WO2018195621A1 - Moteur à turbine à cycle binaire constitué par trois processus isobares et quatre processus adiabatiques, et procédé de commande pour le cycle thermodynamique du moteur à turbine - Google Patents

Moteur à turbine à cycle binaire constitué par trois processus isobares et quatre processus adiabatiques, et procédé de commande pour le cycle thermodynamique du moteur à turbine Download PDF

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WO2018195621A1
WO2018195621A1 PCT/BR2018/050110 BR2018050110W WO2018195621A1 WO 2018195621 A1 WO2018195621 A1 WO 2018195621A1 BR 2018050110 W BR2018050110 W BR 2018050110W WO 2018195621 A1 WO2018195621 A1 WO 2018195621A1
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processes
subsystem
energy
cycle
adiabatic
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PCT/BR2018/050110
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Portuguese (pt)
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Marno Iockheck
Saulo Finco
LUIS Mauro MOURA
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Associação Paranaense De Cultura - Apc
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
    • F02C1/05—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy

Definitions

  • This invention relates to a turbine-type thermal motor and its seven-process thermodynamic cycle, more specifically a thermal machine characterized by an energy conversion subsystem and an energy conservation subsystem and both perform an interdependent but non-differential binary thermodynamic cycle, operates on gas, this system performs a thermodynamic cycle composed of seven continuous processes, that is, all processes occur simultaneously, three of which are "isobaric” and four "adiabatic” with transfer of processes. dynamically varying mass from one subsystem to another, which may be null or partial.
  • thermodynamics defines three concepts of thermodynamic systems, the open thermodynamic system, the closed thermodynamic system and the isolated thermodynamic system. These three concepts of thermodynamic systems were conceptualized in the nineteenth century in the early days of the creation of the laws of thermodynamics and underlie all motor cycles known to date.
  • the isolated thermodynamic system is defined as a system in which neither matter nor energy passes through it. Therefore, this concept of thermodynamic system does not offer properties that allow the development of motors.
  • the open thermodynamic system is defined as a thermodynamic system in which energy and matter can enter and leave this system. Examples of an open thermodynamic system are the Otkins cycle Atkinson cycle internal combustion engines, Sabathe cycle Otto cycle diesel cycle, Brayton diesel cycle internal combustion engine, Rankine exhaust cycle from steam to the environment.
  • the materials that come into these systems are fuels and oxygen or working fluid or working gas.
  • the energy that enters these systems is heat.
  • the materials that come out of these systems are the combustion or working fluid exhaust, gases, waste, the energies that come out of these systems are the mechanical working energy and part of the heat dissipated.
  • the closed thermodynamic system is defined as a thermodynamic system in which only energy can enter and leave this system.
  • Examples of closed thermodynamic systems are external combustion engines such as Stirling cycle, Ericsson cycle, Rankine cycle with closed circuit working fluid, Brayton heat cycle or external combustion, Carnot cycle.
  • the energy that enters this system is heat.
  • the energies that come out of this system are the working mechanical energy and part of the heat dissipated, but no matter comes out of these systems, as they do in the open system.
  • thermodynamic cycles composed of a series of sequential and independent processes, and only one process occurs at a time until the cycle completes, in some cases the processes that form its cycle all occur simultaneously. but with constant gas mass within a single system, such as Brayton cycle turbine engines for example, which is formed by two isobaric and two adiabatic processes. Therefore, form the state acts! from the technique until the year 2010 the cycle engines Otto, ⁇ tkinson, Diesel, Sabathe, Brayton, Rankine, Stirling, Ericsson and the ideal theoretical cycle of Carnot.
  • Equation (a) (U) represents the internal energy in "Joule”, (ri) represents the number of mol, (R) represents the universal constant of perfect gases, (7) represents the temperature of the gas in "Kelvin” and ( ⁇ ) represent the adiabatic expansion coefficient.
