The propulsion system and rotary engine |
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IPC classes for russian patent The propulsion system and rotary engine (RU 2171906):
     
 Turbomolecular installation with bleed air from the turbofan engine / 2168122
The invention relates to refrigeration, and in particular to air turbopropeller installations
 Device for increasing the efficiency of a heat engine / 2161717
The invention relates to the field of engine development, namely the heat-engines /piston internal combustion engines, as well as to the gas turbine and a pulsed jet-propulsion engines, with a wide range of capacities and the ability to work on all known types of hydrocarbons
 Turbojet engine / 2153593
The invention relates to a turbojet engine with afterburner chamber and rotary jet nozzle system control and regulation of the rotary nozzle, mounted on highly maneuverable multifunctional fighters
 Turbojet disk engine / 2153592
 Turbojet engine / 2151900
The invention relates to a turbojet engines for aircraft gas turbine, operate the compressor that uses compressed air to oxidize the fuel
 Afterburning fuel / 2150597
 The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle (options) / 2143578
The invention relates to a turbojet engine with an additional supply of heat in the afterburner and rotary jet nozzle
 Turbojet engine / 2141051
The invention relates to the field of engine development, in particular to the construction of turbojet engines
 Turbojet engine / 2135805
 Gas turbine engine / 2161714
 Turbocharger / 2147691
 Gas turbine installation / 2146012
The invention relates to gas turbine units, designed for heat recovery from heat source
 A rotary vane internal combustion engines / 2121065
The invention relates to energy, transport, mechanical engineering and can be used as a transport and stationary internal combustion engines
 The method of operation of a heat engine and a heat engine / 2107176
The invention relates to the field of rehabilitation of the environment (ecology), specifically to the field of heat engines operating by the heat of industrial gases, gas heating systems
 Turbocharger kondakova / 2094633
The invention relates to energy, namely, gas turbines, and can be used to improve the efficiency of internal combustion engines by their charge, as well as in gas turbine engines and other power machines
 The method of converting thermal energy into mechanical work into heat machine and heat engine / 2084645
 Gas turbine engine / 2074968
 The rotary vane engine / 2171896
The invention relates to mechanical engineering, in particular to rotary vane machines, including internal combustion engines
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(57) Abstract: The invention relates to energy, in particular to aircraft power plants. The propulsion system includes a turbine and a low-pressure compressor, two propeller with shaft mounted coaxially. The installation includes two motor shafts mounted coaxially. The installation includes two engines with coaxial rotors installed with the possibility of the opposite direction of rotation. The shafts of the propellers are connected with the rotors of the motors in them are made of the axial bore. One of the shafts of the propellers is located in the hole of the other shaft. Inside both shafts mounted shaft connection of the compressor and the low-pressure turbine. The motor unit can be used a rotary motor, the stator of which has a leading rotor and driven rotor, with inlet and outlet ports purge depressions made in the bores of the stator under driven rotors. The objective of the invention is to increase the efficiency of the rotary engine, and therefore the propulsion system. 2 C. and 16 h.p. f-crystals, 7 Il. The invention relates to energy, in particular to aircraft power plant, and can be used in motor complexes in water trench screws (Skubachevskii, S. Aircraft gas turbine engines. M : mechanical engineering, 1981, S. 15, Fig. 1,1) containing two parallel gas turbine engines. The disadvantages of this scheme are a large area of the midsection and a significant drag reducing flight efficiency, as well as a large mass, complexity and low reliability designs with step-down gear. Known structural diagram of a turbofan installations Skubachevskii, S. Aviation gas turbine engines. M: mechanical engineering, 1981, S. 8, 10, Fig. 1.03 b, 1.06), adopted as a prototype for the first invention and containing the turbine and the low-pressure compressor and the mover, such as a fan, with the shaft. This design has no gearbox, but mover efficiency is relatively low due to the small degree of bypass ratio and significant losses in the stationary guide vanes of the fan. From the patent literature known rotary internal combustion engine (GB patent 1057282 A, class F 01 1/20, publ. 01.02.1967,), adopted as a prototype for the second invention and containing the stator housing and two end caps, trailing internal working cavity in the form of three n is tion protrusions (teeth), and in two extreme has two driven rotor with three cavities, each associated with contactless minimum clearances with the tabs of the male rotor. In the Central cavity are camera compression and expansion, and in the Cabinet wall it made box with connections for inlet air charge and extended release products of combustion. In case the side walls of the cavities with slave rotors have outlet ports connected a by-pass channel with the camera an extension of the inlet window and rinsing troughs driven rotors compress air and nozzles for fuel injection. The engine operates on the two stroke cycle, purely rotational movement of the rotors provides a unique speed