Abstract: A modular blade connection structure includes a first module, a second module and a structural adhesive module. The first module is provided on an end face thereof with a bonding flange extending into the second module; a gap between the butting surfaces of the first module and the second module is injected with a structural adhesive, which is extruded and cured to form a structural adhesive module; and the thickness of the first module at the starting end of the bonding flange extends towards the inner surface to form a first reinforcement, and the structural adhesive module extends inside the second module in a direction away from the bonding flange to form a second reinforcement. The present disclosure facilitates the control the bonding quality of the double-sided overlapping of the modular blade by means of the bonding flange and the improvement of the fatigue resistance at the assembling position.

Abstract: A gas-cycle system operable using a Bell-Coleman cycle, the gas-cycle system comprising an expander (23) and a compressor (27) incorporated in a flow path (13). The expander (23) and compressor (27) are integrated in a rotary machine (41), and each comprises a rotor assembly (70) configured to define one or more zones (80) each of which changes continuously in volume during a rotation cycle of the rotor assembly. The expander (23) and compressor (27) are drivingly interconnected whereby rotational drive applied to one is transmitted directly to the other. Each rotor assembly (70) comprises an inner rotor (73) and an outer rotor (75) adapted to rotate about parallel axes at different rotational speeds. The inner rotors (73) are each drivingly connected to a common shaft for rotation therewith. The two outer rotors (75) are coupled together such that rotational drive applied to one is transmitted directly to the other.

Abstract: A wind turbine blade is provided, which includes a blade body extending from a blade root toward a blade tip along a blade length direction, a first sprayed layer disposed so as to cover at least a leading edge on a side of the blade tip of the blade body, for suppressing erosion of the leading edge of the blade body, a second sprayed layer formed between the blade body and the first sprayed layer, and having a lower electrical resistivity than the first sprayed layer, and a first conductive part for electrically connecting the second sprayed layer to a ground.

Abstract: In a compression unit, an upper compression unit suction tube is connected to an upper suction hole of an upper cylinder, and a lower compression unit suction tube is connected to a lower suction hole of a lower cylinder. In an accumulator shell of an accumulator vessel, an accumulator suction tube, an upper gas-liquid separation tube, and a lower gas-liquid separation tube penetrate a side wall of the accumulator shell, and are fixed by welding to a first through hole, a second through hole, and a third through hole of the accumulator shell, respectively. The upper gas-liquid separation tube is connected to the upper compression unit suction tube via an upper connecting tube outside the accumulator shell. The lower gas-liquid separation tube is connected to the lower compression unit suction tube via a lower connecting tube outside the accumulator shell.

Abstract: Various examples of the present disclosure provide aircraft engine sensing apparatuses and methods of manufacturing aircraft engine sensing apparatuses. For example, an example aircraft engine sensing apparatus includes an aircraft engine sensor, a plurality of connection wires, and at least one ceramic insulator. In some examples, the aircraft engine sensor is positioned within an aircraft engine. In some examples, the plurality of connection wires connect the aircraft engine sensor to a sensor connector. In some examples, the plurality of connection wires are positioned within a wire protection housing. In some examples, the at least one ceramic insulator is positioned within the wire protection housing and defines a plurality of insulator openings. In some examples, each of the plurality of connection wires passes through one of the plurality of insulator openings.

Abstract: The disclosure provides rotary machines that include, in one embodiment, a shaft defining a central axis A, the shaft having a first end and a second end. The shaft can have a first gearbox disposed thereon defining one or more cavities therein. At least one contour is slidably received into an arcuate cavity in an exterior surface of the gearbox. The contour has a convex outer surface that cooperates with an inwardly facing curved surface of a housing to form a working volume. A gearbox mechanism consisting of gears, crankshafts, bearings and connecting rod creates an oscillatory motion 2 times per revolution such that the contour can navigate about the arcuate cavity without contacting the cavity at a high rate of rotating speed. Thus, said working volume can expand and compresses twice per rotatable shaft revolution.

Abstract: A turbine (10) for a charging device (1) with a turbine housing (100) with a feed duct assembly (200), a turbine outlet duct (110) and a receptacle space (120). The feed duct assembly (200) includes a first feed duct (210) having a first fluid inlet portion (211) and a first fluid outlet portion (212), and a second feed duct (220) having a second fluid inlet portion (221) and a second fluid outlet portion (222). The first fluid outlet portion (212) extends across a first angular range (?1) about the guide installation (400). The second fluid outlet portion (222) extends across a second angular range (?2) about the guide installation (400). The first angular range (?1) is larger than the second angular range (?2). The first fluid inlet portion (211) and the second fluid inlet portion (221) are mutually spaced apart in the circumferential direction (26).