  • the current state of the art comprises a number of engines, most of them dependent on very specific and special conditions to operate, for example, internal combustion engines, each requiring its own specific fuel, fine fuel control, oxygen and combustion time and in some cases require specific conditions including pressure, fuel flexibility is quite limited.
  • internal combustion engines each requiring its own specific fuel, fine fuel control, oxygen and combustion time and in some cases require specific conditions including pressure, fuel flexibility is quite limited.
  • the most flexible engine is the Rankine cycle, external combustion, Stirling or Ericsson, also external combustion, these are more flexible in their source.
  • the current state of the art comprises a series of engine cycles, most of which require combustion, that is, the burning of some type of fuel, and therefore the need for oxygen.
  • the current state of the art comprises a series of engine cycles, most of which require high operating temperatures, especially those of internal combustion, usually operating with working gas at temperatures above 1500 ° C.
  • External combustion engines or engines operating from external heat sources such as Rankine and Stirling cycle, are typically designed to operate at working gas temperatures between 400 ° C and 800 ° C.
  • Rankine and Stirling cycle are typically designed to operate at working gas temperatures between 400 ° C and 800 ° C.
  • motors based on open and closed systems they often require high temperatures to operate, all of them have their efficiencies limited to Carnot's theorem, that is, their maximum efficiencies depend exclusively on temperatures as defined by equation (b).
  • the current state of the art comprises basically six motor cycles and some versions thereof: the Afkinson cycle Otto cycle, similar to the Sabathe cycle Diesel cycle Otto cycle, similar to the Diesel, Brayton cycle, Rankine cycle, Stirling cycle, Ericsson cycle and Carnot cycle, ideal theoretical reference for engines based on open and closed systems.
  • the latest developments in the current state of the art have been introduced through innovations by joining more than one old cycle into combined cycles, ie: new engine systems composed of a Brayton cycle machine operating on fossil fuels, gas or oil. and a heat-dependent Rankine cycle machine rejected by the Brayton cycle machine.
  • new engine systems composed of a Brayton cycle machine operating on fossil fuels, gas or oil.
  • a heat-dependent Rankine cycle machine rejected by the Brayton cycle machine or the same philosophy, combining a diesel engine with a Rankine cycle engine or an Otto cycle engine, also joining it with a Rankine cycle engine.
  • Carnot's ideal engine while considered the ideal, most perfect engine to date, is in theory and within open and closed system concepts considering all ideal parameters, so it is the reference to date for all existing engine concepts.
  • THE Carnot's moor is not found in practical use because real materials lack the properties required to make Carnot's engine a reality, the physical dimensions for Carnot's cycle to be performed as in theory would be unviable in a practical case, therefore it is an ideal engine in open system and closed system concepts, but only in the theoretical concept.
  • PCT / BR2013 / 000222 defined as "Carnot Thermodynamic Cycle Thermal Control Machine and Control Process” which is comprised of two power conversion subsystems and operates In each subsystem, a thermodynamic cycle formed by two isothermal processes and two adiabatic processes.
  • PCT / BR2014 / 000381 defined as "Thermal Thermodynamic Transform Differential Thermal Machine and Control Process” which consists of two energy conversion sub-systems and operates a thermodynamic cycle formed by four isothermal processes of four adiabatic processes.
  • references differ from the present invention especially by two very striking features, the most important being that the references cited are characterized by differential cycles and have two energy conversion to work subsystems, while the proposed technology has a energy conversion to work subsystem. and the other energy conservation subsystem, and its cycle is binary and not differential and processes are continuous, that is, all processes that form its cycle occur simultaneously.
  • the hybrid or binary thermodynamic system concept provides the basis for the development of new thermal motor families, the differential binary cycle thermal motor family and the family of Non-differential binary cycle thermal motors and each motor will have its own characteristics according to the processes and phases that constitute its respective thermodynamic cycles.
