A system includes a steam turbine. The steam turbine includes an outer casing and an inner casing disposed within the outer casing. The inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion. The steam turbine also includes an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage. The steam turbine further includes at least one reaction stage having multiple blades. The at least one reaction stage is integrated within the inner casing.

These new thrusters simultaneously use wheels of the CARPYZ THRA Turbo Powered Helicopter Reactor type and wheels of the CARPYZ TaG Bucket Turbines type or wheels of the CARPYZ TaC Scoop Turbines type, representing real global technological breakthroughs for fluid mechanics. They use, upon vertical take-off of the aircraft, propellers driven by electric motors and temporarily use the required additional high vertical axial thrust that is then supplied by the reactors of the THRA wheels, which also use an energetic fluid. The CARPYZ type thrusters, due to the low diameter and weight afforded thereto, are progressively horizontally inclined and the force of the reactors is progressively replaced by that of the propellers, which then supply the flows required in order for the aircraft to travel horizontally using wings that rely on the lift of the fluid, like airplanes. Photovoltaic wings are then deployed that are like butterfly wings and this economical solution will enable voyages over longer distances. It really is the safe mass market vertical take-off car of the future that can be achieved in less than 10 years by virtual of the new CARPYZ type thrusters, the little things change everything!

A steam turbine is provided. The steam turbine includes a housing, a first steam inlet configured to discharge a first steam flow within the housing, and a second steam inlet configured to provide a second steam flow. A rotor and stator are coupled to the housing and configured to form a first flow path therebetween and in flow communication with the first steam flow. The rotor includes a plurality of blades coupled to the rotor, at least one root of the plurality of blades has a first side, a second side and a passageway coupled in flow communication to the first side and the second side. The passageway is configured to receive the second steam flow within the at least one root. The at least one root includes an angel wing configured to seal the second steam flow from the first flow path.

An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor provides a supplementary energy to the compressor.

A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15.

A steam turbine system 1 includes a steam turbine 10including a plurality of rotor blades 16; a first mixed steam supply pipe 21 that supplies the steam, which is supplied from a steam supply source 40 capable of supplying the steam with fluctuating pressure, to an upstream stage Sa within the casing 11; a second mixed steam supply pipe 22 that supplies the steam to the second stepped part Sb; an adjusting unit 25 that adjusts a flow rate of the steam supplied to the first stepped part Sa and the second stepped part Sb; and a control unit 30 that controls the adjusting unit 25 on the basis of a differential pressure between a pressure P0 of the steam supplied from the steam supply source 40 and a pressure in the first stepped part Sa.

System for electrical energy generation from steam comprising at least one stage, each stage including: a steam-driven rotating toroidal ring; a housing comprising a toroidal cavity for containing the rotating toroidal ring, the housing further comprising at least one steam inlet, the housing further comprising a plurality of steam outlets for removing pressurized steam from the channels for at least a second portion of rotation of the rotating toroidal ring within the toroidal cavity; at least one bearing arrangement comprised by or attached to the housing within the toroidal cavity; and at least one pair of electrical coils, each electrical coil located on the outer surface of the housing at locations diagonally opposite from the other coil of each pair across the axis of the minor radius of the toroidal cavity and within the specific region where a time-varying magnetic field will occur as the rotating toroidal ring rotates.

A turbine engine such as a pusher fan engine is provided. This turbine engine includes a nacelle with a bypass flowpath. A fan rotor is configured to propel air out of the bypass flowpath. A plurality of guide vanes are configured to direct the air to the fan rotor.

An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

A system is provided for a gas turbine engine. This gas turbine engine system includes a flowpath wall and a deflector. The flowpath wall includes a surface and an opening to a blind aperture. The surface forms a peripheral boundary of an internal engine flowpath. The opening is disposed in the surface. The blind aperture extends vertically into the flowpath wall from the opening. The deflector projects vertically out from the flowpath wall into the internal engine flowpath. The deflector is configured to deflect gas flowing within the internal engine flowpath over the opening.