RU2354841C2 - Jet propellant plant - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engines. The proposed jet propellant plant incorporates outer flaps and screw-like cellular round rotor made up of a set of bent trapezoidal interjointed tubular elements to add to extra propellant force for aerodynamic-body aircraft. The said plant comprises air intake front part (6), cylindrical central part (7) and rear tube (8). Front part (6) features an oval shape and is furnished, on its upper and lower sides, with guides (6.1) allowing the air passage. The plant comprises also a locking system (6.3) representing flat gates or a swinging pan (3). The lower part of front part (6) is partially closed, upward to the said guides, by sector (6.2).

EFFECT: fuel savings, lower level of contamination.

2 cl, 7 dwg

Description

The proposed invention relates to a jet propulsion system for the movement and stabilization of aircraft. This installation includes a system in the inner center of which is located a helical round cellular rotor connected to a high-speed internal combustion engine; its body has a set of holes and slots equipped with dampers, hatches and throttle dampers, allowing both to stabilize and balance the engine of the aircraft, and to facilitate the landing and take-off process, since such a design requires a rather small landing strip and relatively low speed.

BACKGROUND

In order to facilitate takeoff and landing processes for an airplane engine, two separate methods are used that cannot be used together. If necessary, in addition to the speed damper, a landing parachute may be used during landing; no auxiliary methods are needed to maintain the lifting force, but to ensure low production costs, new propellant internal combustion engines or jet engines can be installed.

DESCRIPTION OF THE INVENTION

A propulsion system with a helical rotor located at the center point of the product is described in detail in Patent PCT / ES 2004/000087, "Round Cellular Rotor", which is currently under patenting by the applicant Felix Sanchez Sanchez. It is an important tool in this technical solution and is designed to equip all types of flying aircraft. It is provided by an internal combustion engine with a large number of revolutions per minute (r.m.); air intake occurs in front of the aircraft at intervals between the rails. On the one hand, the air is taken in due to two effects: 1) due to the actual speed of the machine and 2) absorption or absorption created by a helical round cellular rotor. On the other hand, the throttle-type damper orientates the flow of this air in two different horizontal directions: the first position of the air intake, which is basic for the normal functioning of the aircraft; and the second position, the main purpose of which is to completely turn off the horizontal air intake, producing an instantaneous perpendicular change in the position of the throttle, which allows you to control the upward force through suction. This first housing is located in front of the rotor, the central nozzle of a cubic shape which was fixed in the aforementioned internal combustion engine and whose rotation is protected by the second housing of the product, which has a cylindrical tubular shell. The internal combustion engine is permanently installed in the third building, made in the form of a pipe with a conical base and a decrease in the pressure of the air leaving the conical base, increases the number of rotors, which is key for determining the speed of the aircraft. Due to this conical shape, the air pressure obtained by means of a helical round cellular rotor increases, the throttle type damper located in the outlet with a conical base is responsible for the orientation of the air in two different directions, backward as the main engine for the normal functioning of the aircraft and down as a jet of air, creating a supporting force and, thus, the balance behind the aircraft. These two oppositely directed forces were applied to the front (bottom) and rear (top) of the aircraft, creating a balance that allows the aircraft to fly at low speed and, therefore, facilitates landing on very small landing strips with a minimum speed (km / h). This even applies to very small aircraft that could land like helicopters, which is why there is a two-way shutter in the lower rear of the plane: the first for orienting the air stream, which is perpendicular to the throttle, closing the exit section of the air stream and creating a supporting source strength. In the second position (45 ° approximately), the air stream is directed in the opposite direction, providing the aircraft with lifting force, allowing it, once landing, to move without additional technical support. At the same time, cylinders with a conical base have small flaps on the back on one side, which in the open position allow the air jet to move left or right, depending on which flap is open, and cause the aircraft to land or take off, while 90% reduction in air pollution, which depends on stabilizers. All this contributes to the creation of shorter landing strips, which leads to the fact that the area of airports is increasing in width and decreasing in length, which will allow several planes to take off or land at the same time and also reduce the risks of take-off and landing by slowing down in both processes.

DESCRIPTION OF DRAWINGS

Figure 1 is a section on which you can see the complete support system of the propulsion system (1), as well as the stabilization of the aircraft by means of the head part (6) and extendable support rails (6.1). Air is drawn in at intervals left by the guides (12 guides are shown in the drawings) and the locking ring (6.3) shown at the back, connected to the suspended tray (3).

The lower part is partially covered by a cap (6.2), behind which there is a ring (6.4), from which 3 guides (6.5) extend, connected to a central nozzle of a cubic shape (6.6), which supports a guide bearing (11), which directly supports the axis (2.1) ) of the rotor (10), enclosed in a casing (7).

