RU2362881C2 - Multicylinder cubical expansion turbine - Google Patents

Abstract

FIELD: mechanical engineering.

SUBSTANCE: invention relates to heat and power engineering and mechanical engineering and can be used in the capacity of pumps, compressors, power plants with outer and inner heat supply for stationary and mobile objects. Turbine contains two axial cylinders, between which it is installed rotor faceplate and relative to each it is implemented, at least, by one co-axial cylinder, blades. Cylinders, which are in the same diametral plane, are concatenated to each other by means of passageways, communicating to cylinders' cavity in area of intervane capacities decreasing from maximal up to minimal in one and simultaneous increasing from minimal up to maximal in other forming, at least, one spiral air-gas channel of compression or expansion. Passageways of air-gas channels are circumferentially separated from each other by areas, including its communicating to each other of length not less than blade spacing. Induction and exhaust ports are implemented in the first and in the last cavities of air-gas channel.

EFFECT: turbine provides at its application in different heat engines of external and internal combustion to provide transformation of all potential energy of operating heat directly into mechanical and correspondingly provide indexes of high efficiency, affordability, ecological purity, and also overall-weight behaviour and minimal specific weight.

Description

The invention relates to a power system and transport engineering and can be used as pumps, compressors, power plants with external and internal heat supply for stationary and mobile facilities, for water, automobile, railway, air transport, for thermal power plants, as well as in space technology .

The closest analogues of the claimed turbine by design are rotary-vane rotor machine (Application RU No. 20021132702 - prototype) and an engine with external heat supply (Application RU No. 2002116338 - analogue) containing at least one annular cylinder with an eccentrically installed in rotor, made in the form of a faceplate with an annular cylindrical protrusion, in the longitudinal slots of which are installed blades, inlet and outlet windows and a bypass channel.

The main disadvantages of these machines and the engine is the limited range of use of excess parameters of the working fluid during expansion (pressure, temperature), which limits the thermal and effective efficiency.

The objective of the invention is the creation of a volume expansion turbine with an increased range of variation in working volumes, ensuring the efficient use of all excess pressure and the maximum use of thermal energy to perform useful work, as well as reducing mechanical losses.

The problem is solved in that the turbine containing at least one annular cylinder with an eccentrically mounted rotor in it, made in the form of a face plate with an annular cylindrical protrusion, in the longitudinal slots of which are installed blades, inlet and outlet windows and an overflow channel, according to the invention contains two axial cylinders between which a rotor faceplate is mounted and with respect to each of which at least one coaxial cylinder is made, while cylinders lying in one diametrical plane spans are connected in series with each other bypass channels communicating the cavity of the cylinders in the zone of decrease in interlobed volumes from maximum to minimum in one and at the same time increase from minimum to maximum in another, forming at least one spiral-shaped flow part of compression or expansion, while the bypass channels of the flow part in the circumferential direction are separated from each other by zones that exclude their communication with each other with a length of at least the pitch of the blades, and the inlet and outlet windows are made in the first and last cavities of the flowing part.

Bypass channels communicating the cylinders with each other can be made directly in the cylindrical walls separating them from each other.

Cylinders lying in one diametrical plane and forming one flow part can be made with cross sections successively increasing from cylinder to cylinder, forming a flow part of the expansion, or with successively decreasing, forming a flow part of compression.

The change in cross sections is provided by increasing or decreasing the length of the cylinders in the axial direction from the faceplate, while the protrusions of the faceplate, blades and support liners are made with a length corresponding to the width of their cylinders.

The flow parts of expansion and contraction can be performed both by centrifugal and internal combustion, may contain two flow parts formed by interconnecting cylinders located in one diametrical plane or two flow parts formed by cylinders located in two diametric planes, while one flow part performs expansion function, the second compression, the last cavity of which in the zone of minimal inter-blade volumes is communicated by the bypass channel with the first cavity of the flow part in the zone of its minimal inter-blade volumes, where a candle and a nozzle or only a nozzle (diesel) are also installed. With external mixture formation, an injector for fuel injection can be installed in the cylinder wall of the flow part of the compression. An inlet window is made in the first cavity of the flow passage of the compression in the zone of maximum interspersed volumes, and an outlet window is made in the last cavity of the flow passage of the expansion in the zone of maximum inter-blade volumes.

