Abstract: An easily serviceable liquid filter assembly having a housing with a drain to provide draining of fluid (e.g., liquid) from the housing. The filter assembly has a fluid inlet to receive dirty fluid into the housing, a fluid outlet to expel filtered fluid from the housing, and a drain, when open, to expel unfiltered (dirty) fluid from the housing. By removing a cover from the housing, the filter element opens the drain so that all fluid in the housing can be directly collected or can flow into the oil pan to be collected with the fluid present in the pan. All fluid, now in the drain pan, can be drained and collected in a disposable container such as a plastic pouch, which can be recycled. The filter element can be removed from the housing via the removed cover.

Abstract: An aircraft can include a stacked propeller to generate lift during assent and descent. The stacked propeller includes a first propeller and a second propeller that co-rotate about an axis of rotation. In one embodiment, the blades are coupled to a rotor mast that contains an internal cavity. In one mode of operation, the first propeller and/or the second propeller can be stored in the internal cavity in order to reduce drag during flight. The aircraft can include one or more stacked propellers, such as a port propeller and a starboard propeller, which rotate in opposite directions during one or more modes of flight.

Abstract: A piston assembly includes a piston head for reciprocating back and forth within a cylinder of an engine, an upper rod coupled to the piston head at one longitudinal end of the upper rod and fixed relative to the piston head, and a lower rod rotatably coupled to an opposite longitudinal end of the upper rod, the lower rod configured to pivot about the opposite longitudinal end of the upper rod. The lower rod is configured to couple to a crankshaft at a longitudinal end of the lower rod opposite the upper rod. Methods of forming a piston assembly and engines incorporating such piston assemblies are also disclosed.

Abstract: An anti-polish ring for an internal combustion engine is provided. The anti-polish ring includes an axially extending ring portion that is configured to scrape a top portion of a piston in a cylinder liner. The anti-polish ring is configured to accommodate passage of an intake or exhaust valve thereby. The anti-polish ring may include an alignment feature so that the anti-polish ring is inserted in a predetermined orientation in the cylinder. The anti-polish ring may include a heat shield and/or a seating member.

Abstract: A valve assembly failsafe configured to be coupled to an actuator of a coolant control regulator assembly is provided. The valve assembly failsafe includes a wind arm, a spring that engages the wind arm under spring tension, a latch that engages the wind arm, a drive gear that engages the wind arm and the actuator, and a driver that engages the latch. The valve assembly failsafe is configured to be positioned in a set state where the latch engages and retains the wind arm under spring tension and the drive gear freely rotates during rotation of the actuator, and a tripped state where the driver rotates the latch to disengage the latch from the wind arm, causing the wind arm to rotate under the spring tension to engage the drive gear and cause the drive gear to drive the actuator to a default position.

Abstract: Systems, methods, and computer program products for monitoring a wind turbine (10). The system receives a signal (426) indicative of a pitch force being applied to a blade (20) of a wind turbine (10). The signal (426) is sampled to generate a discrete time-domain signal (426) including a plurality of pitch force samples. Samples are selected for analysis using a sampling window (326) that excludes samples obtained under operating conditions determined to be detrimental to obtaining good data. The selected samples are processed to generate a spectral density (150) of the signal (426), and the frequency content of the spectral density (150) analysed to determine the condition of one or more components of the wind turbine (10). If the analysis indicates that a component of the wind turbine (10) needs attention, the system generates an alarm.

Abstract: An internal combustion engine system is described herein. The internal combustion engine system uses one or more fuels that may be hydrophilic. The system uses a water measuring sensor to determine the concentration of water in the hydrophilic fuel. To meet power demands, the system uses the measured water concentration to modify data stored in a fuel map. The fuel map provides a controller the pump speeds and mixing ratio of the fuels for a given power level. The system receives that data and modifies it based on the measured concentration of water.

Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.

Abstract: The disclosure relates to a control device, in particular in an electromechanical camshaft adjuster, comprising an electric motor and a control transmission coupled to the electric motor via a coupling element and designed as a harmonic drive. A two-armed wire coupler is provided as the coupling element, the arms of which engage in openings of an inner ring of a waveform generator of the control transmission, and the wire coupler has a winding which is wound around the motor shaft of the electric motor in a non-rotating manner.

Abstract: A reciprocating combustion engine includes at least one cylinder, in which a reciprocating piston is arranged back and forth movable. The reciprocating combustion engine includes a pin structure arranged on the combustion chamber side in the area of the cylinder head or the piston bottom. Due to the pin structure, local peak temperatures can be avoided during the combustion process, so that NOx emissions can be avoided or at least greatly reduced. A motor vehicle, for example a commercial vehicle, includes a reciprocating combustion engine.

Abstract: A fuel system, comprising at least one fuel component formed of a steel alloy comprising 0.01-0.31 wt. % carbon, 0.0-0.20 wt. % silicon, 0.15-0.50 wt. % manganese, 0.0-0.015 wt. % phosphorous, 0.0-0.001 wt. % sulfur, 4.80-5.20 wt. % chromium, 4.80-6.20 wt. % nickel, 0.60-0.80 wt. % molybdenum, 0.0-0.550 wt. % vanadium, and 2.000-2.400 wt. % aluminum, wherein the at least one fuel component is configured to come in contact with fuel when fuel is ran through the fuel system.

