P3 Technologies, LLC

Rocket Technology Holdings, LLC

Brandon A Demski

Philip C Pelfrey

Robert W Sanders

A centrifugal impeller includes a pressurized cavity that reduce the stresses in the impeller disk, blades, shroud and hub as the stiffness of the rotor is not compromised while weight is reduced across the component and peak stress regions are shifted across the part. The centrifugal impeller can be a centrifugal pump or a radial inflow turbine. The pressurized cavity is formed between a forward wall and an aft wall of the impeller and can include a plurality of orifices that open into the cavity to supply pressure from low to high pressure location around the impeller. Annular rings can be used within the cavity to stiffen the impeller. Radial and tangential stiffening ribs can be used on the two walls to stiffen the impeller.

High-speed pressurized impeller disk

A self-contained actuating magnetic pump (SCAMP) having an inlet valve and discharge valve, a piston, a compression cavity, an electromagnetic coil, a frame, and an armature to drive the piston. In one embodiment, the electromatic coils are isolated from the working fluid. In one embodiment, the SCAMP includes a housing that allows for thermal transfer from the electromagnetic coil to the working fluid. In one embodiment, the SCAMP includes a control unit that enables operation of the SCAMP in a power mode, a coast mode, and a retraction mode.

Self-contained actuating magnetic pump

A monopropellant rocket engine in which nitrous oxide is the propellant includes a catalyst bed on an end of a diverging combustion chamber to inject a first flow of monopropellant to ignite the monopropellant, followed by a series of additional monopropellant injections along the diverging combustion chamber where the previously injected monopropellant decomposes to be used to ignite the downstream injected monopropellant. When all monopropellant has been decomposed, the monopropellant is passed through a throat and nozzle to produce thrust. A control valve is used to regulate an amount of monopropellant injected at each point in order to regulate an amount of thrust.

Monopropellant cascade rocket engine

A multiple channel diffuser having an annular shaped radial inlet and a tangential outlet, and a plurality of separated diffuser channels connecting the radial inlet to the tangential outlet such that a flow does not mix. A tap-off passage can be used to provide flow to a gas generator or a preburner. A cross-over passage can also be used to provide flow from a first diffuser to a second diffuser.

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Jupiter, FL, United States of America

Brandon A Demski