In addition, a combined cycle consisting of two - a duty cycle of an internal combustion engine and a duty cycle of a gas-steam turbine with internal heat supply can be implemented in a turbo engine, for which the engine is equipped with a source of excess pressure of a vaporizing liquid (water, water-alcohol mixture, etc.) , which bypass channel is in communication with the first cavity of the flow passage of the expansion in the zone after expansion of the combustion products of the fuel. Entering a gas with a temperature of 1200-1700 ° C and with a pressure of 5-12 kg / cm ² , the liquid, evaporating in a high-temperature gas, forms a gas-vapor working mixture with it at a lower temperature and higher pressure, while the first half of the first cavity performs the function of an internal combustion engine and a gas generator for the second half of the cavity, which performs the function of a steam-gas generator of mixing action and generates a gas-vapor mixture for the rest of the flow part of the expansion, when moving along which it expands to atmospheric gas pressure and before condensation of the vapor in the liquid.

The liquid can be used as a cooling liquid before being introduced into the flow part of the expansion and passed through the cooling system of the high-temperature expansion zone of the fuel combustion products, while the cooling system performs the function of a regenerative heat exchanger. The heat accumulated by the liquid is used to carry out work and, accordingly, increases thermal efficiency.

When using a turbine as a heat engine with an external heat supply operating according to the Stirling thermodynamic cycle, it contains an external heater in contact with the cylinder walls of the expansion duct, an external cooler in contact with the cylinder walls of the compression duct, a recuperative heat exchanger, and two bypass channels, one of which the last cavity of the flow part of the compression in the zone of minimum inter-blade volumes reports with the first cavity of the flow part of the expansion also in the zone m of minimal interlobe volumes and passes through a recuperative heat exchanger and an external heater, and the second bypass channel informs the last cavity of the expansion flow section in the zone of reduction of its interlobe volumes from maximum to minimum with the first cavity of the compression flow section in the increase zone from its minimum to maximum interlobe volumes and passes through said recuperative heat exchanger.

In addition, to operate the turbine as an engine with an external supply of heat, one flow part can be used, the cavities of which, from the first to the last cylinder, are used as expansion ones, and the last cavity of the last cylinder as a compression cavity, while the bypass channel communicating the cavities of the last cylinder passes through a recuperative heat exchanger, and the second bypass channel communicates a compression cavity in the zone of its minimum inter-blade volumes with the first expansion cavity also in the zone of minimum volumes and ohodit through said regenerative heat exchanger and an external heater.

In addition, cylinders lying in the same diametrical plane can function as independent expansion and compression stages and each contain a heater, a recuperative heat exchanger and a cooler, while the cylinders from the first to the last sequentially communicate with each other bypass channels communicating the output from the regenerative heat exchanger one cylinder with the entrance of the expansion cavity of another cylinder and passing through the heater, and the last cavity of the last cylinder in the zone of decrease of its intersection maximum to minimum volumes is communicated by a bypass channel passing through the recuperative heat exchanger of the last cylinder and an external heater, with the working cavity of the first cylinder also in the zone of minimal inter-blade volumes.

In addition, the turbine may contain several single-cylinder turbines and one multi-cylinder with a common rotor shaft, which from the first to the last operate as expansion high pressure in the overheating mode without recovery and external coolers, while one of the two flow parts of the last multi-cylinder turbine is used as an expansion with continued expansion and contains a spiral-shaped multi-cylinder flow part of the expansion, and its other flow part is used as a compressor with a large step compression and contains a spiral-shaped compression flow part equipped with an external cooler, while the recuperative heat exchanger is installed in the last turbine in the channel communicating the last expansion flow chamber cavity with the first compression flow chamber cavity, the last cavity of which in the zone of minimum inter-blade volumes is provided with an outlet window communicating the bypass channel with the inlet window of the expansion cavity of any of the previous turbines or with all simultaneously passing through the regenerative heat exchange ir and an external heater.

