Abstract: A deposition planning method for an additively manufactured object includes: acquiring shape data; determining a welding path of each layer by slicing a three-dimensional shape of the additively manufactured object into layers; classifying a plurality of welding paths into intersection region paths and constant region paths; dividing the intersection region paths into a lower layer path and an upper layer path of an intersection portion; and determining welding conditions of the intersection region paths such that an upper layer deposit amount is more than a lower layer deposit amount, a sum of the upper layer deposit amount and the lower layer deposit amount is equal to a deposit amount in the constant region paths, and in a cross-section orthogonal to a longitudinal direction of the weld beads formed along the upper layer path, profiles of the weld beads adjacent to each other overlap each other.

Abstract: A fuel system including: a liquid hydrogen fuel tank for holding a first portion of hydrogen fuel in a liquid phase; a gaseous hydrogen fuel tank for holding a second portion of hydrogen fuel in a gaseous phase; and a fuel delivery assembly including a liquid hydrogen delivery assembly in fluid communication with the liquid hydrogen fuel tank, the liquid hydrogen delivery assembly having a pump for pumping, in the liquid phase, the first portion of hydrogen fuel through the liquid hydrogen delivery assembly; a gaseous hydrogen delivery assembly in fluid communication with the gaseous hydrogen fuel tank, the gaseous hydrogen delivery assembly extending in a parallel arrangement with the liquid hydrogen delivery assembly; and a regulator assembly in fluid communication with both the liquid hydrogen delivery assembly and the gaseous hydrogen delivery assembly for providing gaseous hydrogen fuel to the engine when installed in the vehicle.

Abstract: A welding apparatus comprising a first fixing plate and a second fixing plate arranged at an interval; a gas-electric slip ring is connected to the side of the first fixing plate facing the second fixing plate; a hollow shaft drive unit is connected to the side of the second fixing plate facing the first fixing plate; a conductive link is connected to the hollow shaft drive unit and passes through the second fixing plate; a curved conductive nozzle is connected to the conductive link on the outer side of the second fixing plate; and a plurality of support rods are uniformly distributed around the rotational axial direction of the hollow shaft drive unit, and are respectively connected to the first fixing plate and the second fixing plate; the hollow shaft drive unit drives the conductive link to rotate, and the conductive link drives the curved conductive nozzle to oscillate.

Abstract: A spray nozzle assembly includes a nozzle cap body and a deflector cap. The nozzle cap body having a fluid passage extending there through. The downstream end of the fluid passage being defined by an end wall having a discharge orifice. The end wall defines an exterior end surface of the cap body. A deflector cap is arranged at a downstream end of the cap body. The deflector cap has an upstream end defining a deflector surface spaced from the exterior end surface of the nozzle body in a longitudinal direction of the spray nozzle assembly and opposing the discharge orifice. The exterior end surface of the cap body and the deflector surface define a radially outwardly extending, annular discharge passage communicating with the discharge orifice and that together with the discharge orifice produces a full hollow cone spray discharge pattern.

Abstract: A heating system having: i) at least one resistive heat element; ii) at least two terminals for receiving a grid voltage from a power grid, and iii) a controller for being connected to the terminals for receiving the grid voltage, the controller connected to the at least one resistive heat element and being configured for controlling a load current through the at least one resistive heat element, wherein the controller is configured controlling the load current though the at least one resistive heat element. The controller comprises an FCFO-bidirectional power switch connected in series with the at least one resistive element for controlling the load current that is received from the power grid. A method is for controlling the load current through the at least one resistive element, which applies a certain algorithm to avoid inrush current, shortens the length of a cold start and solves problems such as EML.

Abstract: An exhaust system for an aircraft engine, has: a turbine exhaust duct (TED) having an inner wall and an outer wall defining an inlet conduit and outlet conduits; and an exhaust case enclosing the TED and defining exit ports and extending from a forward end to a rearward end and having: a first section extending between the ends, the first section extending from a first edge to a second edge and having a first flange and a second flange at the first and second edges; and a second section extending between the ends and from a third edge to a fourth edge and having a third flange and a fourth flange at the third and fourth edges, wherein the first section is detachably secured to the second section via the first flange being detachably secured to the third flange and the second flange being detachably secured to the fourth flange.

Abstract: A resonator for a combustor is provided. The resonator includes an outer body that partially defines a first chamber and one or more outer apertures configured to convey a first fluid between an outer fluid plenum and the first chamber. The resonator further includes an inner body that partially defines a second chamber and one or more inner apertures configured to convey a second fluid between the second chamber and a combustion chamber. The resonator further includes a flexible membrane that is disposed between the inner body and the outer body and partitioning the first chamber and the second chamber.

Abstract: A rotating detonation engine (RDE) injector and method of creating the same. In some embodiments, the RDE injector is configured such that the fuel to oxidizer pressure ratio is in a range of 0.8775 to 1.4917. In some embodiments of the method of creating a RDE a particular combination of propellants is identified, and their gas specific constant and specific heat ratio are recorded. A plurality of initial flow conditions is established, and the compressible mass flow equation is used to determine an appropriate cross-sectional area of each injector to produce a fuel to oxidizer pressure ratio is in a range of 0.8775 to 1.4917.

