阅读说明：本技术 除压式发动机 (Pressure-removing type engine ) 是由 李晓亮 于 2021-07-26 设计创作，主要内容包括：本发明开公了一种包括做功能部分(1)、泄力部分(2)、吸能部分(3)和支承部分(4)的除压式发动机,安在水(1-5)中的水泵(1-1),将水池(1-4)中的水(1-5)送到三通(1-3)上,水(1-5)从三通(1-3)的一个出口喷向挡板(3-1)上,另一个出口将水(1-5)喷向后方；其它零部件将挡板(3-1)受到的力传到飞机上；而向后喷的水(1-5)受到安在上方出来的水(1-5)的冲击,使得向后面喷射水的速度减小；飞机受到向前的推力而向前飞行。由于水比空气比重大,所以,飞机受到的推力大,工作效率高,能耗小,飞行航程远,载荷大。(The invention discloses a pressure-removing type engine which comprises a working function part (1), a force release part (2), an energy absorption part (3) and a supporting part (4), wherein a water pump (1-1) arranged in water (1-5) sends the water (1-5) in a water pool (1-4) to a tee joint (1-3), the water (1-5) is sprayed to a baffle (3-1) from one outlet of the tee joint (1-3), and the water (1-5) is sprayed to the rear part from the other outlet; other parts transmit the force received by the baffle (3-1) to the airplane; the backward sprayed water (1-5) is impacted by the water (1-5) arranged above, so that the speed of the backward sprayed water is reduced; the aircraft is subjected to forward thrust to fly forward. Because the specific gravity of water is greater than that of air, the aircraft is subjected to large thrust, high working efficiency, low energy consumption, long flight range and large load.)

1. A pressure-removing type engine is characterized in that: the water (1-5) is placed in the water pool (1-4), when the water (1-5) is pressurized and sent to the tee joint (1-3) by the water pump (1-1), one end of the tee joint (1-3) is sprayed forwards and is shot to the fixed baffle (3-1), and the other end is sprayed backwards; the backward sprayed water (1-5) has the speed reduced to the back under the impact of the water (1-5) sent by the discharge pump (2-1) sprayed from the right angle (2-5); the airplane is subjected to forward acting force more than backward acting force; the aircraft flies forwards under the effect of the resultant force.

2. A pressure-removing type engine is characterized in that: the water (1-5) is placed in the water pool (1-4), when the water (1-5) is pressurized and sent to the tee joint (1-3) by the water pump (1-1), one end of the tee joint (1-3) is sprayed upwards and shot to the fixed baffle (3-1), and the other end is sprayed downwards; the downward sprayed water (1-5) has the speed reduced downward under the impact of the water (1-5) sent by the discharge pump (2-1) sprayed from the right angle (2-5); the airplane is subjected to an upward acting force which is larger than a downward acting force; the total downward force of the aircraft under the action of the resultant force is reduced, and the traveling speed of the aircraft is increased.

3. A pressure-removing type engine is characterized in that: water (1-5) is placed in a water pool (1-4), when a water pump (1-1) pressurizes the water (1-5) and sends the water to a tee joint (1-3), one end of the tee joint (1-3) sprays forwards to shoot at a fixed baffle (3-1), the other end sprays backwards to spray the water (1-5) backwards; when the water pump (1-1) pressurizes and sends the water (1-5) to the tee joint (1-3), one end of the tee joint (1-3) sprays upwards to shoot at the fixed baffle (3-1), and the other end sprays downwards; in the middle, the water (1-5) sprayed backwards by the tee joint (1-3) is converged with the water (1-5) sprayed downwards by the other tee joint (1-3); the merged water (1-5) is acted on by the water (1-5) sprayed from the right angle (2-5) at the back. At this point, the speed of the aircraft will be greatly increased. The load to be shipped also increases.

4. The pressure-relief engine according to claim 1, 2 or 3, characterized in that: the baffle (3-1) is fixed on the supporting frame (3-2), and the supporting frame (3-2), the water pool (1-4) and the outer supporting body (3-3) are connected by a bolt (3-4) and a nut (3-5); the water pump (1-1) is connected with the water pipe (1-2) through a bolt (1-6) and a nut (1-7), and the water pipe (1-2) is connected with the tee joint (2-3); the pressure relief pump (2-1) is connected with the connecting pipe (2-6) through a bolt (2-7) and a nut (2-8), the upper connecting pipe (2-6) and the lower connecting pipe (2-6) are connected with the main pipe (2-2) through a tee joint (2-3), the upper connecting pipe (2-6) is connected with the branch pipe (2-4) through a right angle (2-5), and the branch pipe (2-4) is connected with the right angle (2-5).