  • thermal motors can be classified as follows: open system based thermal motors, closed system based thermal motors, differential binary cycle hybrid thermal motors and non-differential binary cycle hybrid thermal motors .
  • the closed system is Stirling cycle engines, Ericsson cycle engines, Rankine cycle engines, Brayton external combustion cycle engines, Carnot cycle engines.
  • the hybrid differential cycle system comprises all engines formed by two energy-to-work conversion subsystems.
  • the non-differential binary hybrid cycle system comprises all motors made up of a working energy conversion subsystem and an energy conservation subsystem.
  • the aim of the invention focuses on eliminating some of the existing problems, minimizing other problems and offering new possibilities.
  • a new concept of thermal motors has become indispensable and the creation of new motor motors is necessary. so that the efficiency of the engines is no longer dependent solely on temperatures and whose energy sources can be diversified and that allow the design of engines for environments even without air (oxygen).
  • hybrid system and differential and binary cycles eliminates the dependence of efficiency exclusively on temperature, the efficiency of any thermal machine depends on its potentials and their potential differentials, while open and closed systems generate potentials where the mass of gas is constant and for this reason they cancel out, demonstrated in the equations, the hybrid differential and binary cycle systems the mass is not necessarily constant, so they do not cancel and their efficiencies they depend on the potentials from which the driving force originates, that is, the pressures.
  • the hybrid system concept provides dependent potentials proportional to the product of the working gas mass by temperature.
  • (q) is the yield
  • (Ta) is the initial temperature of the high temperature isobaric process
  • (Tb) is the final temperature of the high temperature isobaric process, this temperature tends to equalize.
  • Tq hot source temperature
  • (Tc) is the initial temperature of the low temperature isobaric process
  • (Td) is the final temperature of the low temperature isobaric process, this temperature tends to equalize with the cold source temperature (Tf)
  • all temperatures in "Kelvin" (n1) is the number of moles in the heating chamber shared by the energy conversion subsystem and the energy conservation subsystem, indicated by region (ab) indicated at 21 3 in Figure 2
  • (n2) is the number of moles of the energy conversion subsystem, indicated by region (cd) in drawings 21 and 213 of Figure 2.
  • thermosolar thermosolar
  • geothermal become fully viable and their efficiencies have the mass, or number moles, as shown in equation (c), as a parameter for obtaining better efficiencies, even with relatively low temperature differentials and thermonuclear energies for space uses, eliminating fuel dependency and high reservoir volumes.
  • thermodynamic cycles Otto, Atkinson, Diesel, Sabathe, Brayton, Stirling, Ericsson, Rankine and the Carnot cycle operate on a single thermodynamic system and have a constant working gas mass, referenced to the mechanical cycle of the driving force elements, their control is a direct function of the power supply power, in turn the hybrid system binary cycles perform two interdependent cycles, for this reason is called binary and all their processes occur simultaneously indicated at 19, 213 and 32 of Figures 1, 2 and 3 respectively, enabling the control of the thermodynamic cycle separate from the mechanical cycle, the cycle can be modulated and thus the mechanical cycle becomes a consequence of the thermodynamic cycle and not the other way around as in open and closed system motors.
  • Binary cycle turbine engines are characterized by having two subsystems, forming a complex hybrid system, represented by 21 in figure 2, each subsystem executes a cycle referenced to the other subsystem in order to always execute all its processes. simultaneous and interdependent. Otherwise, considering a hybrid binary cycle system with properties of both open and closed systems simultaneously, the system is said to perform a composite thermodynamic cycle, indicated by 19, 213 and 32 of Figures 1, 2 and 3, ie always runs all processes simultaneously, including mass transfer between subsystems. Therefore these are turbine engines and cycles completely different from engines and cycles based on open or closed or hybrid differential cycle systems.
  • Figure 2 shows the correlation of the mechanical model indicated in 21 and the cycle graph indicated in 213.