Abstract: Fuel injectors for gas turbine engines include an inner housing having a center body installed within the inner housing, an intermediate housing arranged radially outward from the inner housing, and an outer housing arranged radially outward from the intermediate housing. The center body is a hollow body structure defining a center body airflow passage therethrough, a first fluid passage is partially defined between an outer surface of the inner housing and an inner surface of the intermediate housing, a second fluid passage is partially defined within the intermediate housing, and a third fluid passage comprises the center body airflow passage, an inner airflow passage defined between an exterior surface of the center body and an interior surface of the inner housing, and an outer airflow passage that is defined by the outer housing and radially outward from the intermediate housing.

Abstract: A method of servicing a portion of a gas turbine engine includes inserting a rigid guide tube into an inspection port in a shroud of the gas turbine engine. The flexible guide tube is inserted into and through the rigid guide tube. The flexible guide tube is pre-shaped such that the flexible guide tube is biased towards a predetermined shape after being inserted through the rigid guide tube. A tool is pushed through the flexible guide tube such that the distal end of the tool moves out of and away from an end of the flexible guide tube. An area of interest of the gas turbine engine is then serviced with the tool.

Abstract: A passive cooling system includes a fan configured to generate an air flow path for a radiator, the air flow path extending from the fan to the radiator and a cooling pipe extended between a turbocharger and an intake manifold, the cooling path positioned in the air flow path between the fan and the radiator.

Abstract: A variable geometry turbine (VGT) comprising an intake channel, a rotor, an adjustable nozzle, a nozzle actuator, and a controller. The controller comprises a calibration routine, arranged for calibrating the VGT during normal operation thereof. In the calibration routine, the controller is arranged for performing the steps of: adjusting the adjustable nozzle from an initial position towards a closed position, while monitoring a pre-turbine pressure; detecting a deflection point position of the adjustable nozzle at which a sharp difference in the pre-turbine pressure occurs; and adjusting a minimum cross sectional area in the closed position, to adjust a working range of the VGT in dependence of varying operating conditions, wherein the working range excludes the detected deflection point position.

Abstract: A gas turbine intake has a swirl housing having a tangential inlet fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the tangential inlet, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis, each vane having a twisted and flat body having a length extending from a leading end to a trailing end, the leading end being oriented mainly circumferentially and axially at the swirl path, the trailing end being oriented mainly axially and radially at the annular outlet, the twisted and flat body twisting between leading and trailing ends around the central axis, around a radial axis perpendicular to the central axis, and around a tangential axis perpendicular to both the central axis and the radial axis.

Abstract: A vacuum pump suitable for prolonging the life of a heating means used as a measure to prevent product deposition in the vacuum pump, and a heating device for the vacuum pump. A vacuum pump that exhausts gas by rotation of a rotating body has an exhaust flow path for exhausting the gas, and a heating means for heating the exhaust flow path, wherein the heating means has a plurality of resistance heating elements connected in parallel to a pair of wiring lines. The heating means has a current measuring means for measuring a sum of values of currents flowing through the plurality of resistance heating elements, a determination means for determining failure conditions of the plurality of resistance heating elements on the basis of a measured value obtained by the current measuring means, and an output means for outputting the failure conditions determined by the determination means.

Abstract: The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

Abstract: A proactive method prevents vibrations in one or more rotor blades of a wind turbine when the wind turbine is in a standstill idling state with a rotor hub free to rotate. The method determines a minimum revolution rate of the rotor blades that prevents vibrations of the rotor blades and that the actual revolution rate of the rotor blades is below the minimum revolution rate. A wind parameter is detected and determined to be above a threshold limit. The method also detects if grid power is available for pitching the rotor blades. Based on the wind parameter, a controller determines a pitch angle for one or more of the rotor blades to increase rotation of the blades to at least the minimum revolution rate. The controller initiates pitching the rotor blades to increase the revolution rate of the rotor blades prior to vibrations being induced in the rotor blades.

Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

Abstract: A non-transitory computer readable medium with instructions stored thereon, the instructions executable by one or more processors for selecting infrequent or frequent autotuning of a combustor; and determining the health of a combustor. Also, a method of monitoring a combustor within a gas turbine engine system, comprising providing a gas turbine engine system, wherein the gas turbine engine includes an autotuning system; selecting infrequent or frequent autotuning of the combustor; and determining the health of the combustor; wherein said determining the health of a combustor comprises receiving real-time fuel gas temperature data from at least one thermocouple.

Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Abstract: A heat dissipation fan includes: a body including a fan air inlet surface, a central shaft driving surface located inside the fan air inlet surface, and a plurality of protrusion structures configured at spacings in a circumference direction of the central shaft driving surface; and fan blades including first fan blades connected between the central shaft driving surface and the fan air inlet surface, and second fan blades connected between the protrusion structure and the fan air inlet surface. A fan air inlet angle is formed between each fan blade and the central shaft driving surface, and the plurality of protrusion structures are configured to vary the fan air inlet angle to control a flow field of an airflow entering the fan air inlet angle.