RU133564U1 - ADIABATED GAS-STEAM TURBO ENGINE ROMANOVA - Google Patents

Abstract

1. An adiabatic gas-steam turbo engine containing two mirror-identical blocks of annular cylinders, one of which is made eccentric, and the rest are concentric, the rotor concentrically installed between them, bypass channels communicating the eccentric cylinder with concentric cylinders, and inlet and outlet windows, characterized in that the concentric cylinders of the blocks and the rotor are formed by alternating fixed annular protrusions, in each of which at least one bypass channel with plane parallel walls, while the walls of the bypass channels of the blocks and the rotor are located at an angle to the diametrical-axial plane of the turbo-engine, providing, when they communicate, the location of their walls relative to each other at an angle of about 90 °, in addition, an annular receiver cavity is made after the eccentric cylinder of the blocks, the cylindrical walls of which are made bypass channels communicating with the eccentric cylinder and the turbine flow part of the turbo engine, and in the annular walls of the blocks separating the eccentric cylinders Cores and receivers, recuperator cavities are made, the input of which communicates with the source of the evaporating liquid, and the outputs communicate with the cavity of at least one bypass channel communicating an eccentric cylinder with an annular receiver cavity, in addition, in the cylindrical walls of the receiver cavity at the joints with the rotor end ring seals are installed in the form of spring-loaded rings or pneumodynamic impeller seals made in the form of spiral grooves coinciding with the direction of rotation of the rotor. 2. Adiab

Description

The utility model relates to power engineering and engine building and can be used for any stationary and mobile objects as a universal power plant generating mechanical energy and heat, in the form of a gas-vapor mixture or hot condensate, or at the same time mechanical energy, electric and thermal.

Known gas-steam turbo engine of full volume expansion, containing two mirror-identical blocks of annular cylinders, one in each of which is made eccentrically, and the rest concentrically with thin dividing walls, each of which has one bypass window. A rotor with annular protrusions is mounted concentrically between the blocks, in which blades are mounted on hinges for eccentric cylinders, and thin-walled blades are made for concentric cylinders (RF patent No. 2353536 - prototype).

The disadvantage of a turbo engine is the low efficiency of the turbine part, the expansion steps of which, except for the first, do not provide torque while simultaneously decreasing pressure and increasing volumes, working in the throttling mode, which also does not allow it to be used as an expansion with an external supply of the working bodies, instead of the well-known steam and gas turbines of volumetric expansion.

A turbine of radial, reactive-pulse, stepwise volumetric expansion is known, containing two mirror-identical blocks of annular cylinders formed by alternating fixed stationary annular protrusions with bypass channels, and a rotor concentrically mounted between them, made also with cylindrical protrusions and with bypass channels. In the central part of the turbine, annular cavities are made - receivers, into which a working fluid, gas or steam, ready for expansion, enters from an external source. The receivers have inlet windows uniformly located in the circumferential direction, through which the working fluid enters the flow parts of the turbine for expansion (application for utility model of the Russian Federation No. 2012111392 - prototype).

The technical tasks in creating the utility model were to ensure the maximum generation by the heat of combustion of the fuel of the pressure of the working fluid and the maximum efficiency of the volumetric conversion of the pressure of the working fluid into the rotational force of the shaft and the possibility of generating electricity directly, without a separate electric generator.

The first problem is solved in that in a turbo engine containing two mirror-identical blocks of annular cylinders, one of which is made eccentric, and the rest concentric, concentric mounted between them rotor, bypass channels communicating the eccentric cylinder with concentric cylinders, concentric cylinders of the blocks and rotor are formed alternating stationary annular protrusions, in each of which at least one bypass channel with plane-parallel walls is made, while the bypass walls are the blocks and rotor analgeses are located at an angle to the diametrical-axial plane of the turbo-engine, providing, when they communicate, the location of their walls relative to each other at an angle of about 90 °, in addition, after the eccentric cylinder of the blocks, an annular receiver cavity is made, in the cylindrical walls of which bypass channels are made connecting it with the eccentric cylinder and with the turbine flow part of the turbo engine, and in the annular walls of the blocks separating the eccentric cylinders and receivers, recuperator cavities, the entrance of which communicates with the source of the evaporating liquid, and the outputs communicate with the cavity of at least one bypass channel communicating an eccentric cylinder with an annular receiver cavity, in addition, end ring seals are installed in the cylindrical walls of the receiver cavity at the joints with the rotor in the form spring-loaded rings or pneumodynamic impeller seals made in the form of spiral grooves made coinciding with the direction of rotation of the rotor.