5. The pressure relief engine according to claim 1, 2, 3 or 4, wherein: the vertical rod (4-1-2) is welded in the water pool (1-4), and the other end of the vertical rod (4-1-2) is welded with the cross rod (4-1-1); after the semicircular cover (4-1-4) covers the main pipe (2-2), the bolts (4-1-5) and the nuts (4-1-6) are arranged on the cross rod (4-1-1), the branch rods (4-1-3) are welded on the cross rod (4-1-1), and after the semicircular cover (4-1-4) covers the water pipe (1-2), the bolts (4-1-5) and the nuts (4-1-6) are arranged on the branch rods (4-1-3); one end of the bracket (4-2-1) supports the water pool (1-4), and the other end is arranged on the base (4-2-3) through a bolt (4-2-2).

6. The invention is not limited to aircraft, but is applicable to automobiles, ships, trains, airships, flying discs, satellites, rockets, missiles and space shuttles.

The first, the field:

the present invention relates to an engine for propelling an aircraft.

Secondly, background:

existing aircraft engines, one of which is propeller-type; in addition, there are also jet systems. But they are all reactive with the latter air. Because the air can flow and has compressibility, the air has small reaction after being sprayed backwards, low working efficiency, large energy consumption, short flight range and small load.

The invention content is as follows:

the invention aims to solve the problems that: a new method is found, air is not used as an acting force object, and the working efficiency of the airplane is higher than that of the existing engine, the energy consumption is low, the flight range is long, and the load is large.

In order to solve the above problems, the operating principle of the pressure-removing engine of the present invention is: water with certain pressure is sprayed forwards and backwards simultaneously, the water sprayed forwards impacts the fixed baffle plate, the force impacting on the baffle plate is transmitted to the airplane through the fixing piece, the water impacting backwards is impacted by the water from the side surface and the upper surface and the lower surface, the speed of the water impacting backwards is reduced, and therefore the forward acting force of the airplane is larger than the backward acting force of the airplane. The aircraft is sailing forward. According to the principle, the technical scheme of the invention is as follows: water is put in the water tank, the water pump is put in the water, one end of the water pipe is connected with the water pump, and the other end of the water pipe is connected with the tee joint; the pressure relief pump is also placed in the water, and the water pumped by the pressure relief pump is transferred to the right angle by other parts; one end of the water from the tee joint impacts the baffle plate in the front, and the water impacted by the other end of the water from the tee joint is in the rear; the water sprayed out from the right angle just impacts the water impacted backwards from the tee joint from the upper part downwards, and the speed of the water impacted backwards in the tee joint is reduced. On which the work pieces are supported and fixed by parts of the carrier part.

After the method is adopted, the specific gravity of the water is more than one thousand times that of the air, the compressibility and compressibility of the water are very small, and the fluidity of the water is smaller than that of the air, so that the method has high working efficiency, small energy consumption, long flight range, high flight speed and large load; meanwhile, the noise is low, and the processing is convenient when a fault occurs.

Because the structure can also be used for pushing upwards, the weight of the whole machine can be reduced, the flying speed is increased, and the load of the airplane is improved.

Because of the many advances this method can be used not only on board, but also on space shuttles, automobiles, boats, trains, airships, flying discs, satellites, rockets, and missiles.

Description of the drawings:

FIG. 1 is an assembly view of a first embodiment of a compression-release engine 1 according to the present invention.

Fig. 2 is a partial structure view of the pressure-reducing engine 1 according to the first embodiment of the present invention.

Fig. 3 is a partial structure view of the second embodiment of the pressure-reducing engine 2 of the present invention.

Fig. 4 is a partial structure view of the pressure-reducing engine 3 according to the present invention.

Example (b):

