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.

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: 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: 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 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.