Abstract: An aircraft comprising at least one dihydrogen tank, at least one dihydrogen consumer system, a supply line arranged between a consumer system and a tank, for each consumer system, a loop containing a heat transfer fluid, for each tank and each supply line, a supply heat exchanger which exchanges calories between the heat transfer fluid and the dihydrogen and, for each consumer system, a return heat exchanger which exchanges calories between the heat transfer fluid and the consumer system.

Abstract: A gas turbine engine generally defines an axial direction and includes a combustor assembly. The combustor assembly includes a plurality of liner tiles defining at least part of a combustion chamber that extends between a forward end and an aft end generally along the axial direction. A combustor liner support assembly is positioned on a cold side of the plurality of liner tiles and defines a rail extending radially toward the combustion chamber. A retainer assembly includes a bushing where at least one liner tile of the plurality of liner tiles is floatably coupled to the rail via the bushing.

Abstract: A shower device includes a shower device body. The shower device body includes a body water channel, a shower head with spray holes, a storage box for storing cleaning liquid, a control valve, and a one-way valve. The shower head is connected to the shower device body, and the spray holes are fluidly coupled to the body water channel. The storage box includes a liquid inlet and a liquid outlet and is installed in the shower device body. The liquid inlet and the liquid outlet are fluidly coupled to the body water channel respectively. The control valve is installed in the liquid inlet and is configured to control opening and closing of the liquid inlet. The one-way valve is installed in the liquid outlet.

Abstract: The laser beam machine includes: a laser emitting system for emitting a laser beam, wherein the laser emitting system has a protective glass capable of transmitting the laser beam; and a housing attached to the laser emitting system. The housing includes, a first end facing the laser emitting system, a second end opposite to the first end, and a first blowing portion located over an entire circumference of an interior of the first end. The first blowing portion blows a gas toward a central axis of the housing.

Abstract: A combustor assembly for a gas turbine engine includes a combustor defining a combustion chamber. The combustor assembly includes a combustor liner support shell, and a plurality of liner tiles defining at least part of the combustion chamber. Each liner tile of the plurality of liner tiles defines a protrusion and a recess opposite the protrusion where the recess is configured to at least partially receive the protrusion of an adjacent liner tile of the plurality of liner tiles. A fastener assembly is at least partially disposed in the recess for coupling a respective liner tile to the combustor liner support shell.

Abstract: A fuel cell electric power system includes a fuel cell stack, and a charge air system including an intake air compressor, an exhaust turbine, and a flow control valve assembly. The flow control valve assembly includes at least one flow control valve rotatable in a valve housing to fluidly connect an exhaust inlet, selectively, to a turbine feed outlet via a variable flow area to adjust a torque applied to the exhaust turbine by a flow of exhaust.

Abstract: A plasma thruster has a tunable electron source configured to provide electrons with controllable energy. An entry electrode and an exit electrode permit an air flow to pass from the entry electrode to the exit electrode. The entry electrode and exit electrode receive electrons from the tunable electron source. A controller selectively controls the entry and exit electrodes to accelerate positive and negative ions in the air.

Abstract: An aircraft propulsion system includes a cryogenic fuel system and a fuel flow path where a fuel flow is circulated from upstream in a direction downstream to a combustor of the core engine. A first heat exchanger inputs heat into the fuel flow downstream of the first heat exchanger is used to heat the fuel flow from the fuel storage tank and a second heat exchanger inputs thermal energy from a heat source into the fuel flow from the core engine downstream of the first heat exchanger. A turboexpander is configured to generate shaft power from expansion of the fuel flow exhausted downstream from at least one of the first heat exchanger and the second heat exchanger.

Abstract: The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.

Abstract: A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, a compressor of the compressor section comprising an aft-most compressor stage; a stage of stator vanes located downstream of the aft-most compressor stage; a stator case including a seal pad; and a spool drivingly coupled to the compressor, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the spool comprising a seal tooth assembly, the seal tooth assembly including a seal support extension, a seal tooth extending from the seal support extension toward the seal pad, and a dampener operable with the seal support extension.

Abstract: A fuel system can include a first fuel circuit, a second fuel circuit, and an inert gas purge system operatively connected to both the first fuel circuit and the second fuel circuit to purge at least a portion of either or both of the first and/or second fuel circuit. The first fuel can be a liquid fuel and the second fuel can be a gaseous fuel. The first fuel circuit can include a first fuel manifold configured to fluidly communicate a first fuel supply with at least one dual fuel nozzles downstream of the first fuel manifold.

Abstract: A method for energy conversion for a vehicle is provided. The method including extracting a flow of compressed fluid from a compressor section of a propulsion system; flowing the flow of compressed fluid to a turbine operably coupled to a driveshaft, in which the driveshaft is operably coupled to a load device; expanding the flow of compressed fluid through the turbine to generate an output torque at the driveshaft to operate the load device; and flowing the expanded flow of compressed fluid from the turbine to thermal communication with a thermal load.