JP2022519442A - Combustion engine - Google Patents

Abstract

The present invention relates to a structural arrangement of fixed or vehicle-mounted universal internal combustion engines for machines (arranjo estrutural para um motor de combustao interna universal) that can use different types of fuels. More specifically, the present invention has improved combustion efficiency, better thermodynamic efficiency, smaller dimensions, and an output / weight ratio that exceeds that of an airplane turbine using the Brayton thermodynamic cycle and consumes fuel. It relates to an internal combustion engine that emits up to one-third of gas to the environment.

Description

The present invention relates to a fixed or vehicle-mounted universal internal combustion engine for machines that can use different types of fuels (arranjo estrutural para um motor de combustao interna universal).
The present invention relates specifically to an internal combustion engine capable of excellent combustion thermodynamic efficiency, improved efficiency, reduced fuel consumption, low emission of gas to the environment and minimization of size.

The current engines used in transport vehicles such as aircraft, vehicles and boats, machines and fixing devices were invented in the latter half of the 19th century. Improvements have been made to this engine over the years, for example thermal efficiency has increased from 5% to nearly 30% in the laboratory.

In addition, the outgassing rate to the atmosphere has decreased, and the direct impact on air pollution has also decreased. However, the design of this old engine has virtually reached its limit (no limite).

Therefore, the present invention was developed to provide a more modern and more efficient placement technique for the above engines, the invention of which is the current engine by using a more efficient thermodynamic cycle. It is possible to make it about 3 times as much as.

The present invention relates to a mixed reciprocating rotary internal combustion engine (um motor de combustao, rotativo alternativo misto formado) formed by one or more sectors for multiple applications such as stationary devices, vehicles and machines. More specifically, the present invention relates to the structural arrangement of internal combustion engines using a variety of different types of fuels. The vehicle may be land, sea, rail or air. More specifically, the present invention is an airplane turbine that uses the Brayton thermodynamic cycle (ciclo termodinamico Brayton) with improved combustion efficiency, better thermodynamic efficiency, smaller dimensions, and a power / weight ratio. It relates to an internal combustion engine that consumes fuel and emits gas to the environment by up to one-third.

Indicates an internal combustion engine with external accessories (accessories) removed.

2A and 2B show an engine shaft with an eccentric body (cam, excentrico) and a ring (anel).

3A and 3B show the subassemblies (rings, anel) of the present invention.

The eccentric body (cam, excentrico) of the subassembly of the present invention is shown.

5A and 5B show a subassembly of an engine shaft with an eccentric shaft (eixo excentrico) and a red ring (anel) of the present invention.

The subassembly of the seal blade (pas-selo) of the present invention is shown.

The frame structure block for the engine element of this invention is shown.

The cover (tampa) which separates the engine sector of this invention is shown.

The thermodynamic profile of the engine of the present invention is shown.

10A and 10B show a submontagem no interior with shafts, eccentric bodies (cams), rings, seal blades, blocks forming a combustion chamber or compression chamber.

The present invention relates to a mixed reciprocating rotary combustion engine (um motor de combustao, rotativo alternativo misto formado) formed by one or more sectors for universal use. In particular, the structural arrangement of the engine of the present invention is simple with few moving elements, simplifies the manufacturing and assembly process, and requires only a small radiator to cool the system. The system can also be cooled with air. The engine of the present invention has only the following moving elements: rings, shafts, eccentric bodies (cams) and seal blades.

The features of the engine of the present invention provide a structural arrangement that allows for smaller dimensions and is capable of performing a thermodynamic cycle at each rotation of the shaft in the same number of times as a very efficient combustion chamber.

It will be appreciated by those skilled in the art that the term sector (setores) as used herein includes the smallest set of parts required to form an engine.

In the engine technology provided by the structural arrangement of the present invention, compression, which is the first part of the cycle, occurs in one or more stages, the number of which is unlimited. Thermodynamic cycles using this engine are more efficient than currently used thermodynamic cycles in which compression is performed in one or more steps. Intermediate cooling can significantly reduce the force required to perform compression and maximize the energy of the gas in the expansion process. What's more, this cycle maximizes the energy produced by the fuel and minimizes waste.

