STRUCTURAL ARRANGEMENT IN A LOW-TEMPERATURE TURBOCOMPRESSOR FOR AN INTERNAL COMBUSTION ENGINE

Abstract

The low-temperature turbocompressor structural arrangement for an internal combustion engine is a system for using the energy that is available but unused during operation of an internal combustion engine, for cooling the air supplied to said engine by supercharging, applicable to internal combustion engines of any type. The temperature of the air compressed by the compressor is reduced by a cooling system and the air is then conveyed to a further turbine actuated by the intake air flow of the engine, affording the benefits of enhancing engine performance levels, which may be used in order to obtain greater power or reduce consumption, since the denser air allows more fuel into the combustion chamber, achieving greater combustion, which increases the power-to-weight ratio, and the cooler air allows work at more aggressive compression and/or ignition advance ratios without problems of pre-ignition/pinking, thereby enhancing engine performance levels. The structural arrangement may be mounted in the integral form thereof or in partial forms, and also each component may be fitted into existing systems.

Claims

1-4. (canceled)

5. A turbo compressor for an internal combustion engine having an air intake pipe and an exhaust pipe comprising: a first exhaust gas turbine having a first intake in fluid communication with the exhaust pipe and a first discharge in fluid communication with an ambient environment, the first exhaust gas turbine is fixedly attached to a first axle and rotates the first axle in response to a supply of pressurized exhaust gas from the engine; an intake gas turbine having a second intake in fluid communication with the air intake pipe and having a second discharge in fluid communication with the internal combustion engine, the intake gas turbine is fixedly attached to the first axle and rotates the first axle in response to a supply of air under pressure from an ambient environment; a return gas turbine having a third intake in fluid communication with the air intake pipe and a third discharge in fluid communication with a first compressor, the return gas turbine is fixedly attached to the first axle and rotates the first axle in response to a supply of air under pressure from a return pipe; the return pipe connecting the third intake to the air intake pipe; a valve installed in the return pipe for means of regulation of the returning mass flow; the first compressor having a fourth intake in fluid communication with the air intake pipe and a fifth intake in fluid communication with the third discharge, the fourth and fifth intakes being united or separated, the first compressor is fixedly attached to the first axle and rotates in response to the rotation of the first axle in order to supply pressurized air from the air intake pipe and the return gas turbine to the system, the first compressor having a fourth discharge in fluid communication with an intercooler, the fourth discharge combines the air from the intake pipe and the air from the return gas turbine; and, the intercooler having a sixth intake in fluid communication with the fourth discharge and a fifth discharge, the intercooler having a heat exchange surface between the sixth intake and the fifth discharge, a temperature of air in the sixth intake is higher than a temperature of air at the fifth discharge, the fifth discharge is in fluid communication with the second intake.

6. The turbo compressor of claim 5 further comprises a second compressor having a seventh intake and a sixth discharge installed in fluid communication with the first compressor and a second exhaust gas turbine having a eighth intake and a seventh discharge installed in fluid communication with the first exhaust gas turbine.

7. The turbo compressor of claim 6 wherein the second compressor is mounted to the first axle and rotates in response to the rotation of the first axle in order to provide a supply of pressurized air from the air intake pipe.

8. The turbo compressor of claim 6 wherein the second exhaust turbine is mounted to the first axle and rotates the first axle in response to a supply of pressurized air from the exhaust pipe.

9. The turbo compressor of claim 6 further comprising a second axle supporting the second compressor and the second exhaust turbine for rotation thereabout.

10. The turbo compressor of claim 5 further comprising a third axle supporting one or more turbines and/or compressors;

11. The turbo compressor of claim 10 wherein the third axle is connected to the first axle by gears, belts or other type of connection that transfers mechanical power;

12. The turbo compressor of claim 6 further comprising a second intercooler having a ninth intake and an eighth discharge, the second intercooler is positioned between the first compressor and the second compressor and is in fluid communication therewith.

13. The turbo compressor of claim 5 further comprising a mechanical compressor positioned in fluid communication with the internal combustion engine.

