RU2359140C2 - Yugi's turbo-rotor engine - Google Patents

Abstract

FIELD: engines and pumps. ^ SUBSTANCE: invention relates to rotor engines and compressors, and to aircraft gas turbine engines. The proposed turbo-rotor engine incorporates a compressor and engine, intake and exhaust openings, the 1st, 2nd and 3rd stage turbines. Both compressor and engine is made up of two rotors, one of them being an inner rotor with vanes directed outward, the other one, an outer rotor, features the vanes directed inside. The compressor and engine inner and outer rotors are interconnected. Each engine rotor has two roller couplings, one them provided with a fixed outer collar while the other furnished with outer coupling linked up with the rotor engine output shaft. The outer rotor vanes are furnished with differential valves, while the inner rotor vanes have ball-type slide valves. The axial chamber houses the combustion chamber with a nozzle. The fuel supply pipe with channels to feed fuel and oxidiser to two-component nozzle (with return valve) is arranged inside the turbo compressor shaft with openings linked up, via intensifier, with the rotor engine output shaft. The 1st stage turbine runs in bearings of the inner rotor shaft, right behind the exhaust openings. The 3rd stage turbine disk and shaft run in bearings of the turbo compressor shaft and those of fixed support. The disk coupling the 1st and 3rd stage turbines vanes accommodates the fan vanes in annular channel. ^ EFFECT: increased specific performances. ^ 4 cl, 7 dwg

Description

The invention relates to engine building, in particular to rotary engines and rotary compressors and pumps with variable rotor speed, as well as to aircraft gas turbine engines. The technical result is to increase the specific performance of the engine.

The invention consists in the following.

The fuel supply pipe to the two-component nozzle is located inside the turbocharger shaft with windows connected via a multiplier to the output shaft of the rotary engine, behind the exhaust windows of which the first stage turbine is mounted on the bearings of the internal rotor shaft with blades connected to the external disk to which the third stage turbine blades are connected , the disk and the shaft of which are supported by the bearings of the turbocompressor shaft and the fixed support, and on the external disk are the fan blades in the channel of the ring.

The turbo-rotor engine is designed to drive various machines using liquid or gaseous or two-component fuel.

The analogues of the invention are: patent of N.P. Seima No. 14226, filed on January 5, 1929, and.with. No. 183722, No. 210593, patents No. 2195402, No. 2246040, No. 2253734, as well as the Rostatic turbine described in the book "Design of aircraft gas turbine engines", ed. Doctor of Technical Sciences A.M. Akhmetzyanova, Ufa, 2000

The prototype of the invention is a gas rotary engine according to patent No. 2219357.

The gas-rotor engine contains a housing, a compressor and an engine with inlet and outlet windows, each of which is made of two rotors, one of which is internal, with blades facing outward, the second rotor is external, with covers and blades directed inward, internal compressor rotors and the motor are interconnected, the outer rotors are interconnected, each rotor having a roller clutch with a fixed outer cage and a roller clutch with an outer cage connected to the motor output shaft, a compressor and the engine is equipped with differential valves and ball valves, in the axial cavity there is a flame tube of the combustion chamber with a nozzle.

The disadvantage of the prototype (and the analogue according to patent No. 2253734) is the low efficiency of the use of exhaust gases of a rotary engine.

The objective of the invention is to remedy this drawback.

This task is achieved by the fact that

1. A turbo-rotor engine containing a compressor and an engine with intake and exhaust windows, each made of two rotors, one of which is internal, with blades facing outward, the second rotor is external, with blades directed inward, and the internal rotors of the compressor and of the motor are interconnected, external rotors are interconnected, each motor rotor has two roller clutches, one of them with a fixed outer cage, the second with an outer cage connected to the output shaft of the rotary motor , in the blades of the external rotors there are differential valves, and in the blades of the internal rotors there are ball spools, in the axial cavity there is a combustion chamber with a nozzle, characterized in that it contains turbines of the first, second and third stages, a fuel supply pipe with channels for supplying fuel and oxidizer to a two-component nozzle (with a check valve) is located inside the shaft of the turbocompressor with windows, connected through the multiplier to the output shaft of the rotary engine, behind the exhaust windows of which is located on the bearings kakh of the shaft of the inner rotor of the turbine of the first stage with blades connected to the outer disk, to which the blades of the turbine of the third stage are connected, the disk and shaft of which are supported by the bearings of the turbocompressor shaft and bearings in a fixed support, and on the disk connecting the turbine blades of the first and third stages, fan blades are located in the annular channel.