The turbine can be used as a steam in water or oil vapor, while it is possible to provide higher thermal efficiency than in conventional steam turbines operating according to the Rankine cycle and in which it is impossible to carry out isothermal expansion of steam due to the high speed of the working fluid in the flow part and its linear length.

The operation of the turbine on water vapor is carried out in conjunction with the equipment used for conventional steam turbines of non-voluminous expansion - a boiler, superheater, feed pump, condenser. The turbine can operate in the range of wet and superheated steam without steam condensation to a liquid state and, accordingly, without the above equipment, while the thermal and effective efficiency will be lower.

In addition, a combined cycle with an external supply of heat on a gas-vapor mixture can be realized in a turbo engine, for which the turbo engine is equipped with an external water heater operating on organic or hydrocarbon fuel, a feed pump, a gas pump-compressor, a steam and gas generator, an economizer and bypass channels, one of which are sequentially reported by the flue gas exhaust window of an external heater, an economizer, a gas compressor, a steam and gas generator, and a first cavity of the turbine expansion flow passage us, and the second output sequentially informs a feed pump with the cooling system of the gas compressor with an economizer, an external heater and the steam-gas generator.

As a gas compressor, the turbine compression duct is used, which ensures the exhaust of flue (exhaust) gases and their subsequent compression to the operating pressure of the steam generator. A separator can be made at the exhaust of the turbo engine to separate the condensate from the residual gases by centrifugation. Condensate circulates in a closed circuit and, after purification from dissolved sediments, can flow back to the inlet of the feed pump. Sludge containing toxic substances from combustion products is easily disposed of or neutralized.

Almost all of the thermal energy of fuel combustion is used to heat water and evaporate in a steam and gas generator with the formation of a gas-vapor mixture, which then expands in the flow part of the turbine to atmospheric pressure.

The operation of the turbine with oil vapor can also be carried out both with steam without condensation, and with condensation, for which, in addition to the equipment used in steam turbines or without it, it is necessary to carry out the work circuit tightly and to start and turn on the heaters, vacuum the work pump with a vacuum pump a turbine filled with oil, for example vacuum, and after stopping the turbine, fill its working cavities with inert gas to a pressure not lower than atmospheric, excluding the oxidation of oil vapors by atmospheric oxygen . The use of oil as a working fluid in a closed turbine circuit solves the problem of lubricating friction surfaces and, accordingly, reducing mechanical losses.

Changing revolutions or boosting the power of all types of turbines with an external heat input can be done by changing the supply of the working fluid through the inlet window of the first cavity of the expansion duct, or by sequential supply in the zone from minimum inter-blade volumes to maximum, or bypassing the section of the expansion zone by analogy with the steam inlet conventional steam turbines, or by supply and discharge from the circuit of the working fluid.

To increase thermal efficiency due to the intensification of the processes of supplying and removing heat to the working fluid and thereby creating conditions for the isothermal flow of expansion and compression processes, the inner, near the rotor shaft, and outer peripheral surfaces of the rotor face plates protruding beyond the cylinders can directly contact the working bodies of the heater in the hot zone and the cooler in the cold zone, while the faceplate acts as an additional regenerative heat exchanger, increasing the degree of isothermal expansion and contraction processes.

The rotor faceplate can be made spiral-shaped from the center to the periphery or radial channels for supplying them with a heating medium or cooling due to centrifugal forces, which will additionally provide heat supply along the entire length of the expansion expansion part and heat removal along the entire length of the compression compression part in engines with external supply of heat, and in internal combustion engines for cooling or lubricating friction pairs due to centrifugal forces.

