Rotational ducted fan (RDF) propulsion system

Abstract

In accordance with the present invention, an embodiment of a rotational ducted fan motor comprises a monolithic rotational ducted fan rotor, an electric propulsion system, a static aft-shroud comprising electrochemical-energy-storage, and an engagement system. The rotational ducted fan rotor is the portion of a ducted fan motor comprising a propeller, a duct, and a center hub, and having the effect of increasing the pressure difference from upstream to downstream of the propeller. The electric propulsion system comprises permanent magnets affixed to the rotational ducted fan rotor, repelling magnetic coils affixed to the static aft-shroud and electrical power provided by the electrochemical-energy-storage comprised within the aft-shroud.

Description

RELATED APPLICATIONS[0001]The present application is a continuation application of U.S. patent application Ser. No. 14 / 095,737, filed Dec. 3, 2013, for ROTATIONAL DUCTED FAN, OR RDF FAN MOTOR, by Devin Glenn Samuelson, included by reference herein and for which benefit of the priority date is hereby claimed.FIELD OF THE INVENTION[0002]The present invention relates to an aircraft propulsion system, and more particularly to a novel rotational inlet shroud, and additionally to an energy storage and maintenance system.BACKGROUND OF THE INVENTION[0003]For each barrel of crude oil refined, approximately only 4 gallons of jet fuel are realized. Specific to aircraft fuel, there is a limited global supply of the natural resource of carbon based fuels such as oil. In consideration of other hybrid systems or alternative biofuel systems, the problem of supply and dependence on these types of natural resources creates new economic challenges such as increased consumable costs due to competing ma...

AI Technical Summary

Benefits of technology

The present invention provides a rotational ducted fan motor that includes a monolithic rotor with a static aft-shroud that includes electrochemical-energy-storage. The motor increases the pressure difference from upstream to downstream of the propeller. The electric propulsion system includes permanent magnets affixed to the rotor and repelling magnetic coils affixed to the static aft-shroud. The invention also provides a machine that converts electrical energy to thrust, creates a fluid pressure difference, converts electrical power into mechanical rotational work with magnetic fields, and utilizes heat energy created from electrochemical activation. The invention also provides a method for reducing aircraft non-operational down-times with interchangeable rechargeable electrochemical storage duct segments.

Problems solved by technology

Specific to aircraft fuel, there is a limited global supply of the natural resource of carbon based fuels such as oil.

In consideration of other hybrid systems or alternative biofuel systems, the problem of supply and dependence on these types of natural resources creates new economic challenges such as increased consumable costs due to competing markets, consumable shortages, or even climate disruptions.

Given the current path as the global economy increases the supply and demand of oil creates significant risks for economic stability internationally.

This strain stems from an imbalanced use of natural resources and too high of dependence on non-renewable energy sources.

The carbon footprint of aircraft is negatively impacting the environment from both an atmospheric output of propulsion exhaust, and the extraction and refinery processes of petroleum or biofuels.

Other problems that exist with combustion type systems include design restrictions to accommodate a safe combustible containment structure that facilitates the need for only using static fluid containment systems, thus limiting efficiency to be achieved primarily through focused attention to fluid density, achieved through compressors, entropy, and static nozzle designs historically.

No other solutions in existence today address the three problems that the rotational ducted fan propulsion motor addresses.

The use of a static inlet shroud of traditional gas or electric ducted fan motors does not allow the maximum pressure differentials to be achieved between the inlet and the aft exhaust of the system.

Additionally, it is common for traditional gas or electric ducted fan motors and propeller propulsion systems to experience efficiency losses at the outer blade tips which results in axial propulsive thrust losses.

The operational costs for current carbon fueled combustive propulsion systems are extravagant, for example, with 150 passenger aircraft consuming nearly 15 gallons per minute of a non-renewable fuel source will have economic consequences to future generations, combustive propulsion systems generate noise that creates weight inefficiencies since noise reduction becomes an integral part of the design, and reverse thrust systems are required.

Traditional electric ducted fan motors rely on a separate battery source which results in energy losses through wire resistance caused from separating batteries or stored energy some distance away from its point of use.

Traditional electric fan motors have a static shroud and a dynamic hub which the aero foil blades are attached, which contributes to airflow energy losses at the blade tips, similarly to those losses experienced by combustive propulsion systems.

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