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INVENTION
Russian Federation Patent RU2171906
Propulsion and rotary engines
Name of applicant: S. Vladimirov Porphyry
Name of the inventor: Porphyry Vladimirov S.
The name of the patentee: Porphyry Vladimirov S.
Address for correspondence: 249020, Kaluga region, Obninsk, st.. Engels, 19, kv.6, P.S.Vladimirovu
Starting date of the patent: 1998.11.20
The invention relates to power engineering, in particular to aircraft propulsion. The propulsion system comprises a low pressure turbine and a compressor with two propeller shafts mounted coaxially. Installation of engine comprises two shafts mounted coaxially. The plant comprises two engines with coaxial rotors mounted for rotation in the opposite direction. Propulsion shafts connected with engine rotors and their axial bores formed. One propulsion shafts located in the bore of the other shaft. Inside both shafts mounted compressor shaft connection and a low pressure turbine. The propulsion system may be used a rotary motor, the stator of which is mounted drive rotor and driven rotor, and the inlet and outlet ports blow cavities formed in the stator bores driven by the rotors. The object of the inventions is to improve the efficiency of the rotary engine, and therefore propulsion.
DESCRIPTION OF THE INVENTION
The invention relates to power engineering, in particular to aircraft propulsion systems and can be used in the propulsion on water transport complexes.
Known twin turboprop with a remote gear for driving two coaxial screw (GS Skubachevskii aviation gas turbine engines M.:. Mechanical Engineering, 1981, 15, Figure 1.1..), Comprising two parallel set of gas turbine engines.
The disadvantage of this scheme is a large area of the midsection and a significant drag, which reduces the efficiency of the flight, and a large mass, complexity and low reliability of the design with a reduction gear.
Known constructive scheme turbofan unit (GS Skubachevskii aircraft gas turbine engines. M .: Mechanical Engineering, 1981, pp. 8, 10, Fig. 1.03b, 1.06), adopted as the prototype for the first invention comprising a turbine and a compressor low pressure and propulsion device, such as a fan, with the shaft. This design contains no gearbox, but the propulsive efficiency is relatively low due to the low bypass ratio and substantial losses in the fixed guide of the fan blades.
From patent literature known rotary internal combustion engine (GB, A No. 1057282, cl. F 01 C 1/20, publ. 2.1.1967 g), received as a prototype for the invention and comprising a second stator with a body and two end caps, normally open internal working cavity in the form of three intersecting cylindrical bores, the center of which is located the male rotor with five cycloidal projections (teeth) and two end has two driven rotor with three cavities in each conjugate contactlessly with minimal clearances with the projections of the male rotor. Located in the central cavity of compression and expansion chambers, and in its housing wall formed with a window for admitting air nozzles charge and discharge of expanded combustion products.
The side walls of body cavities with the driven rotor exhaust ports are connected with a passageway expansion chamber, inlet ports for purging cavities driven rotors compress air and the fuel injection nozzle. The engine runs on two-stroke cycle, a purely rotational movement of the rotor it provides a unique rapidity and minimum specific gravity. The disadvantages it should be assigned a relatively small working volume of the expansion chamber, the chamber volume equal to a half in the central cavity, since the second half is occupied by a compression chamber; passageway operation at high speed rotors inefficient due to the inertia of the gas in the channel, throttling and expanding the combustion products impact energy loss, the need of an additional operation for its subsequent expulsion into the outlet.
The object of the first invention is to improve efficiency by reducing fuel consumption, area of the midsection, specific gravity, increasing engine efficiency.
The technical result is achieved by the propulsion system comprises a turbine and a low pressure compressor and the propeller, for example a fan, with the shaft, a second propeller shaft mounted coaxially with the first mover and two engines with coaxial rotors mounted with opposite direction of rotation, shaft propellers associated with engines and rotors are formed axial holes, wherein one of the shafts located with a clearance in the axial bore of the other shaft and one of the rotors and the inside of the two shafts and rotors installed communication compressor shaft and the low pressure turbine. Each engine comprises driving and driven engagement cycloidal rotors, the difference in the number of teeth of which is equal to one. The shaft of one of the movers unloaded thrust bearing installed between the engines.
Propulsion shafts connected to the rotors for axial displacement.
Propulsion shafts connected to the rotor through a gearbox. The setting is complete with rear propulsion.
The second motion during installation is connected to the propulsion nozzle of the last turbine stage and rear fairing. Drive along the first movement of the propulsion unit installation is equipped with a turbine rims, and its shaft unloaded on ball bearings, mounted in frames fixedly connected to the guide vanes and turbine nacelle. Straightener compressor is connected to the motor rotor. The setting is complete with a front-mounted propellers. The compressor and air inlet are installed at the first mover forward facing installation.
The object of the second invention is to increase the power density and efficient performance, design simplification.
The technical result is achieved by the fact that the outlet ports blow cavities are directly connected to the exhaust path, the inlet compression chamber windows are made in the bores of the female rotor, to choose the optimal number of teeth of the drive rotor and the driven rotor.
FIG. 1 shows a propulsion system in the axial section
FIG. 2 - A-A sectional view of the propulsion unit
FIG. 3 - rotary engine in axial section
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FIG. 4, 5 - a cross-section along EE | |
FIG. 6, 7 - three-rotor engine options
The propulsion system comprises a nacelle 1 which are fixedly mounted two rotor motor housing 2 and 3. The housings on bearings 4, 5, 6, 7 are installed several rotors 8 and 9, each of which is formed with an even (4, 6, 8, etc. .d.) number of toothed protrusions formed epitsikloydy equidistant from and meshed with the driven rotors 10, 11, 12, whose number of teeth by one tooth more (e.g., 5, 7, 9), the teeth of the envelope delineated or near gipotsikloyd it curve. Guided unloaded rotors in the housing through a gas-lubricated bearings; in the valleys of the teeth of the female rotor bypass ports 13, which are close to the outer dead point plenums 14 and the filling channels 15 communicate with the combustion chambers 16, which are installed in the fuel injectors 17. The axial length of the rotor 11 is twice the length of the rotors 10, 12 and they are diametrically opposed offset from the axis of the drive rotor. The end caps 18 and disks 19 in housing N.M.T. corresponding to the maximum volume of the chambers 20 formed inlet and outlet scavenging ports 21, 22 connected respectively to the inner space of the nacelle, which communicates with the low pressure compressor outlet 23 and exhaust collector 24, whose output is connected with the working path of the gas turbine engine 25. The working chambers are sealed with a gas-lubricated 26, 27, whose construction is known (SU, auth.'s Certificate. 958 755 a, cl. the F 16 J 15/44, publ. 15.09 .1982).
In addition, the motors have a system of active management gaps between the rotors and the housing, which is similar to (SU, auth.'s Certificate. 1,414,964, cl. 02 In the F 55/00, publ. 07.08.1988) and the figure is not shown. To minimize the gap, and gas leaks it is advisable to use obliteration clearance directly at the engine (RU, Patent 2013582, cl. 02 In the F 53/00, publ. 30.05.1994).
Inside the cavity formed leading rotors, heat exchange channels and cooling fins, and the axial hole and through which splined connection (for example, with intermediate balls) axially offset shaft mounted fan 28 or 29 and screw shaft 30 of the fan 31. The shaft 28 by a radially -upornogo bearing 32 mounted in frames 33 through sealed by the fixed guide vanes 34 with the body. On sealed bulkhead and guiding unit 35. On the shaft 28 is fixed a turbine 25, a fan 29 is connected to the turbine 36, a fan 31 fastened the last stage of the turbine 37, the nozzle 38 and the rear fairing (cook) 39. The shaft 30 is passed through the axial hole of the rotor 9 and unloaded through the angular contact ball bearing 40 located between the engines, on the body.
The axial bore of the shaft 30 is placed between the connection shaft 41 and the rotor 42 turbine 23 low pressure compressor. Rims straightener 43 low pressure compressor unit are installed or in a housing or drum 44 which through the blades 45 and the disk 46 is rigidly connected to the drive of the compressor rotor 8. The rotor is mounted on bearings 47, 48. The fan discs 29, 31 are annular channels crowns turbine blades 49, 50. The variant propulsion system with the traditional scapular turbine engines instead of the rotor, and the propulsion shafts advisable to connect with engine shafts through reducing gearboxes. Possible installation and execution with a front fan, in this embodiment, the compressor and the air inlet 51 may be installed in the front fan.
During rotation of the rotors 8, 11 volume mezhzubovyh cameras varies from a minimum of W. MT up to a maximum in N.M.T. Around 30 o to N.M.T. exhaust ports 21 are opened, then the inlet ports 20 and compressed air in the compressor 23 is carried out once-through purge working chambers of rotary engines, combustion products enter through the manifold 24 to the gas turbine 25, 36, 49, 50, 42, 37. The phase after ~ 270 o tdc purging is injected, the air is compressed to about 2 MPa, through windows 13 and discharge channel 14 with a twist displaced in the combustion chamber 16 mixes with fuel supplied injector 17, the mixture is ignited and burns with pressurized to about 7 MPa, then extension products occurs combustion and purging. Diametrically opposite to the displacement of the female rotor 11 relative to the rotors 10, 12 provides a balancing of radical gas pressure forces on the male rotor 8 and the discharge of their bearings. Power rotary engine via shafts 28, 30 is passed by fans 29, 31 having the opposite direction of rotation; torque on the turbine fan 25 increases further, 36, 49, 50, 37. The energy of the free turbine 42 through shaft 41 provides a drive of the compressor 23.
Technical and economic efficiency of useful suggestions in the following example:
The basic specifications of the propulsion system with 5-fold rotary engine (approximate):
Length mm - 3800
The area of the midsection ( 
740 mm), m 2 - 0.43
Weight, kg - 1100
Fan diameter, mm - 2400
Bypass ratio - 56
Power - 8000 kW
Specific gravity, kg / kW - 0.138
The temperature in the combustion chamber - 2800 K
The degree of pressure increase (at an altitude of 10 km) - 200
Fuel Ud.raskhod - 0.15 kg / kWh
Ud.tyaga - 0.134 kg / kg
Shaft rotation frequency - 3000 rev / min
Excess air ratio - 1
High technical indicators have a natural explanation: the high temperature of the gases in the combustion chamber in excess of approximately 1000 K temperature level in modern gas turbines, high pressure ratio, the possibility of exceptions to the design speed reducer, etc..
Careful optimization of the design and use of modern materials (carbon fiber, ceramics, silica glass, leucosapphire, glass ceramics, etc.) Provided a significant increase in these benefits.
Installation retains the advantages of using traditional coaxial turbine engines due to their location (decrease midsection) and high efficiency coaxial fans or propellers.
The rotary motor 51 comprises a stator working cavity disposed therein, formed with a central cylindrical bore 52 and the male rotor with four intersecting bores by a central bore 53 of the female rotor; which end plates 54 are fastened, 55 in which bearings 56, 57 fitted with the male rotor shaft 58 and the driven rotor 53, evenly spaced around the male rotor bores in the housing. The male rotor is provided with protrusions 59-teeth of cycloidal profile associated with depressions 60 on the female rotor. The central hole has a cylindrical outlet ports 61 with nozzles 62 driven by a rotor bores formed inlet ports 63 for blowing the compression chambers 64, which are formed by volumes of cavities 60 and 65 fragments in the central cavity disposed between the windows 61 and the driven rotors. Furthermore, in the stator bores made under the driven rotors outlet 66 and inlet 67 of the window for purging cavities of combustion products. Inlet ports 63 and 67 are connected to nozzles 68 supercharging unit, such as a turbocharger. FIG. 4, five inlet ports 63, 67 are aligned in a single window with a common nozzle; possible separation performance and their connection with each their spigot, for example, for purging air compression chamber of a higher pressure than from the cavities by blowing through the combustion nozzles 69 are connected with the discharge path. It is expedient execution of the pipes with a resonant length that increases the efficiency of blowing cavities and pre-charge compression chambers by a dynamic boost. Rotation of the connection gear is synchronized rotors 70, 71 mounted in a housing an ignition device 72, as which may be a spark plug, and (or) the fuel injectors.
Body and rotors are made of heat-resistant material with a low coefficient of thermal expansion (CTE), for example, structural ceramics, glass-ceramic, sapphire, Uglekon et al., And are associated with each other in the minimum order of 0.02-0.1 mm working their surface may have a relatively "soft" abradable coating, for example based on graphite; top rotor teeth and the leading edges of the depressions are covered driven rotor material of high hardness and wear resistance. Furthermore, on the sealing edges of the depressions on the tops of the teeth on the rear (in the direction) of the male rotor tooth surface and on the surfaces of bores expedient performance of labyrinth seals, such as scratches, grooves, arranged along a generatrix. The optimum number of teeth of the drive rotor and the driven rotor amount received from two to five, and the number of teeth and the driven rotor can be equal, as in Fig. 4; (The main rotor bearings 56 is almost completely discharged from the gas pressure forces), or the number of teeth of the rotors and the driven performed with the difference in the unit (for example, four and five slave rotor teeth; positive effect - the torque uniformity of the output shaft 58). The stator bores for the rotors may be driven performed additional channels 73 for increasing the degree of expansion of the gas cavities 60, but positive effect to be compared with the negative transient from the (virtually instantaneous) tightness loss when passing through the top of the rotor tooth canal.
A very simple design is shown in FIG. 6 and 7, it comprises a bidentate drive rotor 84 and two driven rotor 75 with the three recesses 76 each; inlet 77 and outlet nozzles 78 for blowing compressed air or depressions benzovozdushnoy mixture outlet ports 79 located in the upstream part of the male rotor 80 of expansion chamber housing, an ignition means 81 (nozzle or spark plug). By using rotary engine as part of the propulsion system in FIG. 1 and 2 for driving the rotor axis run through holes. The variant with the windows 82 and nozzles 83 for blowing the compression chambers 76, made separately from the nozzles 77 (see. Fig. 7).
When the engine through the pipes 68, 69 with compressed air from the fan or the turbocharger performed purge cavities 60 of the female rotor, then the fuel injection through the nozzle 72 with a big advance, the corresponding specific speed of the engine, purge the chamber of compression through the windows 63 with the release of products of combustion through the pipe 62, compression to a minimum volume (VM TA. see FIG. 4), where it ends during the preparation of the mixture and the ignition delay, then ignition, combustion, expansion in the depressions 60, about twice continued expansion chambers 74 and the exhaust gases to escape through the tubes 69 in the exhaust manifold and the turbine unit boost. Execution engine with two protrusions of the male rotor, and two driven rotors with three cavities, each provides a connection during expansion cavity volume with an expansion chamber prior to venting the exhaust pipe 79 (see. FIG. 6), thus the need for a bypass channel, existing in a certain analogy, it is no longer eliminated drawbacks associated to it. The same positive effect is manifested in a rotor with three drills driven rotors having three cavities and chetyrehzubom rotor paired with four driven rotors with two cavities each.
Non-contact seals provide high circumferential rotor speed (of the order of 50-100 m / s), the adiabatic mode of operation with minimum dosage cooled most heated seats and uncooled rotor body; excluded rotors waste oil and grease, while the gas leakage loss less mechanical friction losses in reciprocating engines. The combined effect of these factors provides a very light engine with a specific gravity of ~ 0.03 kg / kW, a simple, reliable, environmentally friendly, with a long service life and high efficiency performance.
CLAIM
1. The power plant comprising a turbine and a low pressure compressor and a mover, such as a fan, with the shaft, characterized in that it is further provided with a second propeller shaft mounted coaxially with the first propulsion motors and two coaxial rotors mounted for rotation in the opposite direction shafts associated with propulsion engines and rotors are formed axial holes, wherein one of the shafts located with a clearance in the axial bore of the other shaft and one of the rotors and the inside of the two shafts and rotors installed communication compressor shaft and the low pressure turbine.
2. The propulsion system of claim 1, characterized in that each motor includes driving and driven engagement cycloidal rotors, the difference in the number of teeth of which is equal to one.
3. The apparatus of claim. 2, characterized in that the shaft of one of the propellers on the unloaded ball bearings mounted between the motors.
4. Apparatus according to claim 2, characterized in that the propelling shafts are connected to the rotor axially offset.
5. Apparatus according to claim 2, characterized in that the propelling shafts are connected to the rotor through a gearbox.
6. Apparatus according to claim 2, characterized in that it is made with rear propellers.
7. Apparatus according to claim 6, characterized in that the second installation direction of travel is connected to the propulsion nozzle of the last turbine stage and rear fairing.
8. Installation according to claim 6, wherein the first drive while moving propeller installation is equipped with a turbine rims, and its shaft unloaded on ball bearings, mounted in frames fixedly connected to the guide vanes and turbine nacelle.
9. The apparatus of claim. 1, characterized in that the straightener is connected to the engine compressor rotor.
10. The apparatus of claim. 1, characterized in that it is made with a front propellers.
11. Apparatus according to claim 10, characterized in that the compressor and the air inlet are installed at the first mover during the installation movement.
12. A rotary motor comprising a stator with a working chamber formed by intersecting cylindrical surfaces (bores) in which the drive rotor fitted with protrusions and driven cycloidal rotors with cavities, inlets and outlet ports for purging and expansion of the compression chamber, intake and exhaust ports for blowing depressions, wherein said outlet ports for purging cavities connected to the engine exhaust path, the inlet compression chamber windows are made in the bores of the stator or rotor driven by aligned with the inlet cavities blowing windows.
13. An engine according to claim 12, characterized in that it comprises from two to five driven rotors arranged circumferentially around the main rotor.
14. The engine of claim. 13 wherein the number of the drive rotor driven protrusions equals the number of rotors.
15. An engine according to claim 13, characterized in that the number of teeth of the male rotor by one tooth more or less than the number of the driven rotors.
16. The engine of claim 13, wherein said drive rotor has two projections and is associated with two rotors have three cavities.
17. An engine according to claim 13, characterized in that the drive rotor and has three protrusions paired with three rotors having three cavities.
18. An engine according to claim 13, characterized in that the male rotor has four projections and four paired rotors having two cavities.
print version
Publication date 28.12.2006gg
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