  • thermodynamic system The concept of binary cycles of the hybrid thermodynamic system is new, characterized by a system formed by two interdependent subsystems and between them there is exchange of matter and energy, and one of them supplies out of its boundaries energy in the form of work and part heat dissipated energy and the other subsystem is energy conservation.
  • This thermodynamic system was created in the 21st century and offers new possibilities for the development of thermal motors.
  • the present invention brings important developments for the conversion of thermal energy to mechanical either for use in power generation or other use, such as mechanical force for movement and traction.
  • Some of the main advantages that can be seen are: the total flexibility as to the energy source (heat), the independence of the atmosphere, does not require atmosphere for a binary cycle motor to operate, the flexibility regarding the temperatures, the motor of Torque cycle can be designed to operate over a very wide temperature range, well above most motors based on open and closed systems, including a torque cycle motor can be designed to operate at both temperatures below zero degrees Celsius, it is sufficient that the design conditions promote the expansion and contraction of the working gas and that the materials chosen for their construction have the properties to perform their operational functions at design temperatures.
  • Binary cycle turbine engines based on the hybrid system concept may be constructed from materials and techniques similar to conventional engines, such as Brayton cycle engines, as it is a closed-loop gas engine, Considering the complete system, this closed-circuit working gas concept with respect to the external environment indicates that the system must be sealed, or in some cases leaks may be allowed provided they are compensated. Suitable materials for this technology should be noted, which are similar in this respect to Brayton external combustion cycle engine design technologies.
  • the working gas depends on the project, its application and the parameters used, the gas may be various, each will provide specific characteristics, as the gases may be suggested: helium, hydrogen, nitrogen, dry air, neon, among others.
  • Conversion chambers items that characterize the hybrid system, may be constructed of various materials, depending on design temperatures, working gas used, pressures involved, environment and operating conditions. One of these chambers is heated by power source, another cooled by a cooling or cooling system and another is insulated and these must be designed observing the requirement of thermal insulation to each other, to minimize the direct flow of energy from hot to cold areas, this condition is important for overall system efficiency.
  • Mass transfer occurs via a valve 23, an expansion rotor 25, and a compression rotor 27, and this transfer always occurs after the conversion of energy into useful work in process (ab) shown in Figure 2. .
  • the main driving force element is the turbine rotor indicated in 24 and is responsible for performing the mechanical work and making it available for use. This driving force element operates by the working gas forces of the engine.
  • Figure 1 shown in 11 shows the curves that characterize the differential cycle of four isobaric processes and four adiabatic processes, is the cycle that most closely approximates the new seven-process binary cycle, both of which are based on the concept of hybrid thermodynamic system. but the differential cycle is characterized by two conversion subsystems and its cycle consists of eight processes where two simultaneous processes always occur at a time, and in the binary cycle turbine engine is characterized by a conversion subsystem, a conservation subsystem, and seven processes occur and all occur simultaneously, indicated at 19 in figure 1;
  • Figure 2 shown at 21, represents the engine's mechanical model. Seven process, three isobaric and four adiabatic binary cycle turbine. In 213 the binary cycle mentions the regions of the mechanical model where the processes occur;
  • Figure 3 indicated at 31, shows a turbine engine concept model with an approximate realistic demonstration, and at 32 the binary cycle making reference to the regions of the mechanical concept model where the processes take place;
  • Figure 4 presents the turbine engine model with an approximate realistic demonstration again, pointing out in more detail its main elements and the channels and chambers where the conversion cycle and the energy conservation cycle occur;
  • Figure 5 represents, indicated in 51, 52 and 53 three curves of the binary cycle under different conditions between the conversion and conservation cycles, showing how the power differentials occur as a function of greater or lesser mass transfer between the subsystems;
  • Figure 8 is a diagram of an example of using a binary cycle turbine engine for power generation
  • Figure 7 shows a diagram of an example of using a binary cycle turbine engine for power generation from a thermonuclear battery, pointing out possibilities for space designs or applications in environments without combustion atmosphere;
  • the binary cycle engine consisting of an energy conversion subsystem, an energy conservation subsystem, an isobaric heating process, an isobaric cooling process, an isobaric thermally isolated compression process, two adiabatic expansion processes. and two adiabatic compression processes is based on a hybrid thermodynamic system because it has two interdependent thermodynamic subsystems which each perform an interacting thermodynamic cycle and can exchange heat, work and mass as shown in Figure 1, indicated by 19.
