Abstract: A system includes an exhaust collector tunnel (32) configured to mount inside an exhaust collector (30) of a gas turbine (12). The exhaust collector tunnel (32) has a tunnel wall (33) configured to extend around a turbine shaft (17, 19) of the gas turbine (12). The tunnel wall (33) has a variable diameter (98) along at least a portion of a length of the exhaust collector tunnel (32).

Abstract: A turbocharger includes a compressor assembly having a compressor housing defining a ported shroud and a switchable trim compressor. The switchable trim compressor is moveable from an open trim position to a closed trim position, with the closed trim position minimizing a diameter of the air inlet opening and blocking air flow through the ported shroud. The positioning of the switchable trim compressor in the open position increases the diameter of the air inlet opening and allows a recirculation air flow through the ported shroud from an interior of the compressor assembly to a position upstream of the switchable trim compressor at a position near the air inlet opening.

Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and a airfoil section that extends between the first and second platforms. The airfoil section has a trailing edge, a leading edge, a pressure side, and a suction side. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Each radial flange extends continuously and includes a first leg portion that extends adjacent the trailing edge, a second leg portion that extends from the first leg portion and curves around the suction side, and a third leg portion that extends from the second leg portion toward the forward side.

Abstract: A turbine vane is provided.

Abstract: A shaft assembly for use with a turbine engine includes a shaft and a magnetic mode control unit. The shaft extends along an axis and is configured to rotate about the axis. The magnetic mode control unit is configured to control deflection of the shaft as the shaft rotates about the axis.

Abstract: The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.

Abstract: An exhaust gas conduction system for a gasoline engine comprises an exhaust gas line and an intake line which can be connected to an intake manifold, a charge air compressor arranged in the intake line, and a turbine arranged in the exhaust gas line. The exhaust gas line has at least one bypass line with a bypass throttle valve. At least one exhaust gas recirculation line with an EGR throttle valve is provided. At least one particle filter is arranged in the bypass line and an exhaust gas valve is provided in the exhaust gas line.

Abstract: In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.

Abstract: A seal system includes a ceramic component, a metallic component, a coating system. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The coating system includes a silicon-containing layer on the surface region of the ceramic component and barrier layer on the silicon-containing layer. The silicon containing layer has a surface in contact with the barrier layer and the barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer serves to limit interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer includes at least one of mullite, zircon, or hafnon.

Abstract: Operating coal fired energy systems. A method of operating a coal fired energy system comprises operating a coal fired steam generator comprising a coal feed system and a main air feed system to provide a coal-air mixture as a heating source for a boiler for generating steam. The method includes operating an auxiliary air compression system comprising a fueled engine coupled to a compressor for providing an auxiliary supply of compressed air to a soot blower of the coal-fired steam generator. The method comprises injecting the auxiliary supply of compressed air along walls of the boiler to remove soot and ash buildup from the boiler.

Abstract: Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Abstract: The invention relates to an exhaust gas turbocharger having a fluid dynamic bearing having a rotor (10) and a counter-bearing part (50) assigned to the rotor (10), wherein a rotor bearing surface of the rotor (10) and a counterface of the counter-bearing part (50) face each other, to form a fluid dynamic bearing, wherein the rotor bearing surface and/or the counterface form(s) a continuous bearing contour when cut longitudinally and through the axis of rotation (R) in sectional view, which bearing contour(s) are formed of at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to generate fluid dynamic load capacities in both the radial and the axial directions, wherein the bearing surface of the rotor (10) is formed by a rotor part (40), which is connected to a rotor shaft (11) and is secured on the rotor shaft (11), and wherein the rotor part (40) is supported relative to the rotor shaft (11) in the area of a support section (14) of the rotor shaft (11).

Abstract: The gas turbine generator includes: a first gas turbine element 2; a second gas turbine element 3; a single combustor 4 connected to the gas turbine elements 2 and 3; a first supply pipe 51 that connects the first compressor 21 to the combustor 4; a second supply pipe 52 that connects the second compressor 31 to the combustor 4; a first discharge pipe 53 that connects the combustor 4 to the first turbine 22; a second discharge pipe 54 that connects the combustor 4 to the second turbine 32; and a flywheel 7 that is connected to at least one of the first rotation shaft 23 and the second rotation shaft 33 and absorbs a torque fluctuation generated in the connected gas turbine element.

Abstract: A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.

Abstract: The wave generator for a rope-controlled hydraulic cylinder in the present invention includes a Wave Energy Harvest and Conversion system (WEHCS), a rope control device and a gravity anchor. The rope control device includes two members which are controllable in relative motion, i.e., frame and an elongated member. When the frame is located above the elongated member, the top end of the frame serves as a connection point with the WEHCS, and the bottom end of the elongated member serves as a collection point with the gravity anchor; however, when the frame is located below the elongated member, the frame serves as a connection point with the gravity anchor, and the top end of the elongated member serves as, a connection point with the WEHCS. The wave generator is applicable for large waves and adapted to tidal changes, as well as effective in rope-retrieving.

Abstract: A steam turbine includes a rotor that rotates about an axis, a casing that covers the rotor from an outer side in a radial direction with respect to the axis, and a cover disposed outside the casing to form a hollow path portion between an outer peripheral surface of the casing and the cover, in which the cover is connected to a negative pressure source configured to put the path portion into a vacuum state, and the path portion is a space isolated from a space inside the casing.

Abstract: A nonlinear control design technique capitalizes on a wave energy converter comprising a shaped buoy having a variable geometry wave energy. For example, the shaped buoy can have an hourglass (HG) geometry having a variable cone or steepness angle. The HG buoy is assumed to operate in the heave motion of the wave. The unique interaction between the HG buoy and the wave creates a nonlinear cubic storage effect that produces actual energy storage or reactive power during operation. A multi-frequency Bretschneider spectrum wave excitation input was simulated for the HG design both with constant and varying steepness angle profiles which demonstrated further increased power generation with changing sea states for the variable design.

Abstract: An adjustable multi-functional bottom-hinged flap-type wave energy utilization device includes at least three wave energy conversion devices arranged in parallel and with adjustable spacing. Each wave energy conversion device includes a wave energy conversion component, a direction adjustment component for adjusting a wave-facing direction of the wave energy conversion component, and a height adjustment component for adjusting a height of the wave energy conversion component. The wave energy conversion component includes a mounting base plate, a transmission shaft arranged on the mounting base plate, a wave energy flap that can drive the transmission shaft to rotate, a generator connected to the transmission shaft, a hydraulic oil cylinder positioned on a back surface of the flap for pushing the flap to reset, and a wave monitor arranged on the mounting base plate for monitoring a draught and a wave direction angle of the flap.

Abstract: An air turbine starter for starting an engine includes a starter housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet. A turbine section is located within the starter housing and includes a turbine member having a central disk and a set of airfoils spaced circumferentially about the central disk, as well as a sealing structure located within the starter housing.

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.