| 摘要 |
A aircraft propulsion device called DiscThruster™ which creates thrust in the form of pressure thrust, as opposed to momentum thrust, wherein a thin round DiscThruster disc 2 spins about its disc rotation axis being driven by a turboshaft engine, wherein the disc 2 exhibits a series of ring-like concentric circumferential disc zones 4 on its flat surface, beginning from the innermost radius out to the circumferential edge of the disc 2, such that each disc zone 4 contains a plurality of interconnected components in series, including a fluid pump 22, a converging only sonic choking nozzle 23, and a fluid collector 24, wherein low sonic velocity two-phase working fluid 9 pressurized by a spinning centrifugal pump 22, passes through and sonically chokes in the nozzle 23 creating both pressure thrust and momentum thrust, and enters the external atmospheric pressure environment 8 where it travels some distance away before being captured by the circumferential scoop-like fluid collector 24 through centrifugal forces that cancel momentum thrust in the direction of pressure thrust, and is then redirected to the next adjacent radially outward disc zone 4, where the cycle is repeated until the fluid 9 reaches the radially outermost disc zone 4, where it is captured and recycled back to the radially innermost disc zone 4, such that no fluid 9 leaves the system. |
| 主权项 |
1. A method of producing pressure thrust propulsion, comprising of a working fluid, a fluid pumping means, a sonic choking nozzle, and a fluid collector means, where said working fluid enters said pumping means, is pressurized through a means and communicates with and passes through said nozzle while being sonically choked through a means, exits said nozzle into view of the external atmospheric pressure environment, where said working fluid communicates with said fluid collector means, that collects through a means and returns said working fluid back to said pumping means, wherein the improvement is lower specific fuel consumption propulsion. |
