Abstract: A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.

Abstract: A turbine blade tip, turbine blade and method where improved cooling is made possible by an improved cooling structure with cooling air holes inside a depression in a blade tip and a special arrangement of multiple cooling air holes which are supplied by a single cooling air channel inside a wall.

Abstract: A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.

Abstract: Provided is a wind power generation transmission system. A first sun gear is a hollow gear. The first sun gear includes a first end surface and a second end surface opposite to the first end surface. A second planetary carrier includes a third connection end. An outer circumferential surface of the third connection end is provided with external splines. An inner circumferential surface of the first sun gear is provided with internal splines. The third connection end of the second planetary carrier extends from the second end surface to the first end surface and is disposed in the first sun gear so that the external splines of the third connection end are connected to the internal splines of the first sun gear.

Abstract: An air supply device for an electrically heated catalyst is proposed. The device includes an electronic supercharger fluidly connected to an intake manifold, an intake valve fluidly connected to the electronic supercharger, an exhaust valve fluidly connected to an exhaust manifold of the engine, an electrically heated catalyst fluidly connected to the exhaust manifold and positioned in a front end of a catalyst part, and a controller configured to control driving of the electronic supercharger and an opening degree of each of the intake valve and the exhaust valve. The controller controls the electronic supercharger based on a door opening condition in a cold operation and switches the intake valve to an advance state and the exhaust valve to a retard state, thus heating the electrically heated catalyst.

Abstract: A turbofan gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan section. A compressor section includes a low pressure compressor section and a high pressure compressor section. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section, and greater than 40. The pressure ratio across the high pressure compressor section is between 7 and 15, and the pressure ratio across the low pressure compressor section is between 4 and 8.

Abstract: A centrifugal compressor includes a first stage and a second stage. At least one of the first stage and the second stage includes an impeller and a shroud spaced from the impeller and configured to guide a fluid flow through the impeller. The shroud is selectively moveable between an engaged position and a disengaged position.

Abstract: A variable capacity turbocharger includes a nozzle flow path which allows a gas to pass from a scroll flow path toward a turbine impeller, a shroud side ring and a hub side ring which face each other in a rotation axis direction of the turbine impeller and form a nozzle flow path therebetween, a bearing hole which is provided in the shroud side ring, a bearing hole which is provided in the hub side ring, and a nozzle vane which is disposed in the nozzle flow path and is supported by both bearing holes. A center axis line of the bearing hole is located on the inside in a radial direction in relation to a center axis line of the bearing hole at a room temperature, and the center axis line is located on the outside in the radial direction in relation to the center axis line during operation.

Abstract: The invention relates to a housing (1) for a fluid machine, in particular for a radial fan (2), comprising at least one housing part (3), wherein the housing part (3) has at least one inlet opening (7), wherein the housing part (3) can at least partially delimit a fluid chamber (8) for receiving at least one fan wheel (9), and wherein the inlet opening (7), at least in part, has a curved inlet surface (11).

Abstract: A range hood, includes a fan system (2), the fan system (2) having a volute (21) and an impeller (22); the volute (21) includes a front cover (211), a rear cover (212) and an annular wall (213); the annular wall (213) has a volute tongue (214); the front cover (211) has an air inlet (215), the air inlet (215) faces downward to make the range hood to be a horizontal range hood; the volute tongue (214) is gradually inclined from the rear cover (212) to the front cover (211) in a direction opposite to the rotation direction of the impeller (22).

Abstract: A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

Abstract: An intake air circuit is structured to transmit intake air from a turbocharger compressor to an intake manifold of an engine. A charge air cooler (“CAC”), a bypass line, and a bypass heater are each positioned along the intake air circuit in parallel with each other. A first control valve is structured to controllably divert the intake air around the CAC. A second control valve is structured to controllably divert the intake air around at least one of the bypass line and the bypass heater. A controller operatively coupled to each of the engine, and the first and second control valves is structured to control each of the first and second control valves to cause the intake air to flow along a determined desired flow path based on each of measured ambient temperature and measured engine load.

