improved propeller blade design by modifying a classic propeller blade design by changing the twist distribution across the propeller blade(s). This is accomplished by increasing the twist of each propeller blade on the inboard portion of the blade compared to a classic propeller design. At a break point, the twist provided across the propeller blade from the break point to the tip of the blade decreases so that the attack angle at the tip of the propeller blade is less than that of a classic propeller blade design.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.