The compression takes place in the compression chamber of the first step, but in each subsequent step it is also compressed in the smaller volume of the combustion chamber, between each stage the system is cooled towards the environment by the radiator and then in the combustion chamber. It is compressed. The final compression performed in the combustion chamber can also be further cooled by injecting spray water into the combustion chamber, which causes the compression to be close to isentropic, followed by an explosion and then expansion. Occur. The adiabatic expansion energy in this final expansion process can be increased to the suction pressure value as much as possible.

The arrangement of the present invention can be quiet exhaust and low temperature. As already mentioned, the noise and temperature are low because the exhaust pressure is very low.

The engines disclosed herein can be designed for universal applications of any size with very high power / weight ratios, in addition to being usable in land vehicles, and are higher than the Brayton cycle of turbines. Due to its efficiency, it can also be used in aircraft, which can increase power output with much less consumption than the turbine requires, is lighter and produces more power, and is relative between parts inside the engine. Since the friction rate is very low, the service life can be extended.

It is also possible to manufacture engines for power plants of 1,000,000 kW or more. Currently known engines have a maximum of 100,000 kW and weigh more than 2300 tons, which is extremely heavy. The engine of the present invention has the same output and is about 30 tons.

In the engine of the present invention, multiple cycles including one revolution of a very lightweight and powerful shaft are completed in each combustion sector. For example, an engine with three sectors with 16 combustion chambers per sector can be used, resulting in 48 explosions (cycles) at each revolution. It should be noted that the present invention is not limited to this example.

The torque of the engine of the present invention is very high, continuous, with little vibration, and can be made at low rpm, thus reducing consumption at minimum rpm. When multiple seal blades are placed on the block, torque can be improved by tilting the seal blades with respect to a predetermined laboratory-proven angle.

Further, the engine of the present invention can store and regenerate energy in the compressed portion in the additional tank. It functions as a spare tank for vehicles such as trucks and trains. Additional tanks can store compressed air without the use of down brakes when the vehicle is moving down (movimento de descida), which can be used as extra energy that can later be reused in uphill movements at no cost.

Condensed water from the additional tank at prepressure during the above reuse can be reinjected at the end of the combustion cycle for system cooling at no energy cost. This cooling occurs during exhaust, further cooling the combustion section of the system.

The heating of the system is perfectly uniform around the engine without hot spots and is very low. The stem can be cooled by a fan mounted on the counterbalance between the cisectors.

The arrangement proposed by the present invention has a straight line without strange curves and a round flat design.

The engine in which the present invention is proposed has a low frictional speed between elements and can have a high revolutions per minute. For example, a high power sports vehicle can be 20,000 rpm or higher, but the present invention is not limited thereto. Since the seal blade is a reciprocating motion that alternates back and forth, the speed of the seal blade relative to the ring or block is minimal and complete lubrication of the seal blade is achieved so that the consumption of lubricating oil is very low. ..

In addition, special materials such as Teflon®, especially self-lubricating metals with similar properties, can be used to eliminate the consumption of lubricating oil, and bearings can be used to system (shaft). Friction in some parts of the can be further reduced.

Since the engine of the present invention can be placed in a very small space, it contributes to the utilization of a larger useful space in all transport vehicles. On aircraft such as airplanes, this engine has a low front section, reducing drag. These mixed turbofan engines (propellers, with inverters included in tube propellers) are extremely high power, much more efficient, over 100,000 HP at 1500 rpm, lighter than turbines and similar to current commercial aircraft. It can be manufactured at a high speed (1000 kmts / Hr).

Moreover, the engine of the present invention operates at a lower exhaust temperature and is substantially undetectable by infrared light and is very quiet. Do not use a reducer or flow divertor for deceleration, use only reversible turbofans or pipe-type reversible propellers. It can also be used with one or more axial or centrifugal turbochargers and supersonic aircraft with a very special design that adds a combustion chamber and expansion. The mixed engine of the present invention is very efficient and does not require a turbine. It can also be used in vertical takeoff planes, helicopters, etc.