  • Energy input is indicated by 1 10
  • energy output, ie cooling is indicated by 1 12
  • useful work is indicated by conversion cycle paths (abcda) and conserved energy is indicated by cycle paths conservation (ab-c'-d'-a).
  • FIG. 2 shows the hybrid thermodynamic system again and the non-differential binary thermodynamic cycle
  • 21 shows the mechanical model representing a binary cycle turbine motor
  • a heating chamber that is the power input is shown in 22
  • the mass of gas is heated by the power source in an isobaric pressure (Ph) process
  • the temperature increases from the value (Ta) to (Tb)
  • the working gas gains pressure to act on the turbine rotors.
  • Conversion 24 and Preservation 25 a three-way proportional control valve 23 is used to direct the desired gas mass to the preservation process.
  • the turbine rotor of the conversion process 24 conducts the working gas to the cooling chamber 28, in this chamber the gas mass is cooled in an isobaric pressure (PL) process, the temperature decreases from the value (Tc) to (Td ), the conversion process compressor rotor 26 performs the gas compression process adiabatically back to the heating chamber 22.
  • the conservation process turbine rotor 25 conducts the conservation gas mass to the compression chamber 29, thermally insulated, in this chamber the gas mass is cooled in an isobaric pressure (PL ') process, the temperature reduces from the value (Tc') to (Td '), the conservation process compressor rotor 27 performs the process of compression of the gas mass and its associated conservation energy adiabatically back to the heating chamber 22.
  • the energy input is indicated by 21 1, the gas energy dissipation after it has performed 212.
  • Useful work is obtained on axis 210. Therefore, the basic design of the binary cycle turbine engine is defined by two thermodynamic subsystems formed by four sets of rotors, 24, 25, 26 and 27, among these.
  • FIG 213 shows the graph of pressure and volumetric displacement demonstrating how the processes that form the non-differential binary cycle that occur in the mechanical model of turbine engine 21 occur, all processes, also called thermodynamic transformations, occur simultaneously
  • the path (ab) shows the isobaric processes of alia temperature of the conversion subsystem and conservation subsystem, but in this path, the conservation process does not use the energy of the source, this only occurs at the operational start of the turbine engine until it reaches the potential differential, from this moment the energy is conserved, that is, the energy of the conservation cycle process (ab) equals the process energy (c'-d ! ) of the conservation cycle compression process.
  • Path (bc) represents the conversion subsystem adiabatic expansion process, this process has the same energy as the conversion subsystem adiabatic compression process (da).
  • the path (b-c ') represents the adiabatic expansion process of the conservation subsystem, this process has the same energy as the adiabatic compression process (d' -a) of the conservation subsystem.
  • the path (cd) represents the heat dissipation isobaric compression process of the energy conversion subsystem. Irajeio (c'-d ! ) Represents the isobaric compression process of the conservation subsystem, this energy is not dissipated, it remains conserved to maintain thermodynamic potential.
  • the presented binary cycle turbine engine operates by a process composed of seven thermodynamic transformations, also called processes, which form the binary cycle of turbine engine 21 being a process or transformation of high temperature heating (ab) isobar expansion.
  • energy conversion and conservation systems, and the gas fraction ( ⁇ ) of the conservation subsystem only receives energy from the hot source at the start of the turbine engine, and then in continuous operation, this fraction of gas conserves its energy by alternating between heat and kinetic energy by lending to maintain the engine's operating potentials, not being used to produce external work, an adiabatic power conversion subsystem (bc) expansion process or transformation, an adiabatic subsystem expansion process or transformation energy conservation (bc !