To increase the efficiency of reactive pulses, by “dividing” them into parts, one or several thin-walled flat blades uniformly spaced across the cross section parallel to the channel walls can be made in each bypass channel.

In addition, in order to increase the efficiency of the use of jet pulses when the engine operating mode changes from optimal to under-expansion when the fuel or vaporizing liquid is increased, one or several thin-walled flat blades at an angle of 90 evenly spaced across the cross section can be made ° to the rotor channels.

In addition, in order to ensure the generation of electricity directly by the turbo engine, the last from the center of the annular protrusions of the rotor are made in the form of permanent magnets, moreover, in blocks, in end walls located axially relative to the last protrusions of the rotor, or in the outer wall of the last cylinder (option), coaxially to the rotor magnets are placed the inductance windings, forming two electric generators.

In addition, in order to ensure the operation of only the turbine part of the turboelectric generator from an external source of the working fluid, the rotor can be made of two parts - the engine, containing ring protrusions with blades installed in them, and the turbine, containing ring protrusions with bypass channels interacting with each other by means of a lockable overrunning clutch, at the same time, channels are provided in the end walls of the blocks for supplying the working fluid to the annular cavities (receivers) of the blocks and gate valves that block the bypass nye channels between the eccentric block cavities and annular cavities receivers. During the operation of the turbine part of the turboelectric generator from an external source of the working fluid (gas or steam), its motor part remains stationary.

Figure 1 shows an exploded view of the main components of a turbo engine; figure 2 is a cross section of figure 1; figure 3 remote element A of figure 2; figure 4 is a schematic diagram of a power plant with a turboelectric generator for vehicles; figure 5 is a schematic diagram of a stationary multifunctional power plant.

The turboelectric generator (figure 1, 2, 3), contains two mirror-identical blocks 1, 2, between which the common rotor 3 is concentrically mounted.

In each block, in the center, an eccentric annular cylinder 4 is made. Behind it, in the radial direction, a concentric annular cavity 5 (receiver) is made. Cylinder 4 and receiver 5 communicate with each other bypass channels 6. Behind receiver 5, annular projections 7 are made, with bypass channels 8. The screen 9 is also made in the receiver.

Inlet windows 10 are made in the cylindrical wall of the receiver 5. Inlets 11, 12, a channel 13 for supplying fuel, a channel 14 for supplying water to the cavity of the recuperator 15, a combustion chamber 16, and a threaded channel 17 for the spark plug are made in the end wall of the stators.

The rotor 3 contains concentric annular protrusions 18, between which through cylindrical channels 19 are made for the hinges 20. In the longitudinal grooves of the hinges 20, blades 21 are installed, spring-loaded relative to the inner annular wall of the protrusion 18 by springs 19, (the variant is shown partially). The blades move along the cylinder without contact with the outer cylindrical wall. It is possible to make the inner cylindrical wall movable in the form of a ring mounted on a rolling or sliding bearing.

In the rotor, behind the annular protrusion 18, annular protrusions 22 are made in which bypass channels 23 are made.

The annular protrusions of the last stages of the rotor (FIGS. 1, 2) are made in the form of permanent magnets 24, while inductance windings 25 are mounted axially to the rotor magnets in the end walls of the blocks, forming two electric generators.

Inductance windings can be made in the outer cylindrical wall of the blocks coaxially with the rotor, also forming two radial type electric generators (option).

The generator can be used as a starter for a turbo engine powered by a small battery power.

In the cylindrical wall of the last cylinder of the blocks, exhaust windows 27 are made, communicating the flow parts of the turbo engine with the exhaust manifold 28, and exhaust windows 29, communicating with the atmosphere and the condensate collector (not shown).

For repeated use in the water cycle (condensate), the turbo engine contains a feed pump that communicates the condensate collector with channels 14 of the blocks, driven directly by a turbo engine (not shown).

After assembling the turbo engine, the annular protrusions 18 of the rotor with the blades 21 are located in the eccentric cylinders of the blocks, forming in each two cavities of uneven cross-section — a compressor, the first cavity from the center with the inlet window 11, and the second, main compression cavity with the inlet window 12. The cavities are connected between a bypass channel 26 made on the inner end wall of the cylinder.

