Plasma turbine

Abstract

The present invention relates to a plasma turbine comprising a compressor (3) and a turbine (1), wherein there are one or more plasma chambers (7) between the compressor (3) and the turbine (1), each chamber having a plasma injector (4) which is provided with a cathode (44) and an anode (43); a first inlet (41) from a microcompressor (5), at a higher pressure than the compressor (3); and an outlet (45) towards the plasma chamber (7), and wherein the air of the first inlet (41) passes through the electrodes, so that the air of the first inlet (41) turns into plasma in the plasma injector (4).

Description

[0001] DESCRIPTION

[0002] Plasma turbine

[0003] TECHNICAL SECTOR

[0004] This application relates to an aircraft turbine, of the type that includes a turbine that rotates through the flow of a gas and uses a plasma system for heating and propulsion. It can be used to generate other types of mechanical work, for example, for aircraft propulsion.

[0005] STATE OF THE ART

[0006] Various types of turbines are known in the state of the art. The simplest are river mill wheels, although some are highly complex. This invention focuses on turbines and installations that utilize the Brayton cycle (compression, heating, expansion, cooling) in a gas to generate work, typically electrical energy or thrust in the case of aviation.

[0007] These systems require fossil fuels burned in chambers or in the turbine itself to generate heat and, sometimes, compression. This system therefore generates waste and pollution. Some of this waste remains in the turbine itself, modifying and reducing its efficiency.

[0008] On the other hand, plasma guns are known for use, for example, in cutting metal. These guns are capable of converting a gas jet into a plasma jet using only a voltage difference. This plasma jet is several thousand degrees hot and has an extremely high ejection velocity.

[0009] The applicant is not aware of any system that would allow the advantages of the invention to be obtained. BRIEF EXPLANATION OF THE INVENTION

[0010] The invention consists of a plasma turbine according to claim 1. Its various variants solve the aforementioned problems.

[0011] The invention aims to completely eliminate combustion residues from fossil fuels (particulate matter, NOx, COx, etc.). In the case of aviation, this represents 20% of the CO2 produced worldwide.

[0012] This installation can be used in turboprops, turboprops, turbofans, turboshafts, etc. in private or military aviation, and can be manufactured as original equipment or modified by any engine that involves a turbine.

[0013] This invention develops an engine where plasma would be produced to heat the air coming from the turbine compressor in the plasma chamber and thus create thrust in the case of aircraft engines or work for electricity generation, turboshaft, turboprop, turbofan, etc.

[0014] The generating plant consists of a compressor and a turbine. Between the compressor and the turbine, it also has one or more plasma chambers with a cathode and an anode: a first inlet from the compressor, a second inlet from an auxiliary compressor or microcompressor, at a higher pressure than the compressor, and an outlet to the turbine. The second inlet passes through the electrodes, so that the air from the second inlet is converted into plasma in the plasma chamber. The microcompressor will raise the pressure to more than four times the compressor pressure, but with a reduced amount of air (frequently 1%).

[0015] This modification does not alter the composition of the turbine's components; only the traditional combustion chamber is replaced by plasma chambers. The turbine's operating cycle (Brayton cycle) is also unchanged, and thrust is maintained. The system thus created is a fully electric and environmentally friendly engine, free of polluting gases, and also avoids the use of green hydrogen, which would require complicated modifications to the aircraft.

[0016] Ideally, the last stage of the compressor is connected to the inlet of the microcompressor, which thus requires less pressure increase, since part of the work is done by the compressor. A control valve can be installed at this inlet to regulate the amount of air entering the microcompressor.

[0017] Other variants can be seen in the rest of the report.

[0018] DESCRIPTION OF THE FIGURES

[0019] For a better understanding of the invention, a section of drawings is included containing the following:

[0020] Figure 1: Diagram of an installation according to the invention.

[0021] Figure 2: Schematic section of an example of a plasma injector.

[0022] Figure 3: Schematic section of an example of a plasma chamber.

[0023] Figure 4: Diagram of a turbojet applying the invention.

[0024] MODES OF EMBODIMENT OF THE INVENTION

[0025] Below, a brief description is given of an embodiment of the invention, as an illustrative and non-limiting example thereof.

[0026] Figure 1 shows an example of a schematic diagram of the installation that forms the plasma turbine of the invention. Part of a turbine (1) that is connected to the point of use of the work, generally an alternator (2) for the generation of electrical energy, as well as by expansion of gases to generate thrust in an aircraft engine. The installation also has a compressor (3) that can be moved by the axis of the turbine (1) itself, with or without interposed multipliers.

[0027] There is also at least one plasma chamber (7) comprising a plasma injector (4). Each plasma injector (4) has a first inlet (41) (shown double in the figures) coming from a microcompressor (5), which takes air and disposes it at a pressure much higher than that of the compressor (3). The microcompressor (5) will normally capture around 1% of the air from the compressor (3). The pressure ranges vary depending on the turbine model. For example, in a Rolls Royce Tay 611c turbine the pressure ratio between the inlet and outlet of the compressor (3) is 15: 1. The microcompressor (5) has a ratio of 4: 1, which makes the outlet of the microcompressor (5) have a pressure sixty times the pressure of the inlet to the compressor (3). That is, it is multiplied by 15 in the compressor (3) and then by 4 in the microcompressor (5).

[0028] The plasma injector (4) has an anode (43) and a cathode (44) supplied with direct current with an electrical potential difference of, for example, 40,000 V. Figure 2 shows an example of an embodiment of the plasma injector (4), with the plasma outlet (45) on the left side.

[0029] The potential difference between both electrodes (43,44) creates an electric arc that converts the intermediate air into plasma, which is pushed by the pressure of the air leaving the microcompressor (5) towards the outlet (45), coming out at 10,000 °C. In this way the air converted into plasma is withdrawn, entering the plasma chamber (7), where it heats the air coming from the compressor (3), and is continuously replaced by the air from the microcompressor (5). This outlet (45) is inside the plasma chamber (7) where it is fed with the remaining air from the compressor (3) through some mouths (71). The air is directed to the turbine (1), causing the movement of the rotor and expands in the nozzle generating thrust.

[0030] As the person skilled in the art will appreciate, the higher pressure air from the first inlet (41) is ionized and converted into plasma as it passes through the plasma injector (4). This plasma, in addition to accelerating the total air, raises its temperature so that more energy can be extracted from the turbine (1). A control valve (6) makes it possible to select how much air is directed to the microcompressor (5). The installation can form part of a propulsion reactor in an aircraft, such that all the equipment is arranged in a casing, forming a straight line, with the microcompressor (5) possibly being on one side. The electrical supply to the electrodes (43,44) can be by the electricity generated in the alternator (2), from a battery...

Claims

CLAIMS 1- Plasma turbine, comprising a compressor (3) and a turbine (1), characterized in that it comprises, between the compressor (3) and the turbine (1), one or more plasma chambers (7) each with a plasma injector (4) having a cathode (44) and an anode (43), a first inlet (41) from a microcompressor (5), at a higher pressure than the compressor (3), and an outlet (45) towards the plasma chamber (7), and where the air from the first inlet (41) passes through the electrodes, such that the air from the first inlet (41) is converted into plasma in the plasma injector (4). 2- Plasma turbine, according to claim 1, characterized in that the compressor (3) is connected to the inlet of the microcompressor (5). 3- Plasma turbine, according to claim 2, characterized in that it comprises a control valve (6) at the inlet to the microcompressor (5).

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