14. A power supply system for vehicles comprising: an internal combustion engine having an air intake pipe and an exhaust pipe; a turbo compressor having an air intake pipe and an exhaust pipe comprising: a first exhaust gas turbine having a first intake in fluid communication with the exhaust pipe and a first discharge in fluid communication with an ambient environment, the first exhaust gas turbine is fixedly attached to a first axle and rotates the first axle in response to a supply of pressurized exhaust gas from the engine; an intake gas turbine having a second intake in fluid communication with the air intake pipe and having a second discharge in fluid communication with the internal combustion engine, the intake gas turbine is fixedly attached to the first axle and rotates the first axle in response to a supply of air under pressure from an ambient environment; a return gas turbine having a third intake in fluid communication with the air intake pipe and a third discharge in fluid communication with a first compressor, the return gas turbine is fixedly attached to the first axle and rotates the first axle in response to a supply of air under pressure from a return pipe; the return pipe connecting the third intake to the air intake pipe; a valve installed in the return pipe for means of regulation of the returning mass flow; the first compressor having a fourth intake in fluid communication with the air intake pipe and a fifth intake in fluid communication with the third discharge, the fourth and fifth intakes being united or separated, the first compressor is fixedly attached to the first axle and rotates in response to the rotation of the first axle in order to supply pressurized air from the air intake pipe and the return gas turbine to the system, the first compressor having a fourth discharge in fluid communication with an intercooler, the fourth discharge combines the air from the intake pipe and the air from the return gas turbine; and, the intercooler having a sixth intake in fluid communication with the fourth discharge and a fifth discharge, the intercooler having a heat exchange surface between the sixth intake and the fifth discharge, a temperature of air in the sixth intake is higher than a temperature of air at the fifth discharge, the fifth discharge is in fluid communication with the second intake.

15. The power supply system of claim 14 further comprises a second compressor having a seventh intake and a sixth discharge installed in fluid communication with the first compressor and a second exhaust gas turbine having a eighth intake and a seventh discharge installed in fluid communication with the first exhaust gas turbine.

16. The power supply system of claim 15 wherein the second compressor is mounted to the first axle and rotates in response to the rotation of the first axle in order to provide a supply of pressurized air from the air intake pipe.

17. The power supply system of claim 15 wherein the second exhaust turbine is mounted to the first axle and rotates the first axle in response to a supply of pressurized air from the exhaust pipe.

18. The power supply system of claim 15 further comprising a second axle supporting the second compressor and the second exhaust turbine for rotation thereabout.

19. The power supply system of claim 14 further comprising a third axle supporting one or more turbines and/or compressors;

20. The power supply system of claim 19 wherein the third axle is connected to the first axle by gears, belts or other type of connection that transfers mechanical power;

21. The power supply system of claim 15 further comprising a second intercooler having a ninth intake and an eighth discharge, the second intercooler is positioned between the first compressor and the second compressor and is in fluid communication therewith.

22. The power supply system of claim 14 further comprising a mechanical compressor positioned in fluid communication with the internal combustion engine.

Description

DRAWINGS

[0019] In order to facilitate the search and understanding of the present patent, as recommended in the report, according to a basic and preferred embodiment created by the applicant, reference is made to the attached drawing, which supplements and supports the present description, in which:

[0020] FIG. 1—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with just one compression stage.

[0021] FIG. 2—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with an additional low-pressure turbocompressor arranged in parallel.

[0022] FIG. 3—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with an additional low-pressure turbocompressor arranged in parallel and an additional intercooler.

[0023] FIG. 4—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with an additional high-pressure turbocompressor arranged in parallel.

[0024] FIG. 5—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with an additional low-pressure turbocompressor on the same shaft.

[0025] FIG. 6—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with an additional mechanical compressor.

[0026] FIG. 7—Schematic view of alternative inversions of the sequence of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine. (A) Inversion of the sequence between the return gas and intake gas turbines; (B) between the exhaust turbine and the compressor.

[0027] FIG. 8—Schematic view of alternative arrangements of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine. (A) Assembly perpendicular to the cold turbines; (B) assembly parallel to the cold turbines.

[0028] FIG. 9—Schematic view of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine with a coupling/uncoupling system for the cold turbines. (A) dependent; (B) independent.

