A miniaturized turbogenerator (200) to directly provide electrical propulsion (307 308, 309) to small land, air, and maritime vehicles without an intervening electricity storage battery (315). The invention comprises of a process of miniaturization (500) of a turbine engine core (100), in particular its compressors and turbines (400), by means of hyper-feed machining by linear force alone, i.e. without rotation of either the workpiece or the cutting tool (505), and a resulting apparatus of a miniaturized turbogenerator (200) that has sufficient power density to provide high-performance electrical propulsion (310) for commercially feasible automobiles, urban air mobility vehicles, and other small vehicles and vessels with greater performance than battery-electric vehicles (300).

A permanent magnet comprises crystal grains each including a main phase. An average size of the crystal grains is 1.0 μm or less, and a degree of orientation of easy magnetization axes of the crystal grains to an easy magnetization axis of the magnet is 15% or more and 90% or less. A recoil magnetic permeability is 1.13 or more, a residual magnetization is 0.8 T or more and less than 1.16 T, and an intrinsic coercive force is 850 kA/m or more.

A permanent magnet comprises crystal grains each including a main phase. An average size of the crystal grains is 1.0 μm or less, and a degree of orientation of easy magnetization axes of the crystal grains to an easy magnetization axis of the magnet is 15% or more and 90% or less. A recoil magnetic permeability is 1.13 or more, a residual magnetization is 0.8 T or more and less than 1.16 T, and an intrinsic coercive force is 850 kA/m or more.

A motor cooling system including, an engine nacelle defining a primary axis, a stator housing within the engine nacelle, a plurality of stator guide vanes attached to the stator circumferentially disposed around the primary axis, where at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to receive a fluid from a first engine component in the engine nacelle and wherein at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to pass the fluid to a second engine component in the engine nacelle.

A motor cooling system including, an engine nacelle defining a primary axis, a stator housing within the engine nacelle, a plurality of stator guide vanes attached to the stator circumferentially disposed around the primary axis, where at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to receive a fluid from a first engine component in the engine nacelle and wherein at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to pass the fluid to a second engine component in the engine nacelle.

A method, device and system for operating internal combustion engines with an increased pressure ratio and vehicle with this system. Internal combustion engines have a technically restricted pressure ratio, which limits the thermal efficiency. Gas turbines have so far had a maximum pressure ratio of 33:1, diesel engines have compression ratios of up to 23:1. An oxidizer is fed into the combustion chamber in (cold) liquefied condition under very high pressure. The fuel is also supplied in liquid form under high pressure. The pressure ratio of the oxidizer pump is 200, 500 or more. In the combustion chamber, the oxidizer and fuel react and expand to more than a thousand times the liquid volume. Depending on the fuel used, an expansion machine with a pressure ratio of around π=500 or more or an equivalent expansion ratio of ε=85 or more can be implemented.

A method, device and system for operating internal combustion engines with an increased pressure ratio and vehicle with this system. Internal combustion engines have a technically restricted pressure ratio, which limits the thermal efficiency. Gas turbines have so far had a maximum pressure ratio of 33:1, diesel engines have compression ratios of up to 23:1. An oxidizer is fed into the combustion chamber in (cold) liquefied condition under very high pressure. The fuel is also supplied in liquid form under high pressure. The pressure ratio of the oxidizer pump is 200, 500 or more. In the combustion chamber, the oxidizer and fuel react and expand to more than a thousand times the liquid volume. Depending on the fuel used, an expansion machine with a pressure ratio of around π=500 or more or an equivalent expansion ratio of ε=85 or more can be implemented.

An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.