An aircraft propulsion assembly, including a turbine engine comprising at least one gas generator configured to generate a main flow, which is supplied by a central jet to at least one power turbine, the central jet being surrounded by an outer fairing, and the power turbine driving, on the periphery thereof, at least one fan rotor. The aircraft propulsion assembly comprises first movable means which are arranged so as to divert at least some of the main flow from the central jet to the outside of the outer fairing and preferably upstream of the turbine engine so as to generate thrust reversal. An aircraft which uses the propulsion assembly, particularly on the rear tip of the fuselage of the aircraft.

Various embodiments may include a drive system for an aircraft comprising: an electrical generator; and an internal combustion engine with a gas expansion turbine. The generator includes a rotor rotating on a rotor shaft. The gas expansion turbine rotates on a turbine shaft. The rotor shaft and the turbine shaft are couplable to transmit torque such that the internal combustion engine can deliver mechanical energy to the generator. A supply air stream impinges at least one component of the generator.

An energy-saving device for rapidly and infinitely compressing air includes housing, rotating shaft, spiral fan blade, power unit, transmission gear set, and fixing bracket, it is characterized in that the housing is connected with the fixing bracket, the rotating shaft with the spiral fan blade has upper and lower transmission gear sets, the power unit provided on the fixing bracket rotates the rotating shaft through the transmission gear set, so that a tornado-like airflow is generated in the space between the housing and rotating shaft, the devices can be stacked infinitely, so that the airflow is continuously accelerated to produce a powerful air thrust. The present invention can be widely used in aircraft and other vehicles, weapons, and protection and other aspects.

A rotary engine system comprises a first-stage working unit and a second-stage working unit configured to complete two passes of work done simultaneously on the same concentric shaft, and the design of two passes of work is based on the work of the pressure on the pistons and the work done by the turbine through the impulsion of the pressure gas and the expansion of the moving mass released by the turbine. The mode of doing work in two cavities is adopted to complete two passes of work in different cavities, namely the work done under pressure and the work done with the mass released by the turbine, thereby realizing twice utilization of total energy. The new structure of the engine system is capable of improving the engine efficiency obviously.

A rotary engine system comprises a first-stage working unit and a second-stage working unit configured to complete two passes of work done simultaneously on the same concentric shaft, and the design of two passes of work is based on the work of the pressure on the pistons and the work done by the turbine through the impulsion of the pressure gas and the expansion of the moving mass released by the turbine. The mode of doing work in two cavities is adopted to complete two passes of work in different cavities, namely the work done under pressure and the work done with the mass released by the turbine, thereby realizing twice utilization of total energy. The new structure of the engine system is capable of improving the engine efficiency obviously.

A toroidal lift force engine is provided. Illustratively, the toroidal lift force engine operates in an enclosed environment without heat and/or expelling particles of any kind, utilizing asymmetric pressure distribution on lift turbine blades solely to generate thrust with the normal component of this lift force, while using the tangential component of this lift force to drive accessories, provide control to the fluid velocity, and/or provide motivation of the fluid's flow. The toroidal lift force engine may be utilized to generate thrust, heat and/or electricity for powering vehicles, homes, etc.

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving gas turbine engine reliability through an electric motor backup system for cooling features of the turbine section.

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving gas turbine engine reliability through an electric motor backup system for cooling features of the turbine section.

A steam turbine exhaust chamber defining therein an exhaust passage through which steam having passed through a last-stage blade of a steam turbine is introduced to a condenser includes: a casing including an outer peripheral wall portion formed on an outer peripheral side of the exhaust passage; a bearing cone disposed on a radially inner side of the outer peripheral wall portion; and at least one bypass passage carrying a part of steam flowing through the exhaust passage from a high-pressure portion of the exhaust passage to a low-pressure portion of the exhaust passage or to the condenser, The at least one bypass passage includes a high-pressure-side opening formed in the bearing cone and a low-pressure-side opening facing steam having a lower pressure than steam facing the high-pressure-side opening.

A steam turbine exhaust chamber defining therein an exhaust passage through which steam having passed through a last-stage blade of a steam turbine is introduced to a condenser includes: a casing including an outer peripheral wall portion formed on an outer peripheral side of the exhaust passage; a bearing cone disposed on a radially inner side of the outer peripheral wall portion; and at least one bypass passage carrying a part of steam flowing through the exhaust passage from a high-pressure portion of the exhaust passage to a low-pressure portion of the exhaust passage or to the condenser, The at least one bypass passage includes a high-pressure-side opening formed in the bearing cone and a low-pressure-side opening facing steam having a lower pressure than steam facing the high-pressure-side opening.