2. The turbo-rotor engine according to claim 1, characterized in that the labyrinth on the cone of the flame tube divides the combustion chamber into the air supply zone from the compressor and the gas exhaust zone into the rotary engine and relies on the inner rotors with the consoles of the inner shell.

3. Turbo-rotor engine according to any one of claims 1 and 2, characterized in that in the cylinder of the outer rotor there are channels for supplying and discharging cooling air into the wall between the rotors of the compressor and the engine, where there is a wall with blades on both sides of different twists, and the wall with engine side is made on the principle of a heat pipe.

4. Turbo-rotor engine according to any one of claims 1 and 2, characterized in that in the shafts of the outer and inner rotors there are rotor oil pump blades and intake and exhaust valves for supplying lubricant to the sealing elements of the blades of the outer and inner compressor rotors.

Figure 1 shows a longitudinal section of the engine. Figure 2 shows a section aa of figure 1. Figure 3 shows a section bb In figure 1. Figure 4 shows the place E from figure 1. Figure 5 shows the place H with figure 1. Figure 6 shows a section CC of figure 5. Fig.7 shows a section DD from Fig.5.

The turbo-rotor engine contains elements of a gas-rotor engine: a housing, a compressor made of two rotors, one of which is internal (Fig. 1, 2), with outward-facing vanes, in which ball spools 1 with check valves are located, and the second rotor is external, with the cylinder 2 and the blades directed inward, in which the differential valves 3 are located with the inlet windows 4. Between the rotor blades are working cavities 5 and 6 (figure 2). The engine is also made of two rotors, one of which is internal (Figs. 1, 3), with outward-facing vanes in which ball spools 7 are located, the second rotor is external, with cylinder 2 in common with the compressor, with vanes directed inward, in which differential valves 8 with exhaust windows 9 are located. Between the rotor blades there are working cavities 10 and 11 (Fig. 3). The internal rotors of the compressor and the engine are interconnected, interconnected and the outer rotors of the common cylinder 2 and the covers. Each rotor has two roller couplings, of which one pair of couplings 12 and 13 (Fig. 1) has a fixed outer cage, the second pair of couplings 14 and 15 has an outer cage made on the output shaft 16 of the rotary engine. In the axial cavity there is a flame tube 17 of the combustion chamber with a nozzle. The new elements in the turbo-rotor engine are a two-component centrifugal nozzle with a check valve 18 (Fig. 1, 5) in the oxidizer supply channel, an input device, a turbocompressor with a diagonal stage of the compressor 19 (analog of the known engine) (Fig. 1), a shaft 20 and a turbine 21 . From the unit box (not shown, located in front of the input device) through the shaft 20 of the turbocharger passes a pipe 22 to a two-component centrifugal nozzle with a check valve 18 located inside the shaft 20 with the windows 23. The shaft 20 has a gear 24 engaged w with satellites 25, which are engaged with the stationary gear 26 and form a multiplier with the axes 27 of the satellites mounted on the output shaft 16 of the rotary engine. Behind the exhaust windows 9 there is a first stage turbine mounted on bearings 28 of the internal rotor of the engine with bandaged blades 29. The bandages of the blades are connected to the outer disk 30, to which the bandages of the blades 31 of the third stage turbine are connected, the disk of which and the shaft are supported by the bearings 32 of the turbocharger shaft 20 ( with hydrodynamic lubrication) and bearings 33 in a fixed support with bearings 35 of the turbocharger shaft. On the outer disk 30 connecting the turbine blades of the first and third stages, there are fan blades 36 located in the channel of the ring 37.

The flame tube 17 of the combustion chamber with a labyrinth 38 on the conical part 39 divides the air supply zone from the compressor from the gas supply zone to the ball valves 7, differential valves 8 of the engine. The heat pipe 17 with the cantilever parts 40 and 41 of the inner shell 42 is installed between the shaft 20 of the turbocharger and the shafts of the internal rotors of the compressor and engine on which it rests.

In the cylinder 2 of the outer rotor there are channels for supplying 43 and cooling air 44 to the wall 45 (Fig. 4) between the compressor and engine rotors, where there is also a wall 46 with blades 47 and 48 on opposite sides of the wall 46, and the wall on the engine side is made according to the principle of a heat pipe with a wall 49. On the outer cylinder 2 there is a visor 50 with small blades (not indicated).

On the shaft of the inner rotor there is a ring 51 (FIGS. 5-7) with grooved grooves and blades 52 with sealing elements 53. The grooves of the grooves include balls 54 with clamps 55 located in the shaft of the inner rotor and secured by the turbocharger shaft 20. In the shaft of the outer rotor there are blades 56 (Fig. 6, 7), a cover 57 (Fig. 5) and inlet 58 and outlet 59 valves with channels extending into the cavities 60 and 61 of the pump (Fig. 6, 7), channel 62 ( 5), going from the pump to the sealing elements of the blades of the inner and outer compressor rotors.

