Abstract: A nose cone for debris deflection comprising a deflector formed in the nose cone, and an actuator in operative communication with the deflector, the actuator configured to engage the deflector configured to create a deflection air stream; the deflection air stream being configured to manipulate a fan inlet air flow such that any debris entrained in the fan inlet air flow has a trajectory line directed away from a core flow of a gas turbine engine and toward a bypass flow of the gas turbine engine.

Abstract: What is provided is a metal ion recovery device including: a raw solution tank that is configured to store a metal ion containing raw solution including metal ions; a recovery liquid tank that is configured to store a metal ion recovery liquid including metal ions recovered from the metal ion containing raw solution; a metal ion selective permeable membrane that separates the raw solution tank and the recovery liquid tank and selectively transmits the metal ions; an anode that is arranged on a side of the metal ion selective permeable membrane close to the raw solution tank; a cathode that is arranged on a side of the metal ion selective permeable membrane close to the recovery liquid tank; a porous current collector that is formed of a conductive material; a first spacer that is configured to maintain a gap between the metal ion selective permeable membrane and the anode; and a second spacer that is configured to maintain a gap between the metal ion selective permeable membrane and the cathode, in which the

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a first propulsor rotor, a geartrain, a rotating assembly and an auxiliary turbine. The rotating assembly is rotatable about an axis and includes a turbine rotor. The rotating assembly is coupled to and is configured to drive rotation of the first propulsor rotor through the geartrain. The auxiliary turbine is coupled to the first propulsor rotor independent of the geartrain.

Abstract: An inlet scroll for a combustor includes an inlet, an annular outlet, a volute duct, and a transition. The volute extends from the inlet to circumscribe an axis to form a monotonically decreasing cross-sectional flow area from the inlet. The transition fluidly connects a radially inner boundary of the volute duct to the annular outlet. The transition includes a radial portion at the volute duct and an axial portion at the annular outlet.

Abstract: A combustor system for an aerial vehicle includes an outer liner with a first end and a second end, an inner combustor case contained within the outer liner and defining a central combustor chamber, a lumen extending into the central combustor chamber, an air flow path extending between the outer liner and the inner combustor case, an integrated air scoop attached to the inner combustor case at the lumen and directing air from the air flow path into the central combustor chamber, and a fuel bolt, the fuel bolt including a head located outside of the outer liner and a body starting outside of the outer liner and extending perpendicular to the outer liner through the outer liner, through the integrated fuel scoop, and ending at the lumen, and fuel manifold with a fuel orifice within the fuel bolt.

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

Abstract: A fuel system includes a reservoir, a heat exchanger, a heating device, a cracker and a fuel injector. The heat exchanger is configured to vaporize a first flow of liquid ammonia received from the reservoir into ammonia gas using heat energy. The heat exchanger is configured to receive the heat energy from the heating device during a first operating mode. The heat exchanger is configured to receive the heat energy from a turbine engine a second operating mode. The cracker configured to at least partially crack the ammonia gas into hydrogen gas and nitrogen gas. The fuel system is configured to deliver the hydrogen gas or a combination of the hydrogen gas and the nitrogen gas to a fuel injector for injection into a combustion chamber.

Abstract: A laser welding method according to an embodiment includes a preparation process and a welding process. The preparation process includes preparing a temporarily-welded member that includes multiple connection portions by temporarily welding a second member to a first member. The welding process includes welding the second member to the first member by irradiating a laser beam on the temporarily-welded member. In the welding process, a first process is performed, after which a second process is performed. The first process includes irradiating a laser beam from a prescribed position to a second connection portion, wherein the second connection portion is adjacent to a first connection portion, and the prescribed position is between the first connection portion and the second connection portion. The second process includes irradiating a laser beam from the first connection portion to the prescribed position.

Abstract: A temperature raising device includes a parallel circuit including a capacitor connected in parallel to a battery that is a temperature raising target, and an alternating current (AC) generation circuit connected to the parallel circuit. When capacitance of the capacitor is denoted by CP, an inductance component of the battery is denoted by LS, and a resistance component of the battery is denoted by RS, CP satisfies Inequality (1) and an angular frequency ? of the AC generation circuit satisfies Eq. (2).

Abstract: A system and method for converting hazardous waste vapors into renewable and reusable energy is disclosed. The system comprises a generator, a compressor operable to pressurize vapors to a selected threshold range, and a gas storage system configured to store and feed the fully pressurized vapor to the generator at a steady state.

