FR2616850A1 - Motorised propulsion unit with a tractive propellor and with reaction - Google Patents

Abstract

The invention relates to a motorised propulsion unit with a rotary engine, part of the energy of which is converted into the form of direct reaction in the atmosphere. It consists of a rotary engine 1, a tractive propellor 2, of items of equipment 3, a ring 4 mounted concentrically around the propellor, the engine and the items of equipment and an orientable fixture 5. A certain quantity of air is sucked in by the propellor at the region of the air inlet 6 of the ring. This quantity of air is then accelerated by a Venturi effect inside the ring forming an ejection nozzle 7 thus creating a thrust which is added to the traction of the propellor. This motorised propulsion unit according to the invention is particularly intended to equip land and air vehicles.

Description

 The present invention relates to a rotary powertrain with an internal combustion engine, part of the energy of which is recovered and transferred in the form of a direct reaction in the atmosphere.

 Currently, CE jet engines fall into four main categories: turbojet engines with or without a propeller, pulsoreactors, ramjet engines and rocket engines.

 The present invention is not akin to these engines which are not of internal combustion and generally operate by direct reaction in the atmosphere.

 This reaction powertrain according to the invention is not similar to the "streamlined propellers" which are fitted to certain hovercraft, air-boats or aircraft which are propellant "protection" devices.

 The purpose of the inventive inventive is to propel a powertrain with an internal combustion engine, that is to say with a motor directly transforming the energy of the fuel into mechanical energy, equipped with a tractive propeller and a ring forming " air inlet "and" ejection nozzle ".

 This jet powertrain according to the invention is characterized in that this ring is mounted concentrically around the assembly constituted by the propeller and by the engine and its equipment, allowing a flow of air to be sucked in, d 'to be accelerated and to be ejected, thus creating a power by direct reaction in the atmosphere.

 The ring is constituted in its first third by an air inlet in the form of a funnel and in its other two thirds by the cylindrical or slightly flared part towards the rear which acts as an ejection nozzle.

 Advantageously, the flow rate of the air flow in the ring can be modified as a function of the adjustment of the propeller blades.

 It should be noted that the power thus obtained by direct reaction in the atmosphere and which is expressed in daN of thrust, is added to the tractive power of the propeller alone.

 The internal combustion engine used is a rotary engine constituted by one or more trochoids and by one or more rotors, for reasons of compactness, light weight and low level of vibrations. Indeed, the invention if it remains conceivable, would become difficult to achieve with an internal combustion engine with reciprocating pistons which is both heavy, bulky and generator of numerous and strong vibrations.

 The equipment necessary for the normal operation of the engine: pumps, carburetion, lubrication, turbocharging, electrical generation, etc., are imperatively housed in the cowling of said engine and in the extension of the latter in order to make possible the application of the invention.

 By design, this jet powertrain can equip all kinds of land and air vehicles and it can be placed as desired: above, in front of, behind or on the side or other surfaces of said vehicles.

 The attachment system or "engine mount" is a cylindrical metal pylon which acts as an axis of rotation; which makes the power train adjustable. This last feature is advantageous because it allows the air flow to be oriented according to the needs of the vehicles thus equipped.

The accompanying drawings illustrate the invention
Figure 1 shows, front view, the propeller mounted on the engine and surrounded by the ring.

 Figure 2 shows, in section, the operation of this jet powertrain.

The jet powertrain according to the invention, shown in Figures 1 and 2 includes
- an engine (1), the combustion chambers of which are trochoids equipped with rotors and a central crankshaft. This engine (1) of a known model is commonly called "rotary engine" or "rotary piston engine"
- a pulling propeller (2) of a known model which is fixed to one end of the engine crankshaft (1)
- equipment (3) necessary for the normal operation of the engine (1) pumps, carburetion, lubrication, turbocharging, electrical generation, and which are housed in the tapered cowling of said engine (1) and in the extension of the latter
- a ring (4) which is mounted concentrically around the assembly made up by the propeller (2), the motor (1) and the equipment (3)
- A steerable "engine mount" (5) allowing the installation of the powertrain & reaction on land and air vehicles in the same way as the turbojets are installed on airframe.

This reaction powertrain according to the invention operates as follows as shown in Figure 2
A certain amount of air is sucked in by the pulling propeller which is activated by the internal combustion engine. This tractive propeller is located inside the ring, approximately in the first third. This first third of the ring is an air inlet (6) in the form of a funnel which promotes the suction carried out by the propeller. The air is then channeled into the cylindrical part flared backwards which constitutes the nozzle (7).

 There is thus recovery of the air flow sucked in by the pulling propeller and this results, on the one hand, in an acceleration of the air flow due to the "Venturi" effect and on the other hand, a direct reaction in the atmosphere at the outlet of the nozzle-shaped ring.

 With an appropriate propeller profile and ring profile, it is possible to increase the acceleration of a mobile equipped with such a power train, by almost 30%. This increase in acceleration is in addition to the acceleration capacity of the actual propeller.

 For such a powertrain, the power is expressed not only in horsepower or watt but also in Newton of thrust. This thrust is the result of the amount of air movement created by the propeller and its ring.

 In the aeronautical field, this jet powertrain has many advantageous features, both technically and economically.

The flow rate of the air flow in the ring can be modified according to the adjustment of the propeller blades
- in the lower layers of the atmosphere, the air drawn into the ring is denser and a small propeller pitch will promote the aerodynamic performance of the assembly for use of the aircraft on the climb;
- at altitude, the air sucks in the ring is less dense and will have a faster flow; a large propeller pitch will promote the aerodynamic performance of the assembly for use of the aircraft while cruising.

 The manufacturing cost of such a powertrain is approximately five times less than that of an eQuiyalente thrust turbojet.

 It consumes six to seven times a month than this same turbojet. As a result, the range and the range of an air vehicle equipped with a powertrain according to the invention are increased in the same proportions.

 He is silent; about six to seven times quieter than propeller or jet engines of equivalent power.

 Its weight is half that of a traditional propeller motor of the same power.

 Its size is reduced, its level of vibrations is low, which favors mounting on all aircraft cells.

Claims (8)

 1) Powertrain constituted by an internal combustion engine (1), by a tractive propeller (2) and by equipment (3) of known models, characterized in that it is equipped with a ring (4) which is mounted concentrically around the assembly constituted by the engine, the hirlice and the equipment, allowing a flow of air to be sucked in, to be accelerated and to be ejected, thus creating a power by direct reaction in the 'atmosphere.  2) Powertrain according to claim 1, characterized in that the ring (4) is constituted in its first third by an air inlet (6) in the form of a funnel and in its other two thirds by a cylindrical part and slightly flared towards the rear which acts as an ejection nozzle (7).  3) Powertrain according to claim 1, characterized in that the flow rate of the air flow in the ring (4) can be modified according to the adjustment of the propeller blades.  4) Powertrain according to claim 1, characterized in that the power per reaction thus obtained and which is expressed in thrust, is added to the pulling power of the propeller itself.  5) Powertrain according to claim 1, characterized in that the internal combustion engine (1) is a rotary engine constituted by one or more trochoides and by one or more rotors.  6) Powertrain according to claim 1, characterized in that all the equipment (3) necessary for the operation of the engine (1) are placed in the same tapered cowling of said engine and in the extension of the latter.  7) Powertrain according to claim 1, characterized in that in is orientable around its fixing axis constituted by a cylindrical metal pylon (5).  8) Powertrain according to claim 1, characterized in that by its design, it can equip all kinds of land and air vehicles and that it can be placed, as desired: above, in front, behind, or on surfaces side or other, of said vehicles.