The turbo-rotor engine operates as follows. When two-component fuel is supplied through the pipe 22 to the nozzle with the valve 18, the fuel jets pass through the shaft windows 23 into the flame tube 17 of the combustion chamber and ignite. The pressure in the combustion chamber rises and acts on the ball spools 7 of the engine (Fig.1, 3).

The balls are displaced, for example, counterclockwise, and the gas pressure enters the cavity 10 (Fig. 3) between the engine blades, the gas pressure in these cavities tends to rotate the rotors in different directions. But the roller clutch 12 and 13, interacting with the stationary outer cages are installed in such a way that both rotors can rotate only in one direction (for example, clockwise). The gas pressure will close the differential valves 8 in the cavities 10 and the outer rotor with the cylinder 2 with blades will begin to turn clockwise, compressing the air and closing the differential valves in the cavities 5 of the compressor (figure 2), and in the cavities 11 of the engine the air will exit through the exhaust windows 9. When the rotor blades approach each other, the differential valves 3 and 8 will close in the cavities 5 and 11 under the action of pressure increasing in these cavities and from the contact of the spool balls 7 with the valve head 8, and open in the cavities 6 and 10. Ha h from the cavities 10 will exit through the exhaust windows 9. In the closed cavities 5 and 11, the pressure will increase and the balls of the spools 1 and 7 will shift clockwise. But in the cavities 5, air was compressed, which through a channel located along the axis of the blade and in the internal rotor, enters the cavity of the combustion chamber, into which fuel is supplied through centrifugal two-component nozzles with a valve 18. Ball spools 1 have check valves (differential), and in the cavities 6, when the outer rotor with the blades rotates clockwise, the vacuum will increase, and air through the windows 4 and valves 3 will enter these cavities. The clockwise displaced balls of the spools 7 will provide gas supply from the combustion chamber to the engine cavities 11, and the displaced balls of the spools 1 will provide air compression in the cavities 6 and supply it to the combustion chamber. Under the influence of gas pressure in the cavities 11 of the engine, the outer rotor will begin to slow down, and the inner rotor will turn clockwise. Next, the cycles are repeated, and the rotors will alternately rotate with acceleration or brake, transmitting torque through the roller clutch 14 or 15 to the output shaft 16 (Fig.1) of the rotary engine.

The axles 27 of the satellites mounted on the output shaft 16 will cause the satellites to run around the stationary gear 26 and rotate the gear 24 on the turbocharger shaft 20, increasing its speed to the operating frequencies of the turbocharger.

The air pressure behind the compressor stage 19 will increase, respectively, the air pressure in the rotary compressor, the combustion chamber and in the rotary engine will increase, and the exhaust pressure will increase. The air behind the compressor 19 enters through the inlet ports 4 (FIG. 2) into the rotary compressor, which is also facilitated by a visor 50 with vanes (FIG. 4), a braking flow. Behind the visor 50, the air partially cools the cylinder 2 of the outer rotor and is heated by the exhaust gases leaving the windows 9 (Fig. 1) and enters through the nozzle apparatus (not indicated) to the blades 29 of the turbine of the first stage, then to the blades of the turbine 21 of the turbocompressor (second turbine stage), then on the blades 31 of the turbine of the third stage. The spinning of the turbine blades of the first and third stages is directed in one direction, and the spinning of the turbine blades of the second stage is in the opposite direction, respectively, and the turbines rotate in different directions, which does not require the installation of straightening devices and facilitates the engine (analogue is a Rostatic turbine).

Between the back of the casing and the outer rotary disk 30 there is a small gap (not indicated), which provides for the ejection of external air by gases leaving the nozzle apparatus. The turbo-rotor engine shown in FIG. 1 is intended primarily for aircraft, hovercraft or flying cars. Therefore, the power of the turbines of the first and third stages through the disk 30 is transmitted to the blades 36 of the fan located in the channel of the ring 37 (which increases the fan traction). For non-flying devices, the power of the turbines of the first and third stages can be transmitted, for example, to the generator from the shaft of the turbine of the third stage. The power of the rotary engine and turbine of the second stage is taken from the compressor shaft 19 through the unit box.