  • a process or transformation of low temperature cooling (cd) isobar compression of the energy conversion means an isobaric (c'-d ') compression process or transformation of the energy conservation subsystem, an adiabatic compression process or transformation of the energy conversion (da) subsystem, an adiabatic compression process or transformation of the energy conservation subsystem (d'-a) is a modulation process or also called working gas mass transfer control and energy conservation through a three-way valve between the conversion and conservation subsystems that occurs together with the adiabatic expansion processes of both subsystems.
  • the conservation subsystem has some very important functions, the most important being the definition of the potentials in which the engine will operate.
  • Thermal motors operate between two potentials, because to produce work mass flow is required, and flux can only occur when there is a potential difference that generates a mass flow from the highest potential to the lowest potential, motion, and consequently, work.
  • the thermal motors designed based on the open or closed systems have constant working gas mass, to generate potential difference a temperature difference is also necessary, when the mass is constant, the potential difference will depend on the temperature only verify through the equation of the universal gas law.
  • the most important function of the conservation subsystem is to generate a difference also in the working gas mass between the heating and cooling chambers, so the potential difference will depend, besides the temperature difference, also on the mass difference, but it is important. Since the project considers that the engine will not be able to perform all the work that the gas mass and the temperature difference allow, part of this work cannot be used, it must be conserved with the function of maintaining the potential difference, that is, mass, this energy is not lost, it is conserved and promotes greater motor efficiency to the limit where all the mass is used for conservation, in which case the efficiency will tend to the maximum, close to 100%, but the work will tend to the minimum, close to zero. Therefore the design of an engine must follow criteria between efficiency and work.
  • the motor needs power to generate the potential differential, but once established, it will be maintained throughout its operation, so the motor must be designed and its process controlled so that it does not convert useful work to energy. used to maintain the potential differential, if it does, efficiency will fall.
  • Figure 3 shown at 31, shows a turbine engine concept model with an approximate realistic demonstration, in the region between points (a) and (b) the isobaric heating process occurs between points (b) and (c) the adiabatic process of expanding the energy conversion subsystem occurs between points (b) and (c ') the adiabatic process of expanding the energy conservation subsystem occurs between points (c) and (d ) occurs the isobaric process of cooling of the working gas of the energy conversion subsystem, between points (c ') and (d') occurs the isobaric process of compression of the energy conservation subsystem, between points (d) and (a) the adiabatic compression process of the energy conversion subsystem occurs, between points (d ') and (a) the adiabatic compression process of the energy conservation subsystem occurs.
  • path (ab) shows the high temperature isobaric process of the conversion subsystem and conservation subsystem, but in this path, the conservation process does not use the energy of the source, this only occurs at the operational start of the engine until it reaches the potential differential, from this moment the energy is conserved that is, process (ab) of the conservation cycle is the same as process (c'-d ') of the compression process.
  • the path (bc) represents the adiabatic expansion process of the conversion subsystem, this process energy equal to the adiabatic compression process of the conversion subsystem.
  • the path (b-c ') represents the adiabatic expansion process of the conservation subsystem, this process in energy equal to the adiabatic compression process (d' ⁇ ) of the conservation subsystem.
  • the path (cd) represents the heat dissipation isobaric compression process of the energy conversion subsystem.
  • the path (c'-d ') represents the isobaric compression process of the conservation subsystem, this energy is not dissipated, it remains conserved to maintain the thermodynamic potential.
