Abstract: An exhaust treatment fluid system includes a tank housing for storing an exhaust treatment fluid. A suction tube includes a first end positioned within the housing. A first sensor is positioned within the tank housing for determining at least one of a fluid level and a concentration of the exhaust treatment fluid. A skirt is positioned in the tank to peripherally surround the first sensor.

Abstract: Provided is a lubricant feed mechanism for a turbocharger, the mechanism that can reduce work of an oil pump while preventing an excessive supply of lubricant to a bearing part. The lubricant feed mechanism for a turbocharger, the mechanism of feeding lubricant to a bearing part that rotatably supports a shaft connecting a compressor wheel and a turbine wheel, includes: an oil supply passage that guides the lubricant fed under pressure from the oil pump to the bearing part; and a flow control valve provided to the oil supply passage for adjusting the amount of the lubricant by throttling the flow passage of the lubricant based on a pressure of the lubricant flowing through the oil supply passage.

Abstract: A multi-stage SCR control system including a front reductant dosing device, a front SCR device, a back reductant dosing device, a back SCR device, and a dosing controller. In normal control cycles, a NSR of the front SCR device is controlled below a stoichiometric reaction ratio to decrease system sensitivity to catalyst aging. In a diagnostic cycle, the NSR of the front or the back SCR device is controlled lower than the stoichiometric reaction ratio, and a reductant quality ratio, which is indicative of reductant quality and dosing accuracy, is calculated. In another diagnostic cycle, the NSR is controlled above the stoichiometric reaction ratio, and an average deNOx efficiency is calculated. The reductant quality ratio and the average deNOx efficiency values are further used in SCR feedback control and permanent catalyst damages can also be isolated from temporary catalyst poisons with these values after a thermal recovery event is completed.

Abstract: A novel latch seat for a switching rocker arm assembly used in variable valve actuation (VVA) systems for internal combustion engines. The seat is formed interactively in the assembled switching rocker arm using a novel fixture and press. The press interactively creates a curved dimple of the correct curvature, position and depth while measuring several lash dimensions. Since the latch seat is formed on the assembled rocker arm assembly, the latch seat depth is designed to account for the inaccuracies in the rocker arm assembly parts which create lash. Therefore all of the parts may be made with less precision since the latch seat is sized to compensate for the inaccuracies of all of the parts. The rocker arm assembly parts now may be manufactured to less stringent standards, but result in a rocker arm assembly with same accuracy of rocker arm assemblies manufactured to previous standards.

Abstract: A variable displacement pump includes a housing having a pair of end wall surfaces; an annular outer rotor guide swingably disposed between the pair of end wall surfaces; a cylindrical outer rotor; an inner rotor provided radially inward of the outer rotor and configured to rotate integrally with a drive shaft at a location eccentric relative to the outer rotor; and a plurality of coupling plates coupling the inner rotor and the outer rotor. The outer rotor is rotatably fitted into an outer rotor supporting surface of the outer rotor guide. A space between the inner rotor and the outer rotor is partitioned into a plurality of chambers by the plurality of coupling plates. A concave portion is formed in the outer rotor supporting surface such that the concave portion exists over an entire axial range between the both end surfaces of the outer rotor guide.

Abstract: A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.

Abstract: A bearing housing (1) of an exhaust-gas turbocharger 2, having an oil guide to at least one bearing point (5) in the bearing housing (1). The oil guide is formed by at least one of bores and cutouts in the bearing housing (1). There is formed in the oil guide a siphon (10) which is integrated into the bearing housing (1).

Abstract: An exhaust-gas turbocharger (1) with a compressor wheel (2); with a turbine wheel (3); and with a shaft (4) on which the compressor wheel (2) and the turbine wheel (3) are arranged in a rotationally secured manner. The turbine wheel (3) has a through-opening (5) in which a first end region (6) of the shaft (4) is arranged, and the turbine wheel (3) is braced between an end-side stop (7) connected to the end region (6) and a compressor wheel-side shaft sleeve (8) fixed on the shaft (4).

Abstract: A selective catalytic reduction (SCR) catalyst is disposed in an exhaust gas system of an internal combustion engine. A reductant injector is coupled to the exhaust gas stream at a position upstream of the SCR catalyst, and first and second NOx sensors provide NOx measurements upstream of and downstream of the SCR catalyst, respectively. A system and method is disclosed for operating the system to determine a NOx amount and/or a NH3 slip amount downstream of the SCR catalyst by decoupling NOx-NH3 measurements from the output of the second NOx sensor to provide control of the reductant injection amount.