Abstract: A reed valve includes a first valve body portion that includes one or more inlet apertures fluidly coupled to a tapered second valve body portion that includes one or more outlet apertures. The reed valve includes at least one sealing surface disposed proximate the one or more outlet apertures and at least one petal continuously, reversibly, displaceable between an OPEN position permitting forward flow through the reed valve when a fluid pressure proximate the at least one inlet aperture exceeds a fluid pressure proximate the at least one outlet aperture and a CLOSED position preventing reverse flow through the reed valve when a fluid pressure proximate the at least one outlet aperture exceeds a fluid pressure proximate the at least one inlet aperture. The reed valve may be installed in an airbox assembly used with a turbocharged engine to reduce the occurrence of turbo-lag on acceleration.

Abstract: This compressed air generation system (12) for an automotive vehicle (V) comprises: —a turbocompressor (4) feeding an internal combustion engine (2) of the automotive vehicle (V) with compressed air, —an air compressor (8), —at least one compressed air tank (10) connected to an outlet pipe (82) of the air compressor (8), the air compressor (8) comprising an inlet pipe (80) fed with compressed air from the turbocompressor (4). The compressed air generation system (12) comprises a pressure regulator (14) placed downstream the turbocompressor (4) and upstream the air compressor (8) and which limits the pressure (P8) of the compressed air fed from the turbocompressor (4) to the air compressor (8) to a first threshold (T1).

Abstract: A turbine includes: a turbine blade wheel housed in a housing unit; two turbine scroll flow paths wound radially outward with respect to the turbine blade wheel and connected at positions different from each other in a circumferential direction in an outer circumferential portion of the housing unit; and two scroll outlets each communicating one of the two turbine scroll flow paths with the housing unit, the two scroll outlets formed along the circumferential direction, at least one of the two scroll outlets having a height distribution in which a height in an axial direction is lower than a surrounding height at at least one of an upstream end or a downstream end.

Abstract: A pump unit includes a rough-vacuum pump and a Roots vacuum pump connected in series and upstream of the rough-vacuum pump in the direction of flow of the pumped gases. The Roots vacuum pump has three pumping stages in which the rotors are designed to be driven simultaneously in rotation by a motor of the Roots vacuum pump. A ratio of the flow rate generated by the first pumping stage of the rough-vacuum pump in the direction of flow of the pumped gases over the flow rate generated by the last pumping stage of the rough-vacuum pump is less than or equal to four.

Abstract: Systems and methods for a heat engine system are described. In one embodiment, a system comprises a heat engine compressor, a heat exchanger, and a heat engine expander. The system comprises a partial state condenser in fluid communication with the heat engine expander. The partial state condenser includes a sense reservoir to hold the working fluid, a reservoir sensor to sense an electrical property of the working fluid, and a reservoir valve. The reservoir valve is in fluid communication with the sense reservoir, the heat engine compressor, and a heat engine condenser. The system comprises a processor to execute instructions to determine a specific energy of working fluid based on the electrical property of the working fluid and control the reservoir valve based on the specific energy to maintain a two-phase saturated state point within the partial state condenser based on the electrical property.

Abstract: A pump includes a pump housing including an inlet for the fluid on a low-pressure side, an outlet for the fluid on a high-pressure side, a circumferential wall facing faces axially away from the delivery chamber and on which the outlet emerges; a spring structure arranged on the outer end face of the end wall; a delivery member movable within the delivery chamber for delivering the fluid from the low-pressure side to the high-pressure side; and a securing device for axial securing the pump housing. The securing device includes a female holding element having an axially extending cavity and a male holding element in a joining engagement, exposable to an axial tensile load, with the female holding element in the cavity. The spring structure and/or the end wall is/are held on the pump housing by one of the holding elements by the joining engagement.

Abstract: A method of optimizing probe placement in a turbomachine is disclosed which includes establishing a design matrix A of size m×(2N+1) utilized in developing flow properties around an annulus of a turbomachine, where m represents the number of datapoints at different circumferential locations around the annulus, and N represents dominant wavelets generated by upstream and downstream stators and blade row interactions formed around an annulus, wherein m is greater or equal to 2N+1, and optimizing probe positioning by iteratively modifying probe positions placed around the annulus and for each iteration determining a condition number of the design matrix A for each set of probe positions until a predetermined threshold is achieved for the condition number representing an optimal probe layout.

Abstract: Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor coupled to the rotating component, the rotating component having a plurality of position markers distributed about a surface thereof, the position markers having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.