Since the air and fuel are pre-cooled, the compression ratio can be increased to very high values.

The exhaust valve operates at low and low temperatures. This fact allows for simpler manufacturing processes and materials and reduces manufacturing costs. Materials that can be used are aluminum, titanium, stainless steel, etc.

Although the engine of the present invention is very different from the engines most used today, the current production line can be easily adapted to the engine of the present invention, and the engine of the present invention can be manufactured quickly at low cost.

Any possible combination can be used in the design of the engine of the invention, one or more different sectors and any number of combustion and / or compression chambers within each sector can be used, among these. Many transformations are possible.

The engine of the present invention can be used in energy production in thermoelectric form using only one-third of the fuel, and can produce a machine with an extremely small and ultra-economical output of over 1000 MW.

When the engine of the present invention is used, for example, in a boat, the desired speed can be almost doubled with the same fuel consumption.

Finally, the engine of the present invention contributes to the health of the earth. That is, global warming is reduced because the CO ₂ emission rate into the atmosphere is significantly reduced.

The structural arrangement of the engine of the present invention may include only a single sector or may include multiple sectors working together as shown in FIG.

The sectors are ordered according to the design of the engine, and the engine of the present invention may have one or more sectors of different shapes, sizes, sequences and configurations for a particular application.

FIG. 1 shows an assembly of an internal combustion engine with external elements removed. The engine is equipped with multiple orifices for the entry and exit of gas and liquid into each sector of the engine.

In a preferred embodiment of the invention, the engine comprises a plurality of sectors along its longitudinal axis, each sector having a cylindrical structure in the form of an anel within it. This is referred to herein as a subassembly. This subassembly is described in detail by [FIG. 2A], [FIG. 2B], [FIG. 3A], [FIG. 3B], [FIG. 5A] and [FIG. 5B].

In addition to free rotation on the eccentric body, the subassembly (ring) adjusts to the outer diameter of its own eccentric body (seu proprio excentrico) over its entire length. As shown in FIG. 2B, the eccentric body forms an inseparable part of the engine, including its shaft and its ring, these elements are fixed to the shaft and eccentric body, and the ring and eccentric body are free. be. In a single sector engine, the shaft and eccentric body can be integrated, but in a multi-sector engine, they must be separated and fixed together at the time of final assembly as shown in [FIG. 11].

It will be appreciated by those skilled in the art that the dimensions, quantity, dimensions of the ring, the quantity, shape and composition of the additional elements of the ring will vary from engine design to engine design. However, the engine shaft and eccentric body vary depending on the configuration, size, and shape, reciprocate within the ring, and rotate together.

FIG. 5B shows an engine with eight combustion chambers or compression chambers in a preferred embodiment of the invention, while FIG. 2B shows an engine with nine combustion chambers or compression chambers. There is. These figures show a cross section of the engine and the ring, which is the main subassembly, is shown in red.

FIG. 6 shows additional elements of the engine, such as seal blades, that work with the subassemblies of the present invention. Each seal blade is placed in each groove of the subassembly. That is, one is arranged in each groove of the frame block.

The seal blade uses a spring or pneumatic force (not shown) to slide inside the groove against the subassembly or structural block, facilitating the combustion or division of the empty interior space within each sector into compression chambers.

The surface of the seal blade is sealed by a slide reciprocating motion against the ring or block structure and slides laterally back and forth with respect to the engine cover.

The above subassembly is an element involved in the operation of the engine of the present invention. If the ring (subassembly) is not present in the project, the engine will only operate on the seal blades inside the block, and the relative velocity to the eccentric body, which is the weakly lubricated part, will be very high, so the relative velocity to the eccentric body will be very high. It gets higher. Therefore, the engine speed is low, the service life is very short, and the emissions are very high. That is, the relative speeds are so high that it is necessary to use large amounts of oil or build large engines, which is not possible.

When the eccentric body starts to rotate, the engine shaft also rotates, but during the rotational movement of the engine and the eccentric shaft, the ring and the subassembly freely reciprocate as shown in [FIG. 5A] and [FIG. 5B].

