| 摘要 |
<p>A multiple-fluid, multiple-substance, multiple-phase, multiple-pressure, multiple-temperature, multiple-stage turbine engine. In preferred embodiments, one or more fluids are supplied by passageways in the turbine shaft or supplied by non-shaft passageways, or both, through rotor passageways to multiple-phase, multiple-fluid, multiple- substance nozzles affixed to one or more perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies. The multiple perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies are preferably configured and located for multiple inlet and exit velocities of the nozzles, multiple inlet and exit pressures of the nozzles, or combinations thereof. The one or more fluids entering the turbine may each be a substance of single phase, or a substance of multiple phase, or a mix of the single-phase and/or multiple-phase conditions for two or more entrance fluids. Additionally, for two or more entrance fluids, these fluids may be at different thermodynamic conditions or characteristics. Also, for two or more entrance fluids, these fluids may be of different substances, provided that, if two or more of said substances are mixed at, in, before, after, about and/or upon exiting the nozzle(s), portion(s) of nozzle(s), set(s) of nozzles and/or combustion chamber-nozzle, then the resulting mixture has appropriate compatibility, especially where two or more substances are reacted to provide a motive force and/or to enhance an existing motive force and/or to modify or change the reaction, or portion thereof, of two or more mixed substances. The multiple-phase, multiple-substance and/or multi-fluid nozzles may be recessed in the turbine rotor surfaces, located at, on or about the turbine rotor surfaces, be integral with the turbine rotor surfaces, or extend from the turbine rotor surfaces, or combinations thereof. The multiple-phase, multiple- substance and/or multi-fluid nozzles may vary in number and/or size for the multiple rotor surfaces of the turbine. The multiple-phase and/or multi-fluid nozzle(s), portion(s) of nozzle(s), set(s) of nozzles and/or combustion chamber- nozzle unit(s) may be equipped with entrance shapes/profiles and/or exit shapes/profiles configured to enhance the efficiency of the nozzle(s), portion(s) of nozzle(s), set(s) of nozzles and/or combustion chamber-nozzle unit(s). The axis of the nozzle(s), portion(s) of nozzle(s), set(s) of nozzles and/or combustion chamber-nozzle unit(s) can have a three-dimensional acute angle with the direction opposite the tangential direction of rotation of the turbine, a three- dimensional acute angle with a radial axis of the turbine rotor, a three-dimensional acute angle with the axial axis of the turbine rotor (Le., the axis of rotation of the turbine shaft), or a combination thereof. The axis of the nozzle(s), portion(s) of nozzle(s), set(s) of nozzles and/or combustion chamber-nozzle unit(s) can be linear or curved, or a combination thereof. The vectorial direction of fluid(s) exiting a nozzle exit area may be altered or changed through the use of shroud(s), or other fluid deflection or fluid re-direction device(s)/method(s).</p> |