The remaining rows of annular protrusions 22 of the rotor are located between the rows of annular protrusions 7 of the blocks, respectively, the rows of annular protrusions of the blocks are located between the annular rows of protrusions of the rotor, and, alternating, form the steps of volumetric expansion.

Valves can be installed in the blocks to open, close, or adjust the passage section of the inlet windows 10 in order to optimize the operation of the motor and turbine parts of the turboelectric generator.

At least one or more flat thin-walled blades uniformly spaced along their cross section and parallel to their walls (not shown) can be made in the bypass channels of the cylindrical protrusions of the blocks and the rotor.

The turbine engine rotor is installed in the stators on two angular contact ball bearings, or, at increased working pressure, on two radial and two axial thrust bearings.

To exclude heat loss to the environment and ensure complete adiabaticity of the gas-vapor working cycle relative to it, the entire surface of the turboelectric generator is covered with a heat-insulating cover (not shown).

In an adiabatic gas-steam turbo engine, when a gas cycle is combined with a steam, three types of recovery are provided continuously: two non-contact ones with heat transfer to the water through the recuperator from the air-fuel mixture during compression and excess heat after ignition and high-temperature combustion and partial expansion for its preliminary heating before injection into pre-expanded gases , and contact recovery after injection of preheated water into hot gases with the formation of steam due to the heat of gases and gas ara mixture. With the overflow of water into gases, a fourth type of recovery can occur - condensation of water vapor in the flow part, while the heat of condensation of water can be returned to gases, increasing their pressure and working capacity before exhaust.

In case of excessive overflow of water into gases, the beginning of steam condensation can begin in the flowing turbine part of the turbo engine, while the heat of condensation of the steam is returned to the gas, increasing its partial pressure and working capacity.

In Fig.2, the rotor is depicted in the position of filling the bypass channels of the first row of rotor protrusions with the working fluid and creating the rotor and the working pulse blocks (working clocks) in all the bypass channels communicated - the charges of the working fluid emanating from the bypass channels of the blocks push the rotor.

In Fig. 3, the rotor 2 is depicted in the position of creation in all the communicating bypass channels of the rotor and the working impulse blocks (working cycles) —the rotor is repelled by the charges of the working fluid ejected from its bypass channels from the blocks, and the exhaust of the working fluid from the bypass channels of the last rotor stage through the exhaust window 27 into the exhaust manifold 28.

The operation of the turbo engine is as follows.

When starting a turbo engine in the initial period of rotation of the rotor 3, the blades 21, passing by the inlet windows 11, 12, cut off the atmospheric air and begin to compress it in decreasing inter-blade volumes. After the blades of the inlet window 12 pass into the inter-vane volumes, air is passed from the compressor cavity through the channel 26, which has entered through the inlet window 11 and fuel is injected continuously through the nozzle. When the combustion chamber 16 is reached, the air-fuel mixture is ignited by a glow plug installed in the threaded channel 17. With further movement of the rotor, a volumeless stepless expansion of gases is carried out with the creation of torque. When the blades reach the bypass channels 6, the gases through them enter the receiver 5 (gas and steam generator). At the same time, heated water is injected into the gases passing through the bypass channel 6, which has previously passed through the recuperator 15, and due to the heat of the high-temperature gases, a gas-vapor mixture is formed in the recuperator.

From the receiver 5, the gas-vapor mixture enters through the inlet windows 10 into the turbine part of the turbo engine, filling the bypass channels 23 of the rotor 3.

In general, the overall duty cycle of the turbine part consists of many separate duty cycles performed by the gas-vapor mixture during movement after inlet along several flowing parts simultaneously with bypass through the bypass channels of the rotor and blocks.

The duty cycle of each bypass channel of the rotor and blocks consists of four clock cycles.

The first cycle - "filling" the bypass channels of the first row of the rotor with a gas-vapor mixture. With further rotation of the rotor and uncoupling of its bypass channels with the inlet windows, a second clock cycle is performed - “cutoff”, then a third clock cycle is performed - “working” when communicating with the stationary channels of the blocks and, after that, a fourth clock cycle is again “cutoff”.

With further movement of the rotor in the circumferential direction, each of its channels again communicates with the next inlet window, is supplemented with a gas-vapor mixture to the initial pressure from the receiver, and then the cycles are repeated in the manner described above. Similar cycles are performed by bypass channels of subsequent rows of the rotor when communicating with the bypass channels of the blocks.