Abstract: A propulsion system for an aircraft includes a gas generating core engine, a propulsor that is driven by an exhaust gas flow that is generated by the core engine, and an inlet assembly where an inlet airflow is communicated to the core engine. The inlet assembly is disposed aft of the core engine and includes a turning duct that directs inlet air into the core engine, and a particle exhaust outlet that directs particulates away from the core engine.

Abstract: A cooktop appliance includes a cooktop plate defining an upper cooking surface, and a plurality of heating elements. The cooktop appliance also includes a controller in operative communication with the plurality of heating elements, a user interface disposed on the cooktop plate, and a light guide positioned below the cooktop plate. The light guide includes a slot. The cooktop appliance also includes a touch foil positioned at the light guide. The touch foil includes a locator graphic positioned on a surface of the touch foil. The locator graphic aligns within the slot of the light guide.

Abstract: A dielectric heating device includes a first electrode and a second electrode that face an object to be heated and to which an AC voltage is applied, and a coil that is electrically coupled in series to the first electrode. A linear distance between one end and the other end of the coil is equal to or smaller than a linear distance between the one end and a central portion of the coil in a magnetic path direction of the coil.

Abstract: An assembly for an aircraft propulsion system includes a nacelle inlet structure which extends axially along and circumferentially around a centerline. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of structure segments. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. Each of the structure segments includes an exterior skin, a mount and an electric heater configured to heat the exterior skin. The exterior skin forms a respective circumferential section of the inlet lip. The mount is connected to the exterior skin. A fastener extends radially through the mount and attaches a respective one of the structure segments to the inner barrel.

Abstract: Ionic thruster methods and apparatus for aircraft are disclosed. An example ionic thruster for aircraft includes a nozzle. The nozzle includes an outlet and an inlet, the inlet to receive fluid and containing an electrode mount. A ground electrode is disposed within the nozzle. Conducting pins are coupled to the electrode mount, each of the pins having a first end coupled to the electrode mount and a second end positioned closer to the ground electrode than the first end, the pins spaced apart from the ground electrode.

Abstract: The provided is a coaxially staged burner for a low-emission combustion chamber of a dual-fuel gas turbine utilizing gaseous and liquid fuels. The coaxially staged burner includes a mounting flange, a main fuel sleeve, and a swirler, where the mounting flange is provided with a fuel supply port; the main fuel sleeve is internally provided with coaxially nested four-stage fuel sleeves; the swirler includes a center pilot stage, a first premix stage, a second premix stage, a first-stage hub, and a second-stage hub; when a liquid fuel operates alone, the liquid fuel enters a swirler passage through a pilot-stage liquid fuel nozzle and a second-stage blade liquid fuel hole to achieve premixing and evaporation; and when a gaseous fuel operates alone, the gaseous fuel enters the swirler passage through a first-stage blade fuel hole and a second-stage blade gaseous fuel hole for mixing.

Abstract: A heating system includes a power supply that applies a first voltage to a sense resistor in series with a resistive heating material during a first time period; and a controller that determines a temperature of the resistive heating material based on a current through the sense resistor and a second voltage across the resistive heating material during the first time period. Additionally, the controller commands the power supply to provide a third voltage to the resistive heating material during a second time period, and the third voltage is based on the temperature of the resistive heating material.

Abstract: A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner at least partially defining a combustion chamber; a wall coupled to the combustor liner; a first fuel supply to supply a first fuel; a gaseous fuel supply to supply a gaseous hydrogen fuel; and a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply and the gaseous hydrogen fuel supply, the fuel nozzle assembly comprising: a main mixer; and a fuel nozzle comprising an outer wall defining a pilot channel and an outer wall fuel orifice to emit at least one of the first fuel or the gaseous fuel radially outward into the main mixer; and a secondary mixer disposed in the pilot channel.

Abstract: A vane heating system for an engine includes a plurality of static vanes, an electrically resistive material, and an electric power source. The static vanes are disposed within the engine, and each static vane has an inner surface that defines a vane cavity. The electrically resistive material is disposed within the vane cavity of each static vane. The electric power source is electrically coupled to, and is configured to selectively supply an electric current to, the electrically resistive material in each static vane. When the electric current is supplied to the electrically resistive material, a temperature of the static vane increases.

Abstract: A device for guiding a main air flow (F1) for an aircraft turbine engine, the device including a first air flowing pipe of a main air flow, the first pipe having a main axis, a plurality of ejectors of a secondary air flow located within the first pipe and configured to eject a secondary air flow and force the flow of the main air flow into the first pipe, the ejectors being distributed around the main axis, and a second air flowing pipe located at the outlet of the ejectors and including one end which is connected to one end of the first pipe, wherein the second pipe includes a narrow end.