To solve the problem of reducing friction surfaces, increasing the service life of the blades and reducing mechanical losses according to one of the options, the blades can be supported by shanks on a support ring mounted on the inner cylindrical wall with the possibility of circumferential movement (on rolling or sliding bearings), and be spring-loaded with shanks relative to the protrusion faceplates, which ensures the retention of the blades at the inner wall of the cylinder and the reciprocating movement of the blades relative to each other in the circumferential direction, as well as moving along the cylinder with a constant angle of 90 ° to the cylindrical walls.

According to the second version, the blades can be installed with shanks in the corresponding arcuate longitudinal with radial walls in the circumferential direction of the grooves of the annular separator mounted on the inner cylindrical wall of the cylinder with the possibility of rotation relative to it. The blades are mounted in the grooves of the separator with the possibility of circumferential reciprocating movement. The shanks of the blades can be spring-loaded in the grooves of the separator in a circumferential direction on both sides to eliminate vibration when shifting the pressure of the working fluid on the blades and to create a peripheral force that facilitates the rapprochement and divergence of the blades when moving their shanks along the grooves of the separator.

According to the third variant, the protrusions of the rotor face plate in front of each blade in the direction of their working movement can be provided with a movable part that is identical in cross section and profile to the protrusion and interacts with it with the possibility of circumferential relative movement, for which a longitudinal groove is made along the entire width of the protrusion or moving part arched walls coaxial with the rotor, and in the movable part or protrusion a corresponding arched longitudinal protrusion, while the movable parts of the protrusion are spring-loaded relative to the circumferential direction itelno fixed protrusions rotor faceplate.

In addition, the blades can be made integral or connected by a fixed connection to the ring in the form of an impeller with blades (blades) mounted on the inner wall of the cylinder with the possibility of circumferential movement (rotation), while the protrusions of the rotor face plates on each side in the circumferential direction are equipped with movable parts identical in cross section to the protrusions of the faceplate and interact with them with grooves or protrusions, for which, similarly to the previously described embodiment of the protrusions of the faceplate with movable parts, in the protrusions or movable parts, a longitudinally arched groove or protrusion arched in the circumferential direction is made over the entire width of the protrusion, and corresponding protrusions or grooves are in the movable parts or protrusions, while the movable parts are circumferentially spring-loaded relative to the protrusions of the faceplate.

In all of the above options, the opposite ends of the blades are made without a supporting surface and the blades move, held either by springs or a separator, without contact with the opposite cylindrical wall of the cylinder. At the ends of the blades, labyrinth seals can be made.

The above technical solutions also provide automatic elimination of gaps during wear of the friction surfaces of the blades with liners and liners with arched grooves of the protrusions and, accordingly, increase the life of the turbine as a whole.

The joints of the rotor faceplate with the ends of the cylindrical walls of the cylinders are sealed with ring seals, and the joints of the protrusions of the faceplate with the end walls of the cylinders behind the bypass zone are sealed with half rings (not shown).

The maximum degree of expansion of the working fluid in the flowing part of the expansion is provided in the first half of the first cavity of the first cylinder, which is a high-pressure cavity, the remaining cavities of the flowing part perform the function of bypassing from one to the other and expanding the working fluid to atmospheric pressure.

The potential energy of the working fluid in expansion machines (engines) is converted into mechanical work as much as possible in the first half of the first cavity of the flow part of the expansion and with its further movement along the flow part additionally in the zones of separation of the bypass channels from each other, in which a pressure drop is created on the blades, at this creates the torque distributed in the circumferential direction, is summed up on the rotor shaft.

In the flowing part of the compression, on the contrary, from the first working cavity to the last, the working fluid is gradually compressed, and in the second half of the last cavity, compression is infinitely continuous with a maximum degree, while the flowing part performs the function of a multi-stage volume compression compressor.

In internal combustion engines, part of the compressed air in the compressor can be used to purge the outlet window of the expansion duct.