and minimum specific weight. The disadvantages should be relatively small chamber working volume expansion equal to half of the volume of the chamber in the Central cavity, because the second half is occupied by the compression chamber; the operation of the bypass channel at high speed rotors inefficient due to the inertia of the gas in the channel, throttling and percussion expansion of the combustion products with the energy loss, it is necessary to make additional work on their subsequent is here reduce fuel consumption, square midsection, specific gravity, increasing engine efficiency. The technical result is achieved by the fact that the propulsion system includes a turbine and a low-pressure compressor and the propeller, for example, a fan shaft, a second propeller shaft mounted coaxially to the first mover and two engines with coaxial rotors installed with the possibility of the opposite direction of rotation, the shafts of the propellers are connected with the rotors of the motors and in them is fulfilled the axial bore, and one of the shafts is located with a clearance in the axial hole on the other of the shaft and one of the rotors and the inside of both shafts and rotors installed the shaft connection of the compressor and the low-pressure turbine. Each motor includes driving and driven rotors cycloidal gearing, the difference in number of teeth is equal to one. The shaft of one of the movers unloaded on the thrust bearing installed between the engines. The shafts of the propellers connected to the rotors with the possibility of axial displacement. The shafts of the propellers connected to the rotor through a gearbox. Installation performed from the rear thrusters. The second in the direction of installation of the driver is connected to the nozzle, the last stage turbine unloaded on the thrust bearing, mounted in the frame fixedly connected with the guide vanes of the turbine and nacelle. A rectifying apparatus of the compressor is connected with the rotor of the motor. Installation performed from a front location of the thrusters. The compressor and the air intake is installed on the ground in the direction of installation of the propeller. The task of the second invention is to increase power density and efficiency, simplifying the design. The technical result is achieved in that the outlet port purge depressions are directly connected to the outlet channel, the inlet window of the compression chamber is made in the bores of driven rotors, optimal number of teeth of the male rotor and the driven rotor. In Fig. 1 shows the propulsion system in the axial section. In Fig. 2 - section a-a of the propulsion system. In Fig. 3 - rotor engine in the axial section. In Fig. 4, 5 - cross-section E-E. In Fig. 6, 7 - ways trehyadernogo engine. The propulsion system includes a gondola 1, in which the fixed housing two rotary motors 2 and 3. In the cases of the bearings 4, 5, 6, 7 installed leading the rotors 8 and 9, each of to whom odawise in engagement with the driven rotor 10, 11, 12, the number of teeth with one tooth more (for example, 5, 7, 9), and the teeth of the defined envelope of hypocycloid or near the curve. Driven rotors unloaded in the housing by means of bearings with gas lubrication; in the hollows of the teeth of the driven rotor is bypass window 13, which are near Century MT injection channels 14 and filling the channels 15 communicated with the combustion chambers 16 in which is installed the fuel injector 17. The axial length of the rotor 11 is two times the length of the rotors 10, 12 and they are displaced diametrically oppositely from the axis of the male rotor. In the end covers 18 and the disks 19 of the housing in the area N. M.T., corresponding to the maximum volume of the chambers made the inlet 20 and outlet 21 of the inlet ports 22 connected respectively with the inner cavity of the gondola, which is communicated with the output of the low-pressure compressor 23 and the exhaust manifold 24, the output of which is connected with the working path of the gas turbine 25. Working camera with motors and seals with gas lubrication 26, 27, the design of which is known (SU, ed. mon. 958755 A, class F 16 J 15/44, publ. 15.09.1982). In addition, the motors are equipped with an active management system clearances between the rotors and the housing, which is similar to (SU, ed. mon. One obliteration gaps directly when the engine is running (EN, patent 2013582, CL F 02 In 53/00, publ. 30.05.1994). Inside the leading rotor is cavities, channels and heat exchange fins of the cooling system, and an axial hole in which, by means of spline connection (for example, with intermediate balls) with the possibility of axial displacement of the installed shaft 28 of the fan or screw 29 and the shaft 30 of the fan 31. The shaft 28 through the angular contact bearing 32 mounted in the frame 33, bonded through a fixed guide vanes 34 with the body. With the frame are fastened together also a guiding apparatus 35. On the shaft 28 fixed turbine 25, the fan 29 is connected turbine 36, with the fan 31 is fastened the last stage of the turbine 37, the nozzle 38 and the rear fairing (COCs) 39. The shaft 30 is passed through the axial hole of the rotor 9 and discharged through the radial-thrust bearing 40 located between the engines in case. In the axial hole of the shaft 30 posted shaft connection 41 between the turbine 42 and the rotor 23 of the low-pressure compressor. Crowns 43 directing vanes of the low-pressure compressor is installed or in the housing or drum 44, through which the blades 45 and the disk 46 is rigidly connected to the leading rotor 8. The compressor rotor is mounted on bearings 