The degree of pressure increase in the diagonal stage of the compressor is about 2.2-2.5 in a rotary compressor with polytropic compression of about 10-12 or more, i.e. the total compression ratio will be 22-30 or more, the temperature will exceed 600 K. The double-acting engine and the thermal stress are very high. To reduce the heat supply from the rotary engine to the rotary compressor on the cylinder 2 there is a visor 50 (Fig. 4) with blades (not indicated) that direct the air to the circumferential air supply channels 43 to the blades 47, which act as a centripetal fan, then to the blades 48 acting as a centrifugal fan, and is ejected through the exhaust channels 44. In the cavity between the wall 49 and the end wall of the engine (not indicated) is a porous material and a working fluid of a heat pipe (such as sodium or lithium), which provides cooling and uniform temperature of the wall 45 when it is cooled by air circulating during rotation of the outer rotor with cylinder 2 with blades 47 and 48, and reduces heat supply to the rotary compressor.

The pressure in the compressor is high and an oil supply with a higher pressure is required to lubricate the sealing elements of the rotors of a double-acting compressor. Therefore, a rotary oil pump is introduced, built between the shafts of the inner and outer rotor. Oil is supplied from the nozzle to the inlet valve 58 (Fig. 5), and when the outer rotor rotates in the cavity 60 (Fig. 6), a vacuum is created where the oil enters. When the outer rotor stops and the inner rotor begins to turn, the inlet valve 58 closes and the oil from the cavity 60 through the exhaust valve 59 enters the channel 62 to the sealing elements of the outer rotor, passes into the lower part of the wall 45 (Fig. 4) and through the cylinder of the inner rotor to its sealing elements are then discharged into the bearing cavity. Sealing elements of the engine can be made, for example, of sintered foam-metal-graphite compound with the addition of molybdenum sulphide and can be lubricated and cooled by water vapor when using two-component fuel. As such fuel, the cheapest and most environmentally friendly and safe to use is alcohol and a hot solution of ammonium nitrate ("Technique of Youth" No. 11, 2002, art. "Universal Fuel"). The engine can operate on hydrocarbon fuel without the addition of an oxidizing agent, and the check valve 18 in the nozzle will prevent leakage of fuel into the oxidizer line.

The proposed engine has a higher effective pressure than existing engines, and almost full use of the energy of exhaust gases, the pressure of which will be greater than the working pressure in the known engine. In the engine there are no rectifying devices for turbines of the second and third stages, which reduces the mass of the engine.

At the Ufa Engine-Building Production Association (UMPO), a prototype of an air motor was manufactured and tested (later patent No. 2246040, an analogue of the proposed engine, was issued).

Despite some design flaws and manufacturing defects in the manufacture, the engine confirmed its efficiency.

Claims (4)

1. A turbo-rotor engine comprising a compressor and an engine with intake and exhaust windows, each made of two rotors, one of which is internal, with blades directed outward, the second rotor is external, with blades directed inward, and the internal rotors of the compressor and engine interconnected, interconnected and external rotors, each rotor of the engine has two roller couplings, one of them with a fixed outer cage, the second with an outer cage connected to the output shaft of the rotary engine , in the blades of the external rotors there are differential valves, and in the blades of the internal rotors there are ball spools, in the axial cavity there is a combustion chamber with a nozzle, characterized in that it contains turbines of the first, second and third stages, a fuel supply pipe with channels for supplying fuel and oxidizer to a two-component nozzle (with a check valve) is located inside the shaft of the turbocompressor with windows, connected through the multiplier to the output shaft of the rotary engine, behind the exhaust windows of which is located on the bearings the axle of the shaft of the internal rotor is a turbine of the first stage with blades connected to the external disk, to which the blades of the turbine of the third stage are connected, the disk and shaft of which are supported by the bearings of the turbocompressor shaft and bearings in a fixed support, and on the disk connecting the turbine blades of the first and third stages, fan blades are located in the annular channel. 2. The turbo-rotor engine according to claim 1, characterized in that the labyrinth on the cone of the flame tube divides the combustion chamber into a zone for supplying air from the compressor and a zone for exhausting gas into the rotary engine and leans on the inner rotors with the consoles of the inner shell. 3. Turbo-rotor engine according to any one of claims 1 and 2, characterized in that in the cylinder of the outer rotor there are channels for supplying and discharging cooling air into the wall between the rotors of the compressor and the engine, where there is a wall with blades on both sides of different twists, and the wall with engine side is made on the principle of a heat pipe. 4. Turbo-rotor engine according to any one of claims 1 and 2, characterized in that in the shafts of the outer and inner rotors there are rotor oil pump blades and intake and exhaust valves for supplying lubricant to the sealing elements of the blades of the outer and inner compressor rotors.

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