Abstract: Disclosed is a process for producing a run-in coating (20, 24, 32, 44) on a component of a turbomachine, in particular of a gas turbine. The run-in coating is applied and produced on the component of the turbomachine by a kinetic cold gas compacting process (K3). The invention also encompasses a run-in coating for a static or rotating component of a turbomachine and a static or rotating component of a turbomachine, in particular of a gas turbine, having at least one run-in coating.

Abstract: A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.

Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.

Abstract: A ram air turbine is presented that includes a turbine having a blade and a turbine shaft, a strut removably coupled to the turbine, wherein the strut has a gearbox section and a drive section, a turbine shaft with a bevel gear oriented perpendicularly to the turbine shaft and positioned within the gearbox section of the strut, a driveshaft coupled to the generator and positioned within the drive section of the strut, and a pinion gear that engages with the bevel gear, wherein the pinion gear is secured to the driveshaft by a spanner nut, wherein the pinion gear utilizes a key configured to interact with the keyed joint of the driveshaft. The pinion gear is supported by a pinion bearing that may be press fit onto the pinion gear and by one of the generator bearings.

Abstract: The object of this invention is to simplify the timing system of all types of internal combustion engine. The system eliminates existing conventional timing trains. The hydraulic, mechanical or electrical/electronic direct timing systems that form the subject of the invention offer minimal resistance and minimal transmission. The piston strokes are given directly by the crankshaft by means of a system fixed thereto which via a mechanical or hydraulic or electrical or electronic system transmits the strokes to the cylinder valves. The system can be connected to all types of indirect transmission and has adjusting systems that allow it to be adapted to suit all types of internal combustion engine.

Abstract: The present invention provides a wind turbine having rotating blades, comprising: a base, a rotation shaft, turbine blades, blade ferrules, an upper flange, a generator and a lower flange. The rotation shaft is arranged on the base. The blade ferrules are installed on the rotation shaft. Blade ferrules are applied to fixate between the rotation shaft and the turbine blades. The rotation shaft is connected to the generator. The upper flange is arranged above the generator and the lower flange is arranged under the generator. The disclosed wind turbine may increase utilization efficiency of wind power and is highly advantageous to startup the generator under breeze condition.

Abstract: A novel latch seat for a switching rocker arm assembly used in variable valve actuation (VVA) systems for internal combustion engines. The seat is formed interactively in the assembled switching rocker arm using a novel fixture and press. The press interactively creates a curved dimple of the correct curvature, position and depth while measuring several lash dimensions. Since the latch seat is formed on the assembled rocker arm assembly, the latch seat depth is designed to account for the inaccuracies in the rocker arm assembly parts which create lash. Therefore all of the parts may be made with less precision since the latch seat is sized to compensate for the inaccuracies of all of the parts. The rocker arm assembly parts now may be manufactured to less stringent standards, but result in a rocker arm assembly with same accuracy of rocker arm assemblies manufactured to previous standards.

Abstract: Disclosed is a motor which uses a hydrostatic force to generate a torque which repeats cyclically owing to a displacement of the center of gravity of a cyclic unit. Float bodies (116) are subjected to a buoyant force in a fluid (134), which buoyant force causes an upward movement (146) of the float bodies and drives these into an upper position. The upward movement drives a drive element. The upward movement furthermore causes air to be forced from upper segments (102a, 102d) of a deformable element (100) into lower segments (102b, 102c), and as a result the center of gravity of the cyclic units which comprise the float bodies (116) and the deformable element (100) is raised above an axis of rotation (106). When the float bodies (116) have passed into the upper position thereof, said elevated center of gravity position permits a rotation of the cyclic units into the initial position thereof.

Abstract: A fan assembly is disclosed that includes one or more fan blades, each fan blade having a flexible airfoil wing. A curved, flexible wing is connected to a main spar element located between the upper and lower portions of the curved, flexible wing element. The curved, flexible wing forms the entire upper surface of the wing, the entire leading edge of the wing, and a portion of the lower surface of the wing.

Abstract: A hot-air engine (10) includes a compressor (12), a heating chamber (14), a rotary displacement type working engine (16) and a drive means (22). The compressor (12) has an inlet (12a) and an outlet (12b). The heating chamber (14) has an inlet (14a), in fluid communication with the outlet (12b) of the compressor (12), and an outlet (14b). The working engine (16) has an inlet (16a), in fluid communication with the outlet (14b) of the heating chamber (14), and an output shaft (16a). The drive means (22) connects the working engine (16) to the compressor (12) such that operation of the working engine (16) causes operation of the compressor (12).

Abstract: Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.