47, 48. The disks ventilyatsionnie blade of gas turbine engines instead of the rotor, while the shafts of the propellers, it is advisable to connect the shafts of the motors through reduction gear. It is also possible the performance of the installation with a front location of the fans, in this embodiment, the compressor and the inlet 51 may be installed on the front fan. When the rotation of the rotors 8, volume 11 magzumovich cameras varies from a minimum in a Century MT to a maximum of N.M.T. Approximately 30oto N. M.T. open outlet port 21, then the inlet box 20 and compressed in the compressor 23 air flow blowing out of the working chambers of a rotary engine, the combustion products through a manifold 24 are received in the gas turbine 25, 36, 49, 50, 42, 37. In the phase of ~270oafter a Century MT blowing pumped, the air is compressed to a pressure of ~ 2 MPa, through the window 13 and the discharge channel 14 with a twist is displaced into the combustion chamber 16 is mixed with fuel supplied by the injector 17, the mixture is ignited and burns with a high pressure of up to about 7 MPa, then the expansion of the combustion products and blowdown. Diametrically opposite the offset of the slave rotor 11 relative to the rotors 10, 12 provides trim radical forces of gas pressure on the driving shaft 8 and unloading their bearings. Power is recorded; torque on the fan increases additionally turbines 25, 36, 49, 50, 37. The free energy of the turbine 42 through the shaft 41 of the drive unit 23. Technical and economic efficiency of the proposal, it is useful to illustrate this with the following example:Main technical data of the propulsion system with 5-section rotary engines (approximate): Length, mm - 3800 The area of the midsection ( 740 mm), m2- 0,43 Weight, kg - 1100 Fan diameter, mm - 2400 The pass ratio - 56 Power - 8000 KW Specific mass, kg/KW was 0.138 The temperature in the combustion chamber - 2800 TO The degree of pressure increase (at an altitude of 10 km) - 200 UD.fuel consumption: 0.15 kg/kWh UD.pull - 0,134 kg/kgf The rotational speed of a shaft - 3000 rpm The air excess factor - 1 High technical indicators have a natural explanation: the high temperature of the gases in the combustion chamber in excess of about 1000 To level temperatures in modern gas turbines, a high degree of pressure increase, the possibility of exclusion from the design of the reduction gearing, etc. Careful optimization of the design and use of modern materials (ug is the R advantages. Installation retains the advantages of using a traditional gas turbine engines due coaxially their location (decrease midsection) and high efficiency axial fans or propellers. Rotary motor includes a stator 51 stop it working cavity formed by the Central cylindrical bore leading rotor 52 and four intersecting with the Central hole bores for the slave rotor 53; to which is bonded end caps 54, 55, in which the bearings 56, 57 are installed leading to the rotor shaft 58 and driven rotors 53, evenly spaced around the male rotor in the bores of the housing. Leading the rotor is provided with a ledge-teeth 59 cycloidal profile associated with depressions 60 on the driven rotors. In the Central cylindrical hole has outlet ports 61 pipes 62, the bores for the driven rotor is the inlet window 63 for purging the compression chambers 64, which are formed by the volumes of the cavities 60 and fragments of 65 in the Central cavity located between the Windows 61 and driven rotors. In addition, the bores of the stator under the slave rotor holds the outlet 66 and the inlet 67 of the window and rinsing troughs from combustion products. Inlet box 6 is placed in a single window with a common pipe; perhaps their separate execution and the connection of each with his pipe, for example, to purge cameras compress air to a higher pressure than when the blowing cavities from combustion products through the pipe 69 connected to the exhaust tract. It is advisable to execution of the branch pipes with the resonant length, which increases the efficiency of purging basins and recharge cameras compression by dynamic boost. The rotors are synchronized by gears communications 70, 71 installed in the housing of the ignition device 72, which may be a spark plug or fuel injector. Housing and rotors are made of heat-resistant materials with a low coefficient of thermal expansion (CTE), for example, structural ceramic, glass-ceramic, sapphire, plekon and other and connected with each other with minimum clearances of the order of 0.02-0.1 mm working surface can have a relatively "soft" abrasion coating, for example, on the basis of graphite; the tops of the teeth of the male rotor and the edges of the depressions of the driven rotors are covered with material of high hardness and wear resistance. In addition, by sealing the edges of the depressions on the tops of the teeth on the rear (downstream) surface of the teeth of the male rotor and polozhennyh along. The optimum number of teeth of the male rotor and the number of driven rotors is taken from two to five, and the number of teeth and the driven rotors can be equal, as in Fig. 4; (bearings 56 of the male rotor is almost completely discharged from the forces of gas pressure), or the number of teeth and the driven rotors are executed by the difference in the unit (for example, four of the slave rotor and five teeth; the positive effect of the uniformity of the torque on the output shaft 58). In the bores of the stator under driven rotors can be filled with additional channels 73 to increase the degree of expansion of the gas from the depressions 60, but this positive effect should be compared with negative