  • Figure 4 indicated at 41, shows the turbine engine concept model with a realistic demonstration in more detail
  • region 42 is shown the rotors of the power conversion subsystem compressor
  • region 43 is shown the rotors of the compressor of the energy conservation subsystem
  • region 44 is shown the chamber of the isobaric working gas heating process
  • region 45 is shown the three-way proportional control valve that has the function of channeling part of the gas mass of work for the turbines of the energy conservation subsystem
  • the turbine rotor of the energy conservation subsystem in region 46 the turbine rotor of the energy conservation subsystem is shown
  • region 47 the turbine rotors of the energy conversion subsystem are shown
  • region 48 is shown compression chamber of the isobaric process of cooling of the energy conversion subsystem
  • region 41 1 the compression chamber of the compression process is shown.
  • FIG. 5 shows the binary cycle under different operating conditions of the binary cycle turbine engine, in almost all working gas is used in the energy conversion process in the conversion subsystem and a small fraction of the gas mass is used in the conservation process of energy, in this case the working gas is subject to a lower potential differential, although almost all the working gas participates in the conversion process, the efficiency is lower since the efficiency is proportional to the difference of the potentials defined by (Ph) and (PL), in 52 a larger fraction of the working gas is used in the energy conservation process in the conservation subsystem compared to the graph indicated in 51, and a larger fraction of the gas mass is used in the conservation process.
  • the working gas is subject to a higher potential differential than the previous case, the efficiency increases, since the efficiency is proportional to the difference of the potentials defined by (Ph) and (PL), in the third graph, indicated By 53, the gas mass of the conservation process is even larger, it can be observed that in this case the work decreases, but the efficiency increases in relation to the two previous cases, showing that As more gas mass is used in the conservation process the efficiency increases but the work decreases tending to approach zero and the process tends to turn into a continuous adiabatic process without work where the gas expands and compresses and the energy is now in the form of mechanical kinetic energy and sometimes in heat in the gas.
  • Table 1 shows the seven processes (ab, bc, bc ⁇ cd, c'-d ', da, d ! -A) that form the non-differential binary turbine engine cycle, shown step by step with three isobaric processes and four adiabatic processes.
  • Table 1 shows all processes that form the binary cycle, but all steps, 1, 2, 3, and 4 occur simultaneously, unlike most processes that form differential cycle motor cycles which normally occur in and different from open and closed engine-based motor cycles which normally occur one by one sequentially except for the Brayton cycle,
  • Figure 6 shows, for example, a simplified power generation system, the turbine motor 61 is connected to a starter motor 82 and an electricity generator 63.
  • Figure 7 indicated by 71 shows, as an example, how the binary cycle turbine engine can be applied to form a system for generating electricity from a generic thermal source 72, which may be of various natures, thermosolar, geothermal. , thermonuclear or from various other sources, including by combustion or heat exchangers in cogeneration systems.
  • a thermal fluid is heated by the source and fed to the turbine engine heating system by means of a pump 73.
  • the flow of the thermal fluid is indicated by 74.
  • the thermal fluid may be any flowable, pumping fluid having properties. to carry the heat. As it is a motor that operates basically with heat and in several temperature ranges, it can be used to generation of energy or mechanical force in environments without atmosphere, eg in space or submerged.
  • the total input energy to the turbine engine is represented by the expression (j) below.
  • Hybrid based non-differential binary cycle turbine engines operate on heat, do not require combustion, although they can be used, do not require fuel burning, although they can be used, so they can operate in environments with or without atmosphere.
  • the thermodynamic cycle does not require changing the physical state of the working gas. Due to their properties set forth in this description, non-differential binary cycle turbine engines can be designed to operate over a wide temperature range, higher than most existing open or closed system based motor cycles.
  • Non-differential binary cycle turbine motors are fully flexible as to the energy source (heat).
  • Figures 6 and 7 show applications for the use of these motors for power generation and mechanical power generation from power sources. from various sources, indicating their applicability for mechanical power generation or power generation in environments with or without atmosphere, for projects using clean and renewable energy in aerospace and even combined cycle projects.