[0029] Unbroken line 1-7: intake pipe

[0030] Dotted line 5-6: Return pipe

[0031] Dashed line 8-9: Exhaust pipe

[0032] T1—Exhaust gas turbine

[0033] C—Compressor

[0034] T2—Return gas turbine

[0035] T3—Intake gas turbine

[0036] IC—Intercooler

[0037] IC′—Additional intercooler

[0038] V—Return valve

[0039] M—Engine

[0040] T′—Additional turbine

[0041] C′—Additional compressor

DESCRIPTION

[0042] In the structural arrangement in a low-temperature turbocompressor for an internal combustion engine (FIG. 1), the turbocompression system is formed by the exhaust gas turbine (T1) rigidly connected to the compressor (C). The compressor conveys the fluid to a cooler that can be an intercooler (IC), but that is not limited to this or other types of heat exchangers, nor to a specific coolant fluid, since any type of coolant fluid can used. Sequentially, the flow of cooled compressed air is conveyed to a second turbine, known as the intake gas turbine (T3), the pressure of which is regulated by a return valve (V) that prevents the overloading of the engine (M), directing the excess flow to a third turbine, known as the return gas turbine (T2), which returns the air to the inlet of the compressor (C). The two turbines T2 and T3 are rigidly connected to the compressor (C) and to the exhaust gas turbine (T1). The system can use compressors and turbines of variable geometry and any other compressors or turbines that can be installed on the same shaft, with any type of assembly constraining the movement thereof. The system can also include multiple stages with turbocompressors on separate shafts or on the same shaft as the former. The system proposed in the structural arrangement in a low-temperature turbocompressor for an internal combustion engine can also be used in conjunction with other air compressors, mechanical (FIG. 6) or otherwise, or even with additional turbocompressors, all in series (FIG. 5) or in parallel (FIGS. 2, 3 and 4) with the first. The system can also be used with compressors and turbines of variable geometry, with multiple stage expansion and/or compression. The engine can be a two- or four-stroke Otto-cycle or diesel engine. Additional heat exchangers can also be used, and any coolant fluid can be used.

[0043] FIG. 1 shows operation of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine, in which the turbocompression system is formed by the exhaust gas turbine (T1), which uses the exhaust gases from the engine that are flowing through the exhaust pipe (dashed line) and is rigidly connected to the compressor (C). The temperature of the air in this compressor (C), which is arranged at the start of the intake pipe (unbroken line), is lowered by the intercooler cooling system (IC), after which the air is conveyed to the intake gas turbine (T3), moved by the flow of intake air of the engine. The pressure is regulated by the return valve (V), which releases some of the compressed air to ensure that the pressure does not exceed the maximum pressure admitted by the engine (M). The air released by this valve is conveyed through the return pipe (dotted line) to the return gas turbine (T2), which expands this mass of air from the working pressure of the engine to atmospheric pressure, resulting in a loss of heat. This air is conveyed to the inlet of the compressor (C) as part of the air that is compressed in the cycle, reducing the work done by the compressor on account of the low temperature thereof. The turbines moved by compressed air are constrained to move with the compressor (C) to generate more power and to enable the compressor (C) to produce even greater pressures. The cycle is therefore fed back by the work of the compressed-air turbines (the return gas turbine (T2) and the intake gas turbine (T3)) and by the lower effort required by the compressor (C) to compress the cooler air, tending to reach an equilibrium resulting from mechanical and thermal losses. Therefore, the objective of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine is to cause the temperature of the intake air of the engine, at a given working pressure of the engine, to be significantly lower than the temperature reached in a normal system.

[0044] To achieve this purpose, other configurations of the structural arrangement in a low-temperature turbocompressor for an internal combustion engine are possible, as shown in FIGS. 2, 3, 4, 5, 6, 7 and 8. FIGS. 2 and 3 relate to the installation of an additional low-pressure turbocompressor in parallel with the turbocompressor formed by the exhaust gas turbine (T1) and the compressor (C). In these configurations, an additional turbine (T′) installed in the exhaust pipe uses the exhaust gases from the engine after the exhaust gas turbine (T1) to drive a constrained additional compressor (C′) installed in the intake pipe before the compressor (C), increasing air intake. In FIG. 3, the air coming from the additional compressor (C′) is cooled by an additional intercooler (IC′) before entering the compressor (C). FIG. 4 relates to the installation of an additional high-pressure turbocompressor in parallel with the turbocompressor formed by the exhaust gas turbine (T1) and the compressor (C). In this configuration, an additional turbine (T′) installed in the exhaust pipe uses the exhaust gases from the engine before the exhaust gas turbine (T1) to drive a constrained additional compressor (C′) installed in the intake pipe between the compressor (C) and the intercooler (IC), also to increase air intake. FIG. 5 relates to the installation of an additional high-pressure turbocompressor on the same shaft as the other turbocompressors. In this configuration, an additional turbine (T′) installed in the exhaust pipe uses the exhaust gases from the engine after the exhaust gas turbine (T1) to drive an additional compressor (C′) rigidly connected to the system, installed in the intake pipe before the compressor (C), also to increase air intake. FIG. 6 relates to the installation of an additional mechanical compressor (C′) arranged in parallel with the turbocompressor formed by the exhaust gas turbine (T1) and the compressor (C). In this configuration, an additional constrained mechanical compressor (C′) is installed on the intake pipe between the intake gas turbine (T3) and the engine (M), also to increase air intake. FIGS. 7 and 8 show other possible configurations intended to take advantage of available spaces and/or conditions. FIG. 7A shows the installation of the intake gas turbine (T3) between the compressor (C) and the return gas turbine (T2), bringing the first turbine of the intercooler (IC) closer. FIG. 7B shows the option of placing the exhaust gas turbine (T1) in sequence with the return gas turbine (T2) and intake gas turbine (T3) positioned on the shaft after the compressor. FIG. 8 shows an example of the rotational transmission options from the return gas turbine (T2) and intake gas turbine (T3) to the compressor (C), perpendicularly using gears (A) or in parallel using a belt (B).

