Abstract: A rotor blade for a turbomachine, in particular in an aircraft engine, with a cooling arrangement for cooling a surface inside the rotor blade by means of a cooling medium, in particular cooling air. The rotor blade having an impingement cooling device with a plurality of impingement cooling openings for deflecting the cooling medium flowing in the interior of the impingement cooling device onto the surface that is to be cooled by means of impingement cooling inside the rotor blade and that is located outside of the impingement cooling device, so that the surface can be cooled by means of an impingement cooling through a cooling medium than exits from the impingement cooling openings, wherein the impingement cooling device is movably mounted with respect to the rotor blade.

Abstract: A method for operating an internal combustion engine for a motor vehicle including receiving measurement signals of a cylinder pressure sensor and determining cylinder pressure fluctuations as a function of the received measurement signals of the cylinder pressure sensor. The method also includes increasing an exhaust gas recirculation rate of the internal combustion engine as a function of the determined cylinder pressure fluctuations until a predefined limiting value of the cylinder pressure fluctuations is reached. In addition, the method includes determining an actual value of the exhaust gas recirculation rate if the predefined limiting value of the cylinder pressure fluctuations is reached, and storing the determined actual value as a setpoint value for the exhaust gas recirculation rate of the internal combustion engine.

Abstract: In a fuel tank, a pressure regulator is placed at an outside of a sub-tank and regulates a pressure of fuel of a pressure-regulation path, which is discharged from a fuel pump and is fed toward an outside of the fuel tank. A fuel recovery passage portion recovers excess fuel, which becomes excess at the pressure-regulation path, to the sub-tank. The sub-tank has an opening at a location that is higher than the suction filter. The fuel recovery passage portion is inserted from the outside of the sub-tank into the inside of the sub-tank through the opening while a gap is formed between the fuel recovery passage portion and the opening, so that the fuel recovery passage portion has an excess fuel outlet that discharges the excess fuel at a location that is on an inner side of the opening where an inside of the sub-tank is placed.

Abstract: An assembly is provided for a gas turbine engine. This assemble includes a stationary structure configured with a first side, a second side and a bore that extends through the stationary structure between the first side and the second side. The assembly also includes a fluid transfer tube extending within the bore and forming a plenum between a sidewall of the fluid transfer tube and the stationary structure. The fluid transfer tube is configured with a first end at the first side, a second end at the second side, a flowpath and an aperture. The flowpath is at least partially formed by the sidewall and extends through the fluid transfer tube between the first end and the second end. The aperture fluidly couples the flowpath with the plenum.

Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.

Abstract: An airfoil includes an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge. The airfoil body defines a plurality of first skin core passages disposed proximate the suction side and radially extend from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end.

Abstract: A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor. Each of the thin plates has a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate.

Abstract: A control device for controlling a fuel injection in an internal combustion engine provided with a fuel injection valve has a driving portion supplying an electric power to a terminal of the fuel injection valve so as to drive the fuel injection valve to be opened; a current detecting portion detecting a drive current flowing through the fuel injection valve when the fuel injection valve is driven to be opened; a voltage detecting portion detecting a terminal voltage of the terminal of the fuel injection valve; a correction portion correcting the electric power supplied by the driving portion so that an actual value of the drive current detected by the current detecting portion agrees with a target value; a valve close detecting portion detecting a valve closing timing of the fuel injection valve based on the terminal voltage detected by the voltage detecting portion in a condition where the electric power supplied by the driving portion is corrected by the correction portion.

Abstract: The invention relates to a device for metering two different liquid or gaseous fuels, comprising a nozzle element (4) in which a first pressure chamber (6) that can be filled with a first fuel is formed, wherein an outer nozzle needle (10) is received in the pressure chamber in a longitudinally movable manner. The outer nozzle needle (10) is equipped with a second pressure chamber (12) which can be filled with a second fuel and in which an inner nozzle needle (15) is arranged in a longitudinally movable manner, said inner nozzle needle interacting with an inner nozzle seal (16) formed in the outer nozzle needle (10) in older to open and close at least one inner injection opening (17). Furthermore, at least one outer injection opening (13) is provided which can be connected to the first pressure chamber (6), the at least one outer injection opening (13) being formed in the outer nozzle needle (10).

Abstract: Systems are provided for aligning and assembling an exhaust gas recirculation (EGR) assembly with an engine intake housing. In one example, an intake system may include an EGR port housing for coupling the EGR assembly on an intake housing. The EGR port housing may include one or more alignment tabs on at least one side of the EGR port housing for aligning and guiding the EGR assembly during installation onto the intake housing.