After starting the turbo engine and filling the bypass channels of the rotor of the first from the center of the row with gases or a gas-vapor mixture from the receiver, during its further movement, the pairs of the rotor and stator channels of the first stage are the first to interact, while the rotor is repelled in the direction of rotation by jet jets from the flat surfaces of the channels of the stationary blocks, while the pressure in the bypass channels of the rotor decreases, and in the bypass channels of the blocks increases. A partial sharp ejection of a gas-vapor mixture (working jet impulse) occurs from the rotor channels, which are under higher pressure, into the channels of the blocks, which are at start-up at atmospheric pressure and, after turning a step between the inlet windows, under lower pressure. In this case, the pressure in both channels becomes approximately equal.

With further movement of the rotor, its channels located in the next row from the center communicate with the channels of the blocks that previously communicated with the channels of the first stages of the rotor and are under pressure from the gas-vapor mixture, while the gas-vapor mixture, sharply flying out of the channels of the stationary blocks, pushes reactive jets rotor. Duty cycles are carried out in the reported bypass channels of the blocks and the rotor of the second stage after the charge enters the turbine flow section. After that, the cavities are disconnected. Further, in the circumferential and in the radial direction from the center to the periphery to the exhaust ports 27, similar work cycles of volumetric, stepwise, reactive-pulse expansion of the gas-vapor mixture are performed.

Depending on the flow rate of the working fluid, the dimensions and power of the turbo engine, the number of inlet windows 10 can be made different. The number of bypass channels of the rotor and the blocks is equal, and may not correspond to the number of inlet windows, while their circumferential size and circumferential distance between them should ensure the performance of one or more complete duty cycles before re-communication with the inlet windows 10.

Centrifugal forces also contribute to the efficiency of bypassing the worker along the steps of the flowing parts and the strength of the reactive pulses.

When starting a cold turbo engine, its output to the operating mode of the gas cycle with the appearance of torque from the beginning of the air intake, the passage of gases through the central and turbine flow parts to the exhaust windows (exhaust) is no more than 2 rotor revolutions. After warming up and entering the water gases, the turbo engine enters the gas-steam mode of operation with the maximum efficiency of the duty cycle.

The total number of turbine engine working pulses per revolution of the rotor will be equal to the product of the number of bypass channels in the rotor by the number of bypass channels of the blocks and the number of stages "rotor-block" and "block-rotor".

So, in the turbo engine version shown in figures 1, 2, 3, comprising: 2 blocks with 8 bypass channels in each, a rotor with 8 bypass channels on each side, with three stages of repulsion of the rotor and with three stages of pushing the rotor in two blocks, the total number (n) of working pulses per revolution of the rotor will be:

n = 2 × 8 × 8 × 6 = 768 pulses

The power of the turboelectric generator, depending on the types of energy it produces, can be adjusted by changing the fuel consumption, or the consumption of water, or fuel and water, while simultaneously providing, depending on the calorific value of the fuel, generation for the turbine part of the gas-vapor mixture with minimum humidity in order to achieve maximum mechanical and, accordingly, electric capacities, or with maximum overmoistening of the gas-vapor mixture with water for maximum generation of thermal energy in the form of mountains barley condensate.

The purely hybrid design of the turbo engine and the continuous, hybrid, gas-steam thermodynamic cycle of full volume expansion realized by it provides several synergistic effects:

1. Reducing the number of parts; one rotor, bearings and two blocks are simultaneously used for 3 engines: an internal combustion engine, for a turbine and for two electric generators.

2. A sharp improvement in overall mass characteristics compared to combined power plants, consisting of a combination of separate types of engines - a heat engine and an electric generator or two turbines - a gas and steam and a separate steam generator in cogeneration combined-cycle plants that implement two separate and different cycles - gas and steam.

The adiabatic (without heat removal) gas-steam cycle with the maximum possible temperature range of the working fluid from T = 3000 ° C after ignition of the air-fuel mixture and to T = 50-70 ° C of the gas-steam mixture at the exhaust, realized by the turbo engine, will provide the maximum thermal efficiency for heat engines - up to 98%.

The generation of additional steam pressure in a hybrid gas-vapor cycle due to the unused heat of gases in known types of internal combustion engines and the most rational volumetric radial expansion of the working fluid with an increase in the radius and area perceiving the working fluid pressure, and the full use of pressure to atmospheric, will provide the highest possible effective efficiency up to 90%, taking into account the fact that mechanical losses and the negative moment associated with them for 3 engines (ICE, turbine, electric generators) will have s occurs only in part of the propulsion turbine engine at small radii - rotor bearings, joints blades with inserts and support cylindrical surface of the cylinder, the two joint end rotor seal with blocks in rolling bearings or slide, on which is mounted turbo rotor.