[0045] FIG. 9 explores the possibility of using a coupling system that enables the turbocompressor formed by the exhaust gas turbine (T1) and the compressor (C) to only connect to the system of the return gas turbine (T2) and the intake gas turbine (T3) when said turbines start generating power for the system. In configuration “A” in FIG. 9, the coupling occurs when the system of the return gas turbine (T2) and the intake gas turbine (T3) in conjunction begins generating power for the system, and configuration “B” in FIG. 9 provides the option of the return gas turbine (T2) being coupled when said turbine starts generating power for the system, followed by coupling of the intake gas turbine (T3) when said turbine reaches the required state.

[0046] “The low-temperature turbocompressor structural arrangement for an internal combustion engine” relates to a system for using the energy that is available but unused during operation of an internal combustion engine to cool the air supplied to said engine by supercharging, applicable to internal combustion engines of any type, characterized in that it supplies the engine with air that is colder and therefore denser than a common turbocompressor, and does so using the same amount of energy as consumed by this latter.

[0047] “The low-temperature turbocompressor structural arrangement for an internal combustion engine” relates to a system for using the energy that is available but unused during operation of an internal combustion engine to cool the air supplied to said engine by supercharging, applicable to internal combustion engines of any type, as described in 001, formed by a system comprising a turbocompressor and turbines and characterized in that the turbocompression system is formed by the exhaust gas turbine (T1) rigidly connected to the compressor (C), in which said compressor conveys the fluid to a fluid cooler that can be an intercooler (IC), but that is not limited to this or other types of heat exchanger, nor to a specific coolant fluid, since any type can be used, and sequentially, the flow of cooled compressed air is conveyed to an intake gas turbine (T3) with pressure regulated by a return valve (V) that prevents the overloading of the engine (M) and directs the excess flow to a return gas turbine (T2) that returns the air to the inlet of the compressor (C), in which the turbines T2 and T3 are rigidly connected to the compressor (C) and to the exhaust gas turbine (T1).

[0048] “The low-temperature turbocompressor structural arrangement for an internal combustion engine” relates to a system for using the energy that is available but unused during operation of an internal combustion engine to cool the air supplied to said engine by supercharging, applicable to internal combustion engines of any type, as described in 1 and 2, with alternative structures characterized in that the system can use compressors and turbines of variable geometry or any other compressors or turbines that can be installed on the same shaft, with any type of assembly constraining the movement thereof, include multiple stages with turbocompressors on separate shafts or on the same shaft as the first, be used in conjunction with other air compressors, mechanical (FIG. 6) or otherwise, or even with additional turbocompressors, all in series (FIG. 5) or in parallel (FIGS. 2, 3 and 4) with the former, use compressors and turbines of variable geometry, with multiple stage expansion and/or compression, in two- or four-stroke Otto-cycle or diesel engines, using additional heat exchangers and any coolant fluid, with the option of assembling fully or partially as required, in which each component part can be adapted to pre-existing systems.

[0049] “The low-temperature turbocompressor structural arrangement for an internal combustion engine” relates to a system for using the energy that is available but unused during operation of an internal combustion engine to cool the air supplied to said engine by supercharging, applicable to internal combustion engines of any type, as described in 1, 2 and 3, with connection of the turbocompressor to the system of cooled air turbines, characterized in that they occur, but not exclusively, from the moment at which said turbines begin generating power for the system, individually or in a group (FIG. 9).

CONCLUSION

[0050] Accordingly, the structural arrangement in a low-temperature turbocompressor for an internal combustion engine is based on novel functional and technical features, as can be seen from the attached figures and understood from the description, thereby qualifying for the claimed legal protection.