Abstract: An estimation device that is applicable to a combustion system including an internal combustion engine includes a mixing acquisition unit, a combustion amount estimation unit, a region estimation unit, and a timing estimation unit. The mixing acquisition unit acquires a mixing ratio of various components contained in the fuel used for combustion in the internal combustion engine. The combustion amount estimation unit estimates a combustion amount of the fuel caused by a pilot combustion produced by injecting the fuel into a combustion chamber of the internal combustion engine with a pilot injection, based on the mixing ratio acquired by the mixing acquisition unit. The region estimation unit estimates a combustion region of the pilot combustion in the combustion chamber based on the mixing ratio. The timing estimation unit estimates an ignition timing, at which an ignition occurs in the combustion chamber with the pilot injection, based on the mixing ratio.

Abstract: A combination system may include a carburetor in fluid communication with an engine intake tract and a fuel injector in fluid communication with the engine intake tract.

Abstract: A pre-chamber for a fuel injector is disclosed. The pre-chamber includes a cylindrical body member extending axially from a first end portion to a second end portion opposite to the first end portion. The pre-chamber further includes a bottom plate located proximal to the first end portion of the cylindrical body member. The pre-chamber also includes a sacrificial member extending axially outwards from the second end portion of the cylindrical body member.

Abstract: In one embodiment, a method may comprise coupling a plurality of reinforcement fibers to a plurality of spherical components; inserting the plurality of spherical components into an enclosure; and heating the enclosure to cause the plurality of spherical components to expand, wherein the plurality of spherical components expands to form a geodesic structure, wherein the geodesic structure comprises a plurality of polyhedron components configured in a geodesic arrangement.

Abstract: A combined exhaust and engine brake rocker arm assembly configured to selectively open first and second exhaust valves, includes a rocker arm body, an exhaust rocker arm assembly formed in the rocker arm body, and an engine brake rocker arm assembly formed in the rocker arm body and configured to operate in a collapse mode and a rigid mode. The exhaust rocker arm assembly is configured to selectively engage a valve bridge to open the first and second exhaust valves, and the engine brake rocker arm assembly is configured to selectively engage the valve bridge to open only the first exhaust valve.

Abstract: A control process for controlling an engine speed governor of an engine is provided. The process comprises the steps of calculating the current engine power being developed by the engine, and determining an appropriate engine speed for the current engine power based upon a first engine map. The process then instructs the speed governor to adjust the engine speed in accordance with the first map if required. The process monitors for desired engine power requests, and calculates a power ratio of desired engine power versus current engine power upon receiving a desired engine power request. The process then establishes an engine speed adjustment value based upon a second engine map of power ratio versus speed adjustment value, and instructs the speed governor to adjust the engine speed in accordance with the speed adjustment value. A speed governor system incorporating the control process, and a work machine or vehicle incorporating such a system are also provided.

Abstract: A multi-cylinder engine includes first and second subsets of cylinders. A dedicated-cylinder exhaust gas recirculation (EGR) system is associated with the second subset of cylinders. A plasma ignition system is disposed in the second subset of cylinders. A controller operates the plasma ignition system to control the plasma igniters to execute plasma discharges in the second subset of cylinders to generate residual exhaust gas, which is recirculated through the dedicated-cylinder EGR system to the intake air system for introduction into intake air.

Abstract: Systems and methods for controlling knock in an internal combustion engine are presented. In one example, spark timing is retarded in engine cylinders where engine knock is indicated and spark is subsequently advanced after it has been retarded. The rate spark timing is advanced may be based on a way engine cylinders have been deactivated.

Abstract: Airfoils and gas turbine engines having the same, the airfoils including an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body, wherein at least one wall of the cooling cavity is a curved end wall, and an end wall contoured pedestal positioned adjacent the curved end wall. The end wall contoured pedestal has a first portion with a contoured side wall and a parallel side wall, and a second portion with tapering side walls, wherein the contoured side wall faces the curved end wall, the contoured side wall paralleling a contour of the curved end wall and defining a meter section therebetween.

Abstract: Disclosed herein is a mounting structure of a fuel rail, including a mounting boss part having a through-hole formed in a longitudinal direction and a first mating surface formed at an outer surface, an injector cup part provided separately from the mounting boss part and having a second mating surface formed at an outer surface and a flow path hole formed at one side of the second mating surface to be connected to the main pipe for transferring fuel to an injector, and a bridge part connecting the mounting boss part and the injector cup part and having a third mating surface. The mounting structure of the fuel rail can effectively distribute stress concentration by increasing contact area with the main pipe, thereby improving fatigue strength.