The axis (2.1) is inserted into the internal combustion engine (2), which rests on the support brackets (2.2) installed in the rear pipe (8), which contains small hatches on their outer sides, which are closed by two throttle valves (9). They can be located on one or both sides in order to be able to carry out orientational maneuvering at the end of this rear pipe, and below it lies an opening regulated by a shutter (5), which has in its central part a rotating pallet that acts as a throttle that closes downward or opens upward ( 4) for air outlet.

Figure 2 - a General view of Figure 1, on which you can see the guides (6.1) of the head part (6) connected to the ring (6.4), behind which there is a rotor covered with a casing (7), and the final outlet pipe of the air stream (8 ), also throttle valves responsible for orientation maneuvering.

Figure 3 - section "BB" Figure 1, on which it is possible to evaluate the sections of the guides (6.1) and the lower cap (6.2), ending with a ring (6.4), which has three equidistant struts (6.5) located from the periphery of the ring to the center, forming at their ends a nest (6.6) in which a guide bearing (11) is located; struts (12.1) securing the entire system to the aircraft (12).

Figure 4 shows a front view of "A" in Figure 1.

5 is a section "CC" in figure 1, showing the rear pipe (8) with a conical base and sections of the joints of the throttle valve (4) for air inlet and outlet and also the shutter (5) located in the lower part of the rear pipe (8).

6 shows a full view of an airplane (12) with aerodynamic bodies with propulsion systems (1), which are located under the wings.

7 is a front view of the aforementioned complete set of engines.

DESCRIPTION OF THE PREFERRED EMBODIMENT

The aerodynamic body, which creates translational motion with a helical round cellular rotor, consists of three cylindrical bodies: the first belongs to the head part (6) with an oval profile formed by a series of guides (6.1) and a throttle valve that closes in the region of the main air intake and is closed in bottom (6.3). This head part is connected to a second housing, consisting of a shell of a rotor casing (10) with a perfect cylindrical shape, which is not the subject of description here, since it is fully included in PCT / ES 2004/00087. The internal combustion engine (2) is mounted on an axis resting on the guides (2.1). The aerodynamic body (1) includes a third body or rear part (8) with a conical base with small hatches, swinging throttle valves (9) and, in its central part, a rotating tray (4) that can fully open or close the circular section of the body.

In the same position at the bottom, a multi-stage opening (5) is shown, whose purpose is to provide support by changing the direction of the air stream and allowing the aircraft to reverse when it is on the landing strip.

This jet propulsion system (1) for practical use is installed on an airplane in the amount of one, two, three or more copies; helical round mesh rotors act as generators to make it possible to move forward with less pollution and save fuel consumption. Thanks to various hatches, bolts and throttles, better balance and stability during maneuverable movements are achieved.

The purpose of this patent was clearly and thoroughly described in order to make it possible to operate, I declare it a new and my personal invention, with the exception of its minor details such as shape, size, materials and production technologies. They can be made of any geometrical regular or irregular shape, as well as re-adapted as part of an unchanged general idea.

Claims (3)

1. A jet propulsion system with external dampers, providing maneuvering of aircraft on the runway or the airport territory, with a helical round cellular rotor, consisting of a set of curved trapezoidal tubular elements interconnected, and providing auxiliary driving force for aircraft and other flying devices, with one or more aerodynamic bodies attached to the aircraft, and the head part (6) for air intake, cent the main part (7) in the form of a cylinder and the rear pipe (8), while the head part (6) of an oval shape is provided on the upper and lower sides with guides (6.1), which allow air to pass through, the locking system (6.3) in the form of flat gate valves or a swinging pallet (3), and the lower part of this head part (6) up to the guides is partially covered by a sector (6.2), which at the periphery covers most of the head part (6). 2. Jet engine installation according to claim 1, characterized in that a circular helical cellular rotor (10) is provided, closed by a central cylindrical part (7), the rotor forming a jet and resting on the head part (6) through a bearing (11), while the other side of the rotor axis (10) is supported by an internal combustion engine (2), supported by supporting brackets (2.2) and placed in the rear part (8), made in the form of a truncated cone. 3. Jet engine installation according to any one of claims 1 and 2, characterized in that the central part (7) is made in the form of a cylinder as a casing for the rotor (10), while the rear tube is made as part of a truncated cone and connected to the rotor casing moreover, this rear part is conical in shape with small hatches on its sides and with swinging dampers (9) of the throttle type and in its central part with a rotating tray (4) or flat valves designed to open or close the entire area of the circumference of the air inlet in h st body during maneuvering, and below the same position is provided a multistage valve (5).

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