Figure 1 shows a schematic diagram of a 4-cylinder turbine, a cross section of one of the blocks; figure 2 is a section aa in figure 1; figure 3 is a linear diagram of parameter changes along the length of the 3-cylinder flow part of the expansion, where P is the pressure, V is the volume, R is the radius of the cylinder cavity, M _cr is the torque, figure 4 is a schematic diagram of a 2-cylinder engine internal combustion (cross section along the second block behind the rotor faceplate). Figure 5 shows the installation of the blades on the support ring, where 6 is the protrusion of the rotor, 18 is the hinge, 19 is the blade, 20 is the movable support ring, 21 is the spring. Figure 6 shows a variant with the installation of the blades in the separator, where 18 is the hinge, 19 is the blade, 22 the stationary protrusion of the rotor, 23 is the movable protrusion of the rotor, 24 is the separator, 25 is the spring. Figure 7 shows a variant with an impeller, where 25 is a spring, 26 is a stationary protrusion of the rotor 27, 28 is the movable protrusions of the rotor, 29 is the impeller.

On Fig shows a schematic diagram of a variant of a turbo engine in oil vapor, where 30 is a turbine, 31 is a boiler, 32 is a vacuum pump for pumping atmospheric air from the working circuit, 33 is an inert gas tank, 34 is a condenser, 35 is a valve communicating a vacuum pump and a working circuit, 36 is a valve communicating with an inert gas tank and a working circuit, 37 is a pump for supplying oil from a condenser to a boiler.

The turbine, FIGS. 1, 2, contains two blocks 1 and 2, each consisting of two cylinders 3 and 4. A rotor with a faceplate 5 is mounted between the cylinder blocks. On the faceplate 5, cylindrical protrusions are made 6. For the longitudinal grooves of the protrusions blades 7 are installed. Cavities of cylinder 3 communicate with bypass channel 8, cavities of cylinder 4 communicate with bypass channel 9, and adjacent cylinder cavities in each of the two blocks communicate with bypass channels 10, forming two spiral grooves on each side of the rotor faceplate s part, in the first and last cavities which are formed intake and exhaust ports (not shown).

The engine, figure 4, contains in each block two cylinders 3 and 4, the cavities of which are successively communicated by the bypass channels 8, 9 and 10. In the cylinder 4 there is an exhaust window 11, an inlet window 12 and an additional outlet 13 communicating with the bypass channel 14 with the inlet a window 15 of the central cavity of the cylinder 3. After the inlet window 15, a spark plug 16. is installed. In the cylinder 4 in the area between the inlet window 12 and the outlet 13 there is a nozzle 17 for continuous fuel supply.

The operation of a multi-cylinder turbine as a heat engine is illustrated in the embodiment of the internal combustion engine of FIG. 4.

When the engine is started, air enters through the inlet window 12 and, compressed in the inter-blade volumes, moves to the exhaust window 13. Fuel is continuously injected through the nozzle 17. Through the exhaust window 13, the air-fuel mixture through the bypass channel 14 enters the inlet window 15 and through it into the zone of minimum inter-blade volumes of the first cavity of the central cylinder 3, where it is ignited by the spark plug 16. The combustion products, while continuing to move and expanding in increasing inter-blade volumes, act on the blades and rotate the rotor.

Having reached the bypass channel 8, the gases through it from the decreasing inter-blade volumes of the first central cavity of the cylinder 3 enter the increasing inter-blade volumes of its second cavity. Having passed the separation zone of inter-blade volumes and bypass channels from each other, the gases, having reached the bypass channel 10, communicating adjacent cavities of the cylinders 3 and 4, come from the decreasing inter-blade volumes of the second cavity of the cylinder 3 into the increasing inter-blade volumes of the first cavity of the cylinder 4. After half a revolution of the rotor, having passed the next separation zone, the gases through the bypass channel 9 enter the second cavity of the cylinder 4 and then, having reached the outlet window 11, go beyond the flow part of the expansion.

The operation of the steam-oil version of the turbo engine of Fig. 8 is as follows.