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Abstract

La présente invention concerne un moteur thermique comprenant une chambre de chauffage d'expansion isobare (22), une soupape de commande proportionnelle à trois voies (23), deux rotors de turbine (24) et (25), deux rotors de compresseur (26), et (27), tous reliés à l'axe (210), une chambre de compression isobare isolée thermiquement (29) et une chambre de refroidissement de compression isobare (28). Ces composants forment deux sous-systèmes, un sous-système de conversion d'énergie et un sous-système de conservation d'énergie, tous deux exécutant un cycle thermodynamique binaire de manière interdépendante, mais non différentielle. L'invention fonctionne avec du gaz, réalisant un cycle thermodynamique constitué par sept processus continus, c'est-à-dire que tous les processus se produisent simultanément, trois de ces processus étant « isobares » et quatre « adiabatiques » avec transfert de masse variable de l'un des sous-systèmes à l'autre dynamiquement, ladite masse pouvant être nulle ou partielle.
PCT/BR2018/050110 2017-04-25 2018-04-17 Moteur à turbine à cycle binaire constitué par trois processus isobares et quatre processus adiabatiques, et procédé de commande pour le cycle thermodynamique du moteur à turbine WO2018195621A1 (fr)

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BRBR102017008552-0 2017-04-25
BR102017008552A BR102017008552A8 (pt) 2017-04-25 2017-04-25 Motor turbina de ciclo binário composto por três processos isobáricos, quatro processos adiabáticos e processo de controle para o ciclo termodinâmico do motor turbina

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DE3233473A1 (de) * 1982-09-09 1984-03-15 Alfons Dipl.-Ing. Genswein (FH), 5160 Düren Waermekraftanlage mit "gas-dampf-kreisprozess", zur vollstaendigen umwandlung von waerme in mechanische arbeit
RU2107176C1 (ru) * 1995-01-12 1998-03-20 Леонид Павлович Козлов Способ работы теплового двигателя и тепловой двигатель
JP2003278598A (ja) * 2002-03-20 2003-10-02 Toyota Motor Corp ランキンサイクルによる車輌の排熱回収方法及び装置
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WO2006037291A1 (fr) * 2004-10-01 2006-04-13 Martin Ziegler Procedes et dispositifs pour utiliser de l'energie thermique, et leurs applications
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WO2013054519A1 (fr) * 2011-10-12 2013-04-18 パナソニック株式会社 Appareil de récupération de la chaleur des gaz d'échappement
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4035243A (en) * 1976-04-28 1977-07-12 Jerome Katz Method and apparatus for high volume distillation of liquids
DE3233473A1 (de) * 1982-09-09 1984-03-15 Alfons Dipl.-Ing. Genswein (FH), 5160 Düren Waermekraftanlage mit "gas-dampf-kreisprozess", zur vollstaendigen umwandlung von waerme in mechanische arbeit
RU2107176C1 (ru) * 1995-01-12 1998-03-20 Леонид Павлович Козлов Способ работы теплового двигателя и тепловой двигатель
JP2003278598A (ja) * 2002-03-20 2003-10-02 Toyota Motor Corp ランキンサイクルによる車輌の排熱回収方法及び装置
GR1004955B (el) * 2004-04-27 2005-07-28 Συσκευη μετατροπης θερμικης ενεργειας σε κινητικη μεσω αυθορμητης ισοθερμης συγκεντρωσης αεριου
WO2006037291A1 (fr) * 2004-10-01 2006-04-13 Martin Ziegler Procedes et dispositifs pour utiliser de l'energie thermique, et leurs applications
CN102155267A (zh) * 2011-01-24 2011-08-17 龚炳新 改进的空气发电机及其相应的循环
WO2013054519A1 (fr) * 2011-10-12 2013-04-18 パナソニック株式会社 Appareil de récupération de la chaleur des gaz d'échappement
JP2015232424A (ja) * 2014-06-10 2015-12-24 サムソン ヘビー インダストリーズ カンパニー，リミテッド 船舶用廃熱回収装置

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