in the embodiment 1 shown in the attached drawings 1-2, the pressure-removing type engine comprises a working part (1), a force-releasing part (2) and an energy-absorbing part (3), wherein the working part (1) comprises a water pump (1-1), a water pipe (1-2), a tee joint (1-3), a water pool (1-4), water (1-5), a bolt (1-6) and a nut (1-7); the stress relief part (2) comprises a stress relief pump (2-1), a main pipe (2-2), a tee joint (2-3), a branch pipe (2-4), a right angle (2-5), a connecting pipe (2-6), a tee joint (2-7), a bolt (2-8) and a nut (2-9); the energy absorption part (3) comprises a baffle (3-1), a support frame (3-2), an outer support body (3-3), a bolt (3-4) and a nut (3-5); the bracket part (4) comprises an inner bracket (4-1) and an outer bracket (4-2); the inner support (4-1) comprises a cross rod (4-1-1), a vertical rod (4-1-2), branch rods (4-1-3), a semicircular cover (4-1-4), bolts (4-1-5) and nuts (4-1-6); the outer support (4-2) comprises a support (4-2-1), a bolt (4-2-2) and a base (4-2-3). The water pump (1-1) is placed at the bottom of the water pool (1-4), the water (1-5) is placed in the water pool (1-4), the water pipe (1-2) is connected with the water pump (1-1) through the bolt (1-6) and the nut (1-7), and the other end of the water pipe (1-2) is connected with the tee joint (1-3); the pressure relief pump (2-1) is placed at the bottom of the water pool (1-4), the pressure relief pump (2-1) is connected with the connecting pipe (2-6) through a bolt (2-7) and a nut (2-8), two ends of the tee joint (2-3) are connected with the connecting pipe (2-6), the other end of the tee joint is connected with the main pipe (2-2), the connecting pipe (2-6) is connected with the right angle (2-5), the other end of the right angle (2-5) is connected with the branch pipe (2-4), the other end of the branch pipe (2-4) is communicated with the right angle (2-5), and a water outlet at one end of the tee joint (1-3) is arranged below the right angle (2-5); the main pipe (2-2) is communicated with another tee joint (2-3), and then the structure is the same as the structure, and five groups are provided. The baffle (3-1) is welded on the supporting frame (3-2), the baffle (3-1) is arranged at the outlet of the tee joint (1-3), the supporting frame (3-2), the water pool (1-4) and the outer supporting body (3-3) are connected through bolts (3-4) and nuts (3-5), and the outer supporting body (3-3) is arranged on the base (4-2-3) through the bolts (3-4); the vertical rod (4-1-2) is welded on the water pool (1-4), the other end of the vertical rod (4-1-2) is welded with the cross rod (4-1-1), the semicircular cover (4-1-4) covers the main pipe (2-2), the bolt (4-1-5) and the nut (4-1-6) are arranged on the cross rod (4-1-1), the branch rod (4-1-3) is welded on the cross rod (4-1-1), the semicircular cover (4-1-4) covers the water pipe (1-2), and the bolt (4-1-5) and the nut (4-1-6) are arranged on the branch rod (4-1-3); one end of the bracket (4-2-1) is supported on the water pool (1-4), and the other end is arranged on the base (4-2-3) by a bolt (4-2-2). When the engine is used specifically, the engine is placed in an airplane, a water pump (1-1) and a force release pump (2-1) are started, water (1-5) flows to a tee joint (1-3) from a water pipe (1-2) under the action of the water pump (1-1), the water (1-5) is sprayed to the front and back directions of the tee joint (1-3), one direction is sprayed to a baffle (3-1), and the other direction is sprayed to the back. On the other hand, the pressure relief pump (2-1) enables water (1-5) to pass through each main pipe (2-2), each connecting pipe (2-6), a right angle (2-5), a branch pipe (2-4) and another straight pipe (2-5) from the connecting pipe (2-6), the water (1-5) is sprayed out from each straight pipe (2-5), the sprayed water (1-5) is just converged with the water (1-5) sprayed out from the tee joint (1-3) once, and the spraying line of each water (1-5) is shown as a dotted line in figure 1; the impulsive force of the water (1-5) sprayed backwards from the tee joint (1-3) is reduced once, and after the water (1-5) sprayed backwards from the tee joint (1-3) is converged for a plurality of times, the backward spraying force is finally greatly reduced. The force acting on the baffle (3-1) is very large, and the force is transmitted to the airplane after being transmitted by a plurality of parts; therefore, the aircraft receives a greater force pushing forward than pushing backward, thereby causing the aircraft to sail forward.

In the second embodiment shown in fig. 1 and 3, it is different from the first embodiment in that: the direction of the water (1-5) discharged from the tee joint (1-3) is not the original direction but is vertical to the original direction, the baffle (3-1) is arranged above the tee joint (1-3), and the water (1-5) sprayed out from the right angle (2-5) pushes and presses the water (1-5) sprayed out from the lower part of the tee joint (1-3); this causes the aircraft to experience an upward thrust greater than a downward thrust, thereby achieving an upward thrust. Due to this force, the downward pressure of the aircraft weight is reduced. Here, if the upward thrust is equal to the total weight of the aircraft, the speed of the aircraft is increased to the speed of light. When the total downward force of the aircraft is very small, the aircraft will be greatly increased from the existing speed. The aircraft load can also be increased.

In the third embodiment shown in fig. 1 and 4, it is different from the 1 st and 2 nd embodiments in that: has a pushing force pushing forward and also has a pushing force pushing upward; meanwhile, in the forward pushing part, the water (1-5) sprayed backwards by the tee joint (1-3) and the water (1-5) sprayed downwards by the tee joint (1-3) are mutually converged in the upward pushing part, so that the backward and downward forces of the water (1-5) are very small and the forward and upward forces are very large under the action of the water (1-5) sprayed by the other straight pipes (2-5). The effect is better than in the previous two embodiments.

The invention is not limited to the above forms, when the embodiment 1, the tee joint (1-3) is replaced by the water pump, and the water pump outputs water (1-5) to the front and back directions; when the external stent (4-2) and the external support body (3-3) are removed; when the particles are sprayed from the right angle (2-5) after the particles at the bottom of the water tank (1-4) are pumped by the discharge pump (2-1); when the water (1-5) sprayed from the right angle (2-5) can be sprayed from the upper part, and can also be sprayed from other directions to the water (1-5) sprayed from the tee joint (1-3); when the backward nozzle of the tee joint (1-3) is enlarged; when the water (1-5) is other liquid or gas or mixture; and the combination of the above forms to form a new form is the content of the invention.

The invention is not only suitable for being used on airplanes, but also suitable for being used on automobiles, ships, trains, airships, flying disks, satellites, rockets, missiles and space shuttles.