In a gas-steam adiabatic turbo-engine, a deeper use of the heat of the combustion products to generate additional pressure and an increase in the cycle efficiency when using additionally, in addition to water, low-boiling liquids with a lower boiling point than water, such as ammonia, is possible.

The coincidence of the torque characteristics of the gas-steam turbo engine and the electric generator synchronously working with it will provide high torque from the minimum speed of the turbo-electric generator, which, when used in vehicles as a power plant, will eliminate the need to use a separate electric generator and heavy expensive batteries.

In comparison with the known piston and rotary internal combustion engines, a gas-steam turbo engine will develop equivalent power at a significantly lower number of revolutions, which will reduce specific mechanical losses and increase its service life.

In combination with a multi-fuel steam generator and steam supply to the turbine part of the turboelectric generator, it will provide the generation of mechanical, electrical and thermal energy using various solid organic fuels (firewood, coal, pellets), which increases the versatility of its use.

The maximum possible use of heat in the work cycle for pressure generation, the most effective volume expansion and the rational kinematic scheme for converting it into torque will provide the minimum specific fuel consumption and, accordingly, high rates of gas and heat emission, exceeding the Euro standards for modern heat engines.

Claims (6)

1. An adiabatic gas-steam turbo engine containing two mirror-identical blocks of annular cylinders, one of which is made eccentric, and the rest are concentric, the rotor concentrically installed between them, bypass channels communicating the eccentric cylinder with concentric cylinders, and inlet and outlet windows, characterized in that the concentric cylinders of the blocks and the rotor are formed by alternating fixed annular protrusions, in each of which at least one bypass channel with plane parallel walls, while the walls of the bypass channels of the blocks and the rotor are located at an angle to the diametrical-axial plane of the turbo-engine, providing, when they communicate, the location of their walls relative to each other at an angle of about 90 °, in addition, an annular receiver cavity is made after the eccentric cylinder of the blocks, the cylindrical walls of which are made bypass channels communicating with the eccentric cylinder and the turbine flow part of the turbo engine, and in the annular walls of the blocks separating the eccentric cylinders Cores and receivers, recuperator cavities are made, the input of which communicates with the source of the evaporating liquid, and the outputs communicate with the cavity of at least one bypass channel communicating an eccentric cylinder with an annular receiver cavity, in addition, in the cylindrical walls of the receiver cavity at the joints with the rotor end ring seals are installed in the form of spring-loaded rings or pneumodynamic impeller seals made in the form of spiral grooves coinciding with the direction of rotation of the rotor. 2. The adiabatic gas-steam turbo engine according to claim 1, characterized in that at least one or several flat thin-walled vanes uniformly spaced along their cross section and parallel to their walls are made in the bypass channels of the rotor and blocks, while the radial walls of the outlet windows the blocks are made flat and thin-walled and located at an angle of about 90 ° to the blades of the last stage of the rotor, and between them at least one or more flat thin-walled blades are also made. 3. The adiabatic gas-steam turbo engine according to any one of claims 1 and 2, characterized in that the rotor is made of two parts, while the part of the rotor containing the annular protrusions with the blades installed in them, and the part of the rotor containing the annular protrusions with the bypass channels interact with each other by means of a lockable overrunning clutch, while in the end walls of the blocks channels are made for supplying the working fluid to the annular receiver cavities and gate valves are installed that overlap the bypass channels between the eccentric cavities blocks and concentric annular cavities of the receivers. 4. The adiabatic gas-steam turbo engine according to any one of claims 1 to 3, characterized in that the last row of rotor annular protrusions from the center is made in the form of permanent magnets, while inductance windings are made axially to the rotor magnets in the end walls of the blocks. 5. The adiabatic gas-steam turbo engine according to any one of claims 1 to 3, characterized in that the row of annular protrusions of the rotor, the last from the center, is made in the form of permanent magnets, while on the cylindrical walls of the blocks between the outlet windows coaxially to the rotor magnets are made of inductance. 6. The turbo engine according to claim 4 or 5, characterized in that at least one of the generators is made in the form of a single reversible electric machine with the function of a starter.

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