Before starting the engine, the valve 35 is opened and the vacuum pump 32 is used to pump out atmospheric air from the working circuit of the engine. After evacuation of air, the valve 35 is closed and the boiler 31 is turned on. After the formation of oil vapor, it flows under high pressure from the boiler into the first cavities of the flow parts of the turbo engine for expansion. After expansion, oil vapor enters the condenser 34 and condenses. After cooling, the oil pump 37 is fed into the boiler 31.

Before the turbo engine stops, the oil boiler 31 is turned off. After cooling the oil, the valve 36 opens, and the working circuit of the engine is filled with inert gas from the tank 33 to a pressure slightly higher than atmospheric pressure.

At the next start of the turbo engine, which was under overpressure of an inert gas, it may not be removed from the working circuit by pumping with a vacuum pump.

Depending on the value of the initial parameters of the working fluid, the corresponding number of cylinders for the flow part of the expansion is selected.

When choosing the number and transverse dimensions of the cylinders, the geometric increase in the volume of the cylinder cavities is taken into account due to the increase in their circumferential length, which depends on the magnitude of the eccentricity of the rotor, the thickness of the protrusions of the faceplate, the thickness of the cylindrical walls of the cylinders, and the width (radial) of the cylinders.

The multi-cylinder volume expansion turbine provides the possibility of implementing more efficient thermodynamic cycles with the conversion of the potential energy of the working fluid directly into mechanical rotational energy using all the excess pressure of the working fluid and almost all the heat to perform useful work, and is the basic module for creating highly efficient, economical and environmentally friendly heat engines.

The simplicity and manufacturability of the design using the most effective kinematic mechanism, the compact spiral-shaped flow part with the centrifugal nature of the movement of the working fluid during expansion provide high rates of efficiency, economy and design perfection.

Significant factors ensuring the achievement of a high performance by a turbo engine are that, in contrast to the well-known internal combustion engines, steam engines with a crank mechanism and a Wankel rotary engine, in which the pressure of the working fluid, which decreases with expansion, creates torques through constant areas and through the appearing and disappearing shoulder (crank radius) and is not fully used, providing an effective pressure of only 20-25% of the maximum pressure developed by the product using combustion chambers, the pressure in the turbo engine decreases from the center to the periphery and is fully used, providing an increase in the effective pressure up to 50% of the maximum, which creates torque evenly distributed in the circumferential direction on gradually increasing areas and radii, ensuring its more efficient use and, accordingly, gain in strength and overall torque on the rotor shaft.

The balance in the axial and circumferential directions, the absence of reciprocating movements of the working fluid and parts and assemblies in the rotor mechanism exclude turbine vibrations, and the operation of the working fluid overpressure to atmospheric pressure ensures a silent exhaust.

Large torque at minimum revolutions and, accordingly, the starting moment (low speed coefficient), gentle throttle characteristics provide stepless variation of the output power on the shaft in a wide range, eliminating the need for a step gearbox in mobile objects.

Claims (11)

