Turbojet engine fan module wheel, including a plurality of blades made of composite material, each blade having a root assembled with a base distinct from the bases of the other blades, each base having a groove extending axially and opening out on the side of the upstream face and on the side of the downstream face, each root cooperating by axial interlocking in a form-fitting manner, for example in the shape of a dovetail, with the groove of the base, whereby the root is retained on the base along the radial and circumferential directions, and each base cooperates with at least one part configured to axially block the root within the groove of the base, whereby the root is retained along the axial direction.

The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter, thermodynamics, and continuum mechanics, providing generalized equations of fluid motion. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables efficient water-harvesting from air. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.

The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field.

The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field.

A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.

Supersonic jet engine includes a housing and an exhaust nozzle. Spike extends outwardly from the housing. Plurality of fans are arranged in an axial direction within the housing, each of the plurality of fans includes a plurality of fan blades. Plurality of turbines are included, and each of the plurality of turbines having a plurality of turbine blades and being arranged and coupled to a respective one of the fans in a radial direction. Plurality of radial compressors are located radially from the each of the plurality of turbines and are operable to drivingly rotate the respective turbine, which in turn rotates the respective fan. Plurality of electric motors are included, and each of the plurality of electric motors are coupled to a respective one of the plurality of radial compressors and drivingly rotating the respective radial compressor.

Supersonic jet engine includes a housing and an exhaust nozzle. Spike extends outwardly from the housing. Plurality of fans are arranged in an axial direction within the housing, each of the plurality of fans includes a plurality of fan blades. Plurality of turbines are included, and each of the plurality of turbines having a plurality of turbine blades and being arranged and coupled to a respective one of the fans in a radial direction. Plurality of radial compressors are located radially from the each of the plurality of turbines and are operable to drivingly rotate the respective turbine, which in turn rotates the respective fan. Plurality of electric motors are included, and each of the plurality of electric motors are coupled to a respective one of the plurality of radial compressors and drivingly rotating the respective radial compressor.

The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

By blending a quantity of synthetic cyclo-paraffinic kerosene fuel blending component comprising at least 99.5 mass % of carbon and hydrogen content and at least 50 mass % of cyclo-paraffin into kerosene base fuel, kerosene based-propulsion fuels can be upgraded to higher quality kerosene based-propulsion fuels such as jet fuel or rocket fuel to meet certain specification and/or increase volumetric energy content of the propulsion fuel.

By blending a quantity of synthetic cyclo-paraffinic kerosene fuel blending component comprising at least 99.5 mass % of carbon and hydrogen content and at least 50 mass % of cyclo-paraffin into kerosene base fuel, kerosene based-propulsion fuels can be upgraded to higher quality kerosene based-propulsion fuels such as jet fuel or rocket fuel to meet certain specification and/or increase volumetric energy content of the propulsion fuel.