Abstract: There is disclosed a composite fan blade root 100 comprising an outer region 110 comprising composite material and defining an outer inspection surface 120 of the component; an inner region 108 surrounded by the outer region 110; and an internal reflection boundary 102 embedded within the root 100 between the inner region and the outer region. The reflection boundary is configured to change a velocity of a signal emitted into the root from the inspection surface, whereby a signal emitted into the root from the inspection surface 120 may be reflected for detection.

Abstract: A rotary blade aircraft includes an airframe, a rotor shaft driven about a rotor axis, and a plurality of rotor blades driven by the rotor shaft about the rotor axis. The rotary blade aircraft includes a swashplate assembly coupled to the plurality of rotor blades. The swashplate assembly is operable to move the plurality of rotor blades about a respective longitudinal axis. The rotary blade aircraft includes a hydraulic control servo coupled between the airframe and the swashplate assembly. The hydraulic control servo is operable to move the swashplate assembly relative to the rotor axis. The rotary blade aircraft includes a harmonic control actuator coupled between the airframe and the swashplate assembly. The harmonic control actuator is operable independently relative to the hydraulic control servo to move the swashplate assembly relative to the rotor axis to reduce vibration at selected frequencies in the airframe.

Abstract: Plasmonically-enhanced catalytic surfaces and accompanying optics are described herein. These elements facilitate efficient coupling of light energy into a photocatalytic system by way of a surface plasmon. Various compatible optical configurations are presented, with an emphasis on the broadband coupling of light into a single plasmon mode. In an example embodiment, dispersive optics are used to direct polychromatic light onto a grating-embossed SPR-active surface. Dispersive optics allow resonance to be achieved at a wide range of incident wavelengths. Energy then transfers from the excited plasmon to an adjacent photocatalyst. The plasmon mode thus acts as a “funnel” of broadband light energy to the catalytic materials. High-efficiency incoupling and outcoupling from the plasmon mode suggest overall enhancement of catalytic activity, and broad applicability is anticipated due to the inherent flexibility of the system.

Abstract: A valve stem seal includes an elastomeric annular seal body including a first seal body section and a second seal body section. The first seal body section includes a first seal lip configured to sealingly abut against the valve stem to delimit an oil space and a second seal lip axially spaced from the first seal lip and configured to sealingly abut against the valve stem to delimit an air space. The first seal body section includes an annular channel in a radially inner wall between the first seal lip and the second seal lip that is spaced from the valve stem when the valve stem seal is mounted on the valve stem, and the surface of the channel includes an undercut configured to facilitate a deformation of the second seal lip toward the first seal lip.

Abstract: A quick return oil cylinder liner is disclosed. The cylinder liner includes an elongated cylindrical body having an outer surface and an inner surface defining a liner central axis extending between a first liner axial end and a second liner axial end. The inner surface is configured to form a combustion chamber with a piston and an engine housing. A quick oil return part is arranged on the inner surface of the cylinder liner corresponding to a non-skirt part of the piston. The oil return part is positioned below a position of the inner surface corresponding to an oil blade of an oil ring of the piston when the piston is positioned at a bottom dead center position. The oil return part extends to the second linear axial end and forms at opening at the second liner axial end.

Abstract: A piston may have an annular body including a crown portion defining a longitudinal axis, a radial direction perpendicular to the longitudinal axis, a plane containing the longitudinal axis and the radial direction, and a contoured combustion bowl. In the plane containing the longitudinal axis and the radial direction, the crown portion includes a radially outer squish surface, and a swirl pocket having a reentrant surface that extends axially downwardly and radially outwardly from the squish surface defining a tangent that forms a reentrant angle with the squish surface that ranges from 53.0 degrees to 57.0 degrees.

Abstract: An internal combustion engine for gaseous fuel includes a cylinder and a piston for reciprocal movement in the cylinder along a reciprocal axis, whereby a combustion chamber is at least partially delimited by the cylinder and the piston. The piston includes a piston crown facing the combustion chamber, a piston crown projection of the piston crown in a direction parallel to the reciprocal axis and onto a piston crown plane extending transversally to the reciprocal axis having a piston crown center point, the piston crown comprising a piston bowl surface defining a piston bowl and a piston rim portion enclosing the piston bowl surface. A piston bowl opening is the intersection between the piston rim portion and the piston bowl surface. The piston bowl opening has an opening center of gravity in the piston crown plane. The opening center of gravity is offset from the piston crown center point.

Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a shim plate having a first shim surface removably arranged on an axially facing surface of the annular ring, a carrier plate having a first carrier surface removably arranged on a second shim surface of the shim plate opposite the first shim surface, and a roller pin coupled to a second carrier surface of the carrier plate opposite the first carrier surface. The shim plate is sized so as to locate the roller pin at a predetermined distance from the annular ring so as to adjust a position of the plurality of variable vanes relative to the roller pin.

Abstract: The subject of invention is a method to derive specifications for an eccentric cam located in a void within the piston of an IC engine which will have parallel faces abutting the cam. These faces will drive the cam in a rotary fashion and transmit the energy produced by the piston by means of the cams axle. The method employs two variables: (a) the radius of the cam; (b) the degree of its eccentricity. These determine the slope of these abutting faces which will be rotated from the plane that is perpendicular to the axis of reciprocation. This slope is eccentric specific and produce a unique solution in each instance. This slope will be the same regardless of the cams radius. The result is an engine with no lateral oscillations.