1. A turbine comprising at least one annular cylinder with a rotor eccentrically mounted in it, made in the form of a faceplate with an annular cylindrical protrusion, in the longitudinal slots of which there are blades, inlet and outlet windows and an overflow channel, characterized in that it contains two axial cylinders between which the rotor faceplate is mounted and with respect to each of which at least one coaxial cylinder is made, while the cylinders lying in the same diametrical plane follow o are connected to each other bypass channels communicating the cavity of the cylinders in the zone of decrease in interlobed volumes from maximum to minimum in one and at the same time increase from minimum to maximum in another, forming at least one spiral-shaped flow part of compression or expansion, while bypass channels the flow parts in the circumferential direction are separated from each other by zones that exclude their communication with each other with a length of at least the pitch of the blades, and the inlet and outlet windows are made in the first and last cavities of the flowing part. 2. The turbine according to claim 1, characterized in that the outlet and inlet windows are successively made behind the bypass channel communicating the penultimate and last cavities of the flowing part in the zone of maximum interspersed volumes, and in the zone of the minimum there is an additional outlet communicating with the bypass channel with the outlet window first the cavity of the flow part of the expansion, made in the zone of its minimum inter-blade volumes, in which the spark plug is also installed after the inlet window, and in the last cavity, in the zone between the inlet window and body exhaust, nozzle installed. 3. The turbine according to claim 1, characterized in that behind the bypass channel communicating the penultimate and last cavities of the flowing part, the outlet and inlet windows are successively made in the zone of maximum inter-blade volumes, and in the zone of the minimum there is an additional outlet communicating with the bypass channel with the inlet window of the first the cavity of the flowing part of the expansion, made in the zone of minimal inter-blade volumes, after which the nozzle is installed. 4. The turbine according to claim 1, characterized in that it is equipped with an external heater in contact with the walls of the cylinders forming the flow part of the expansion, and an external cooler in contact with the walls of the cylinders of the flow part of the compression, a regenerative heat exchanger installed in the bypass channel communicating the last cavity of the flow expansion part with a first cavity of the flow part of the compression, and a bypass channel communicating the outlet window of the last cavity of the flow part of the compression, made in the zone of minimal inter-blade volume s, with an inlet window of the first cavity of the flow path of the expansion, also made in the zone of minimal inter-blade volumes, while the bypass channel passes through a recuperative heat exchanger and an external heater. 5. The turbine according to claim 1, characterized in that the flow part of the expansion is formed by communicating cylinder cavities from the first cavity of the first cylinder to the first cavity of the last cylinder and is equipped with an external heater in contact with the walls of its cylinders, a regenerative heat exchanger installed in the bypass channel communicating the cavity the last cylinder in the zone of decrease in interlobed volumes from maximum to minimum in one and a simultaneous increase from minimum to maximum in another, external cooler, cont casing with the walls of the last cavity of the last cylinder, which is equipped with an outlet window made in the zone of minimal interlobed volumes, communicating bypass channel with an inlet window of the first cavity of the flow part of the expansion made in the zone of minimal interlobed volumes, while the bypass channel passes through a regenerative heat exchanger and an external heater . 6. The turbine according to claim 1, characterized in that the flow part of the expansion is equipped with an external heater in contact with the walls of its cylinders, an external cooler, a regenerative heat exchanger installed in the bypass channel communicating the last cavity of the flow part of the expansion with the cavity of the external cooler, the output of which is communicated through a feed pump, a recuperative heat exchanger and an external heater with a first cavity of the flow part of the expansion. 7. The turbine according to claim 6, characterized in that it contains a sealed working circuit filled with oil, an inert gas overpressure source and a vacuum pump periodically communicating through shut-off devices with the working circuit. 8. A turbine according to any one of claims 1 to 7, characterized in that the cylinders forming the flow part are made with cross sections successively increasing from cylinder to cylinder or decreasing sequentially. 9. A turbine according to any one of claims 1 to 7, characterized in that the bypass channels communicating the cylinders with each other are made in cylindrical walls separating them from each other. 10. A turbine according to any one of claims 1 to 7, characterized in that the blades are provided with shanks on one side only, while the blades are mounted with the possibility of non-contact movement relative to the peripheral cylindrical walls of the cylinders and the end walls, with the possibility of reciprocating movements relative to each other in the circumferential direction and ensuring movement along the cylinders at an angle of 90 ° to their cylindrical walls. 11. A turbine according to any one of claims 1 to 7, characterized in that the protrusions of the rotor faceplate are provided with movable parts that are identical in cross section and profile to the protrusions and interact with them with the possibility of circumferential reciprocating relative movement, for which in movable parts along the entire width the protrusion is made an arcuate groove or protrusion, and in the protrusions, respectively, the protrusion or groove, while the movable parts are spring-loaded relative to the protrusions in the circumferential direction, and the blades are made integral with the ring in the form of an impeller, setting one with the possibility of rotation on the cylindrical wall of the cylinder.

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