In the present invention, the combustion chamber or compression chamber is a closure for combustion between two intermediate or final covers, a carcass (frame, structure or block), a part (subassembly) formed by two consecutive seal blades and rings. It is formed by the internal space. FIG. 8 shows a cover. This cover separates the sectors that make up the engine. The cover can be sized, shaped and configured according to the desired application.

For a given application, the larger the number of combustion chambers, the higher the number of explosions per revolution, which can result in smoother, more resistant, more efficient and longer service life.

The main advantage of the presence of the ring in the engine of the present invention is the relative speed between the ring and the seal blade. This is many times slower than the speed applied to current engines.

As a result, the wear on the blades and all other elements of the engine is much lower. The number of revolutions per minute of the engine can be increased several times, which makes the engine smaller, lighter and faster. There are virtually no restrictions on engine output and size.

The seal blade subassembly has at least one push spring at the innermost end of each seal blade or is served with pressurized air. The push springs, which are not shown, are arranged against the ring or against the block and press them appropriately, as shown in [FIG. 2B], [FIG. 10A] and [FIG. 10B].

The engine is equipped with valves for entering and exiting combustion gas and compressed gas (not shown).

FIG. 9 shows a theoretical thermodynamic profile representing the pressure-volume of an internal combustion engine of the present invention. Those skilled in the art will appreciate that this particular thermodynamic cycle is very efficient and entails enormous fuel savings.

INDUSTRIAL APPLICABILITY The present invention has an extremely low relative speed between the ring and the seal blade, is excellent in lubrication of the system, has sufficient sealing and durability, and can minimize the consumption of lubricating oil. Providing the technology of. That is, high output, high speed (rpm), high efficiency, low consumption, low even if the size and weight of the motor are reduced because the wear of the seal blade is reduced and the engine speed per minute is greatly increased. Achieves contamination and long service life.

The present invention is not limited to the embodiments described herein. Those skilled in the art will appreciate that this specification has been described for ease of understanding and that certain features of the concepts described can be carried out without departing from the invention. The limited features of the subject matter of the present invention relate to the scope of claims that are part of this specification.

Claims (5)

A fixed inner-toothed washer (arruela dentada internamente) -shaped block frame (Fig. 7) and a shaft with a coupled eccentric body in the center of this frame block (Fig. 5A), which makes a circular motion on this shaft. It has four main parts, an outer toothed washer (arruela dentada externamente) (Fig. 2A) and a parallel hexahedral seal blade (Fig. 6), which is embedded in the groove of the outer toothed washer from the outside. (FIG. 2A), it moves radially, is embedded inside the groove of the inner toothed washer (FIG. 7), and moves laterally.
A combustion engine having a structural arrangement of a general purpose internal combustion engine, characterized in that. It has an outer toothed washer (Fig. 2A) or an inner flat washer (arruela lisa interior) (Fig. 3B), which is adjusted to the outer diameter of its own eccentric body along its entire length and rotates freely on it. The combustion engine according to claim 1. The eccentric body further includes a shaft and its washer, these elements are fixed and attached, the shaft rotates with the eccentric body, and the washer rotates with the eccentric body (FIG. 2B). The described internal combustion engine. A parallel hexahedron-shaped seal blade moves radially inside the groove of the outer toothed inner washer with the washer with respect to the inner toothed washer / frame block (FIG. 7) and (FIG. 10B) by the force of a spring or compressed air. (Fig. 2A) (Fig. 10B), or a seal blade (Fig. 10A) freely mounted in the groove of the frame block slides radially in the frame block by the force of the chamber or compressed air. The internal combustion engine according to claim 1, which slides laterally in a flat washer (FIG. 3B) to facilitate the division of an empty internal space within each sector of the combustion chamber or compression chamber in either case. A complete thermodynamic cycle is performed for each rotation and each compression is performed in stages with intermediate cooling (Fig. 9). The combustion engine of the machine according to claim 1, which is maximally compressed in the combustion chamber after the compression stage to burst / burn / burn and immediately utilize the energy gained during the expansion of the gas in the combustion chamber to complete the cycle. ..

Images