An aero-engine low pressure pump is provided for supplying fuel at a raised pressure to a high pressure pump. The low pressure pump has a pumping mechanism which raises the pressure of fuel flowing though the mechanism. The low pressure pump further has electrical motor which drives the pumping mechanism. The low pressure pump further has a variable frequency motor drive which supplies electrical power to the electrical motor. The variable frequency motor drive measures the electrical power supplied to the electrical motor. The low pressure pump further has a control unit which compares the measured electrical power to a reference power, and, when the measured electrical power is less than the reference power by a predetermined amount, controls the motor drive to increase the power supplied to the electrical motor thereby increasing the pressure rise produced by the pumping mechanism.

An impeller for a ventilation unit, especially for use in plants for the aerobic treatment of organic waste, is provided. The impeller comprises a housing, a pair of mutually facing plates received within the housing and provided centrall with a through-hole for a cylindrical hub, and a plurality of first radial blades arranged between the plates. The impeller further comprises second radial blades arranged on at least one plate, on its side facing the inner wall of the housing and extending from the cylindrical hub toward the periphery for creating an under-pressure zone in the central region of the impeller itself, at its hub. Thanks to this measure, condensate water deriving from the humidity of the air sucked/blown by the ventilation unit is prevented from leaking along the rotation shaft of the impeller, towards its motor and towards the outside environment.

The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area designed movable relative to the wall area.

A method for forming a housing for a flow-conducting component includes forming at least two functional regions of the housing having different material properties using at least one of radiation-induced melting and solidification of a build material and a process gas jet. Each functional region of the housing may be generated from a different construction material, and at least one functional layer may be formed with a reduced weight structure such as a honeycomb structure.

An apparatus for converting thermal energy into mechanical energy by a cycle, having a heat exchanger, a reservoir for an operating medium, a feed line, a turbine, and a return line having at least one recovery device. To utilize waste heat for the generation of electrical energy, the turbine is embodied as a disc rotor turbine with full condensation of the operating medium, whereby a separate condenser can be eliminated.

A pump has a brushless electrical motor including a stator assembly and a rotor ring arranged externally of the stator assembly. The pump further has a centrifugal impeller operatively connected to the rotor ring such that the electrical motor rotates the impeller. The impeller is configured to raise the pressure of a fluid which flows through the impeller between an inlet and an outlet thereof. The pump is configured such that a portion of the raised pressure fluid flow is diverted to form a recirculation flow which circulates through and cools the electrical motor before being returned to the impeller for re-pressurisation thereby.

An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a central rotary shaft extending from the housing, at least one fuel and air supply channel having a first portion extending radially from the rotary shaft and a second portion in fluidic communication with first portion of the fuel and air supply channel, at least two propulsion vessels, each propulsion vessel connected to the at least one of the fuel and air supply channel and configured to burn or detonate the fuel and rotate around the central rotary shaft; and at least one exhaust duct extending from the housing.

A power and propulsion system includes an air compressor, a combustor positioned to receive compressed air from the air compressor as a core stream, and a closed-loop system having carbon dioxide as a working fluid that receives heat from the combustor and rejects heat to a cooling stream. The closed-loop system configured to provide power to a fan that provides the cooling stream, and to one or more distributed propulsors that provide thrust to an aircraft.

A magnetic drive, seal-less combination axial air and water pump includes a housing having an inlet and an outlet at least one impeller mounted for rotation within the housing, and a magnetic drive surrounding the first rotor and the second rotor, the magnetic drive being configured to transmit torque to the first rotor and a second rotor at a location radially spaced from a central axis of the first rotor and the second rotor.

A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor.