The engine comprises a low pressure stage (1) and a high pressure stage (2) with two independent rotors (3,4) and associated fixed fluid preparation members (9,10,13,14), combining "compressor" means (15,16) and "expander" means (17,18) and at least one combustion chamber (19,20) in a central volume
The engine comprises a low pressure stage (1) and a high pressure stage (2) with two independent rotors (3,4) and associated fixed fluid preparation members (9,10,13,14), combining "compressor" means (15,16) and "expander" means (17,18) and at least one combustion chamber (19,20) in a central volume defined axially by the rotors (3,4) and laterally by three substantially cylindrical, coaxial walls (22,23,24), defining in pairs an outer duct (25) connecting the outlet of the LP compressor (15) to the inlet of the HP compressor (16) and an inner duct (26) connecting the outlet of the HP compressor (16) to the inlet of a first combustion chamber (19), whose outlet supplies the HP expander (18) with gases produced by combustion guided to the inlet of the LP expander (17), whose outlet is in communication with the outside via at least one exhaust opening (41) for the combustion gases.
대표청구항▼
The invention claimed is: 1. Thermal engine comprising: two independent rotors (3,4,4'), each respectively mounted in one of two casings (5,6,6'), the first rotor (3) belonging to a low pressure stage (1), the second rotor (4,4') belonging to a high pressure stage (2,2'), each stage (1,2,2') provid
The invention claimed is: 1. Thermal engine comprising: two independent rotors (3,4,4'), each respectively mounted in one of two casings (5,6,6'), the first rotor (3) belonging to a low pressure stage (1), the second rotor (4,4') belonging to a high pressure stage (2,2'), each stage (1,2,2') provided with its rotor (3,4,4') and associated fixed fluid preparation members (9,10,13,14,89,91,92, 93) combining gas compression means, known as compressors (15,16,90), and gas expansion means, known as expanders (17,18,90); and at least one combustion chamber (19,20) situated within a substantially cylindrical central volume defined at its bases by the two rotors (3, 4, 4') and their casings (5, 6, 6'), and at its lateral surface by a first substantially cylindrical wall (22), in an inner radial positions; said first wall being substantially coaxial with a second substantially cylindrical wall (23) in an intermediate radial position, these defining between them a first duct (26) connecting the outlet of the compressor (16,90) of the high pressure stage to the inlet of a first combustion chamber (19); and said second wall (23) being substantially coaxial with a third substantially cylindrical wall (24) in an outer radial position, these defining between them a second duct (25), outside the first duct (26) and connecting the outlet of the compressor (15) of the low pressure stage (1) to the inlet of the compressor (16, 90) of the high pressure stage (2, 2'); the outlet of the first combustion chamber (19) supplying the expander (18,90) of the high pressure stage (2,2') with gases produced by combustion, guided from the outlet of the expander (18,90) of the high pressure stage (2,2') to the inlet of the expander (17) of the low pressure stage (1), the outlet of which is in communication with the outside of a casing (24,27,31) of the engine via at least one exhaust opening (41) for the gases produced by combustion. 2. Thermal engine according to claim 1, in which the casing (24, 27, 31) of the engine, which comprises the third wall (24) defining radially towards the outside the second, annular, outer duct (25) for the flow of low pressure compressed gas, is made of thermally conductive material. 3. Thermal engine according to claim 1, in which the first, annular, inner duct (26) for the flow of high pressure compressed gas, is defined between the second wall (23), arranged as an intermediate casing of a thermally insulating material, radially towards the outside and separating it from the second duct (25), and the first wall (22) arranged as an inner casing of a thermally conductive material, radially towards the inside and separating it from the first combustion chamber (19). 4. Thermal engine according to claim 1, in which exhaust towards the outside of the gases stemming from the expander (17) of the low pressure stage (1) is ensured by discrete ducts (41) extending substantially radially towards the outside relative to the axis (XX) of the first rotor (3). 5. Thermal engine according to claim 1, comprising two combustion chambers (19,20) accommodated in the central volume between the two rotors (3,4), of which the first combustion chamber, known as the main combustion chamber (19), supplied with high pressure compressed gas, exiting from the compressor (16) of the high pressure stage (2) via the first duct (26), converges substantially in the direction of the axis (XX) of the second rotor (4) towards the inlet of the expander (18) of the high pressure stage (2), whose outlet (38) leads into the inlet of the second combustion chamber, known as the secondary combustion chamber (20), surrounded by the first annular combustion chamber (19) and which converges axially towards its outlet connected radially towards the outside to the inlet of the expander (17) of the low pressure stage (1), flow of the gases in the two combustion chambers (19,20) taking place substantially axially in opposing directions. 6. Thermal engine according to claim 5, such that the two combustion chambers (19, 20) are separated from one another by a substantially conical central partition (21) of a thermally conductive material shaped so as to define the countercurrent convergent paths of the two combustion chambers (19, 20). 7. Thermal engine according to claim 4, in which ducts (41) exhausting towards the outside the exhaust gases stemming from the expander (17) of the low pressure stage (1) are defined between two substantially radial, thermally insulating inner walls (39,42), one (39) of which surrounds the outlet (40) of the expander (17) of the low pressure stage (1), while the second (42) diverts radially towards the outside the gases produced by combustion stemming from said at least one combustion chamber (19,20) and from the expander (18) of the high pressure stage (2). 8. Thermal engine according to claim 1, for which the ratio of the substantially radial and axial dimensions relative to the axis (XX) of one at least of the rotors (3,4) is about 1. 9. Thermal engine according to claim 1, the low pressure stage (1) of which comprises the first rotor (3), which comprises, on a face facing the outside of the engine, a bladed wheel (7) of a centrifugal compressor (15), which rotates radially inside an annular diffuser (9) with blades which are fixed relative to the casing (5) of the first rotor (3), and, on the inner face of the first rotor, a bladed wheel (11) of a centripetal turbine (17), which rotates radially inside an annular centripetal distributor (13) with blades which are fixed relative to the casing (5) of the first rotor (3), the wheels (7,11) of the compressor (15) and turbine (17) being connected for rotation around their common axis (XX), which is the axis of the first rotor (3). 10. Thermal engine according to claim 9, the high pressure stage (2) of which has an architecture similar to that of the low pressure stage (1), the two stages being inverted relative to one another, the high pressure stage (2) comprising the second rotor (4), which comprises, on a face facing the outside of the engine, a bladed wheel (8) of a centrifugal compressor (16), which rotates radially inside an annular diffuser (10) with blades fixed relative to the casing (6) of the second rotor (4), and, on the inner face of the second rotor (4), a bladed wheel (12) of a centripetal turbine (18), which rotates radially inside an annular centripetal distributor (14) with blades fixed relative to the casing (6) of the second rotor (4), the wheels (8,12) of the compressor (16) and the turbine (18) being connected for rotation around their common axis (XX), which is the axis of the second rotor (4). 11. Thermal engine according to claim 9, the high pressure stage (2') of which comprises a wave compressor-expander, known as a "wave rotor", in which a transfer of energy between compression of a gas and expansion of combusted gases takes place inside a wheel (4') with channels (90) by direct contact between said gas and said combusted gases in said channels (90) and by a process based on the displacement of expansion waves and compression waves in said channels (90) of said channeled wheel (4'), said "wave rotor" comprising an inlet (89) for admission gas (air), an outlet (92) for compressed gas (air), connected to a first combustion chamber (19), an admission inlet (91) for the combusted gases stemming from the outlet of the first combustion chamber (19), and an exhaust outlet (92) for said combusted gases, towards a second combustion chamber (20), if applicable, and the expander (17) of the low pressure stage (1). 12. Thermal engine according to claim 1, of which the rotors (3, 4) are supported axially and radially by gas bearings (44, 45, 46, 47). 13. Thermal engine according to claim 1, in which the casing (24, 27, 31) of the engine defining, radially towards the outside, the second duct (25) is at least partially immersed in a preferably double-walled (52), impermeable, closed water tank (51), intended to produce pressurized steam and to insulate the thermal engine thermally from the outside and facilitate its integration in a receptacle designed therefor. 14. Thermal engine according to claim 13, in which the steam produced in a first chamber (56) of the tank (51) has its pressure controlled by a valve (58) communicating with a second tank chamber (54), itself in communication with the inlet of the expander (17) of the low pressure stage (1), so as to mix steam with the gases produced by combustion stemming from said at least one combustion chamber (19,20), before passage thereof into the expander (17) of the low pressure stage (1). 15. Thermal engine according to claim 14, in which the gases and steam stemming from the expander (17) of the low pressure stage (1) are exhausted via separate ducts (41), and continuing (55) through the water tank (51) before emerging into the surrounding environment, so as to ensure preheating of the water in the tank (51). 16. Thermal engine according to claim 13, in which the stream of gas (air) stemming from the compressor (15) of the low pressure stage (1) is divided into two flows, one of which is directed towards the compressor (16) of the high pressure stage (2) and the other towards utilization (60), in pneumatic form, of the useful power. 17. Thermal engine according to claim 16, in which the flow of low pressure compressed gas (air), corresponding to the useful power transmitted by the compressor (15) of the low pressure stage (1), supplies a turbine (61) of a turbogenerator (68), whose electric generator (65, 66) supplies a battery (72), connected by at least one electrical power outlet (75) to at least one electrical consumer unit. 18. Thermal engine according to claim 17, in which the electric turbogenerator (68) is thermally insulated (67) from the engine casing enclosing the two rotors (3,4), said at least one combustion chamber (19,20) and the ducts (25,26) for the flow of low pressure and high pressure compressed gas (air) and low pressure and high pressure gases produced by combustion. 19. Thermal engine according to claim 18, in which the electric generator (65,66) of the turbogenerator (68) is of magnetic type, comprising at least one permanent magnet (65) mounted on one face of a bladed wheel (63) of the centripetal turbine (61) of the turbogenerator (68), on the opposite side to the face having the blades of said centripetal turbine (61), said at least one permanent magnet (65) being connected for rotation to the centripetal turbine wheel (63) of the turbogenerator (68) and revolving opposite at least one flat armature coil (66) of the electric generator (65,66). 20. Thermal engine according to claim 19, in which the battery (72) supplied by the electric generator (65,66) of the turbogenerator (68) itself supplies at least one electrical ignition device for the gas (air)/fuel mixture in said at least one combustion chamber (19, 20), into which fuel is injected via at least one fuel supply duct (49, 49'). 21. Thermal engine according to claim 17, in which the battery (72) supplied by the electric generator (65,66) of the turbogenerator (68) itself supplies at least one heating resistor (77) disposed in a chamber (56) of the water tank (51), to produce pressurized steam supplying the expander (17) of the low pressure stage (1) so as to start the thermal engine with electrical starter with heating resistor (77). 22. Thermal engine according to claim 17, in which the flow of low pressure compressed gas (air) stemming from the compressor (15) of the low pressure stage (1) supplies the centripetal turbine (61) of the turbogenerator (68) after opening of a check valve (74), through an element selected from an annular centripetal distributor (62) with fixed blades surrounding the bladed wheel (63) of said centripetal turbine (61) of the turbogenerator (68), and a volute surrounding said centripetal turbine (61) of the turbogenerator (68). 23. Thermal engine according to claim 1, equipped with a starter (79) using solid propellant (80), in which the starter (79) is arranged as a gas generator by ignition (82), of the solid propellant (80), such that a gas flow resulting from combustion of the solid propellant is directed, via at least one inlet (86) in a radial end face of the engine casing, preferably around an admission gas (air) inlet opening (30) in the thermal engine, so as to bring about rotation of the rotor (3) of the low pressure stage (1). 24. Thermal engine according to claim 23, in which the starter (79) arranged as a gas generator receives a solid propellant cartridge (80) provided for each start of the thermal engine, said gas generator being connected to the inside of the casing of the thermal engine via at least one quasi-tangential inlet (86) so as to set the rotor (3) of the low pressure stage (1) in rotation.
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