short-term (almost instantaneous) leakage at the time of passage of the tooth tip of the rotor through the channel. Very simple design is shown in Fig. 6, 7, it contains a bidentate leading rotor 84 and two slave rotor 75 with three depressions 76 each, the inlet 77 and the discharge nozzles 78 to purge cavities with compressed air or bessovestnoi mixture, exhaust pipes 79, located in the front along the male rotor side of the camera housing extension 80, the vehicle ignition 81 (injector or spark plug). When COI is I through holes. Possible option of nozzles 82 and Windows 83 for purging the compression chambers 76, made separately from the nozzles 77 (see Fig. 7). When the engine through pipes 68, 69 compressed air from a blower or turbocharger is blowing depressions 60 of driven rotors, then the fuel injection through the nozzle 72 by a large margin, the corresponding speed of the engine, blowing the compression chamber through the window 63 with the release of combustion products through the nozzle 62, the compression to a minimum volume (C. M. I., see Fig. 4) where the end of the period of preparation of the mixture and ignition delay, then the ignition, combustion, expansion in the depressions 60, about twice the continued expansion in the chambers 74 and exhaust through the pipe 69 into the exhaust manifold and the turbine unit charge. The performance of the engine with the two tabs of the male rotor and the two driven rotors with three cavities each connection in the process of expanding the volume of the basin with camera extension before the release of gases into the exhaust pipe 79 (see Fig. 6), thus the need for the bypass channel available in the well-known analogue eliminated eliminated accompanying disadvantages. The same positive amatore, paired with four slave rotors with two cavities each. Non-contact seals provide a high circumferential speed of the rotor (of the order of 50-100 m/s), the adiabatic mode with the lowest dosed cooling the most heated seats corps and uncooled rotor; eliminates lubrication of rotors and waste oil, while losses from gas leaks less mechanical friction losses in reciprocating engines. The combined effect of these factors enables the creation of extremely light engine with a specific gravity of ~0.03 kg/kW, simple, reliable, environmentally friendly, long service life and high efficiency. 1. Motor installation comprising a turbine and a low-pressure compressor and the mover, such as a fan, shaft, characterized in that it further provided with a second driven shaft mounted coaxially with the first mover and two engines with coaxial rotors installed with the possibility of the opposite direction of rotation, the shafts of the propellers are connected with the rotors of the motors and in them is fulfilled the axial bore, and one of the shafts is located with a clearance in the axial hole on the other of the shaft and one of the rotors and the inside of both shafts under item 1, wherein each motor includes driving and driven rotors cycloidal gearing, the difference in number of teeth is equal to one. 3. Installation under item 2, characterized in that the shaft of one of the movers unloaded on the thrust bearing installed between the engines. 4. Installation under item 2, characterized in that the shafts of the propellers connected to the rotors with the possibility of axial displacement. 5. Installation under item 2, characterized in that the shafts of the propellers connected to the rotor through a gearbox. 6. Installation under item 2, characterized in that it is made with the rear thrusters. 7. Installation according to p. 6, characterized in that the second in the direction of installation of the driver is connected to the nozzle, the last stage of the turbine and the rear fairing. 8. Installation according to p. 6, characterized in that the first disk in the direction of installation of the propulsion is supplied by the turbine rims, and its shaft is unloaded on the thrust bearing, mounted in a frame fixedly connected with the guide vanes of the turbine and nacelle. 9. Installation under item 1, characterized in that the straightening apparatus of the compressor is connected with the rotor of the motor. 10. Ustanovke.10, characterized in that the compressor and the air intake is installed on the ground in the direction of installation of the propeller. 12. Rotary engine, containing the stator with the working cavity formed by intersecting cylindrical surfaces (bores), which has a leading cycloidal rotor with ledges and driven rotors with depression, inlet and outlet ports for venting the compression chamber and the expansion, inlet and outlet ports for blowing depressions, characterized in that the outlet port for blowing cavities are connected with the exhaust tract of the engine, the inlet window of the compression chamber is made in the bores of the stator under driven rotors or combined with Windows inlet purge cavities. 13. The engine under item 12, characterized in that it contains from two to five slave rotors, located on a circle around the male rotor. 14. The engine under item 13, wherein the number of protrusions of the male rotor is equal to the number of driven rotors. 15. The engine under item 13, wherein the number of teeth of the male rotor one tooth more or less than the number of driven rotors. 16. The engine on p. 13, characterized in that the leading rotor has two tabs and paired with two of roysta and paired with three rotors, having three cavities. 18. The engine on p. 13, characterized in that the leading rotor has four lobes and is associated with four rotors having two cavities.
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