FACE-COATED WINDER FOR AN AIRCRAFT TURBOMACHINE

Abstract

A shrouded fan (8) for an aircraft turbomachine (1) (2), the shrouded fan (8) comprising a disc (35) carrying an annular row of blades (11), the disc (35) being annular about a longitudinal axis (X), the disc (35) comprising a body (36) and a flange (37) connected to each other by a first web (38), the flange (37) being intended to be fixed to a compressor shaft (19); characterized in that the disc (35) comprises a second web (39) which connects the body (36) and the flange (37), the second web (39) being separated from the first web (38) so as to form between them an annular cavity (40) about the axis (X). Figure for the abstract: 2

Description

Title of the invention: DUCTED FAN FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The present invention relates to a ducted fan for an aircraft turbomachine, as well as to an aircraft turbomachine comprising such a ducted fan. Technical background

[0002] A so-called “Open Fan” turbomachine comprises an unducted mobile fan which is driven in rotation by a power turbine, and an unducted fixed rectifier which is configured to straighten at least a portion of the air flow generated by the unducted fan.

[0003] Such a high bypass ratio turbomachine has the advantage of having excellent efficiency, with in particular a reduction in fuel consumption and carbon dioxide emissions.

[0004] Conventionally, the power turbine is associated with a gas generator which comprises at least one compressor, a combustion chamber and at least one expansion turbine. More precisely, the power turbine is rotated by the gases leaving the expansion turbine.

[0005] To optimize the performance of the “Open Fan” turbomachine, it is known to install a mobile ducted fan and possibly a low-pressure compressor (more commonly called a “booster”) in the air inlet which feeds the gas generator. Such a ducted fan is commonly called a “Mid-Fan”.

[0006] Such a ducted fan is driven in rotation by the power turbine. The ducted fan comprises a disc carrying an annular row of blades. The disc is annular, and may comprise a body and a flange connected to each other by a web, the flange being for example secured to a shaft which is driven in rotation by the power turbine.

[0007] The first feedback obtained by calculation shows that the ducted fan has a stiffness that is too low compared to that predefined in the specifications, which takes into account in particular the vibration behavior of the turbomachine. Too low a stiffness here leads to a placement of the frequency mode in an operating range of the turbomachine and a sensitivity of the vibration response level to the unbalance of the rotor, creating difficulties in avoiding excessive stress on the bearings used to guide the ducted fan.

[0008] To further stiffen the shrouded fan, and in particular its disc, a solution could be to increase its thickness. Such a solution allows a slight gain in stiffness but significantly increases the mass of the ducted fan, and consequently the fuel consumption of the turbomachine, which is not desirable.

[0009] The objective of the present invention is therefore to propose a solution making it possible to increase the stiffness of the ducted fan to meet the requirements of the specifications while minimizing the increase in its mass. Summary of the invention

[0010] The invention thus proposes a ducted fan for an aircraft turbomachine, the ducted fan comprising a disk carrying an annular row of blades, the disk being annular around a longitudinal axis X, the disk comprising a body and a flange connected to each other by a first web, the flange being intended to be secured to a compressor shaft; characterized in that the disc comprises a second web which connects the body and the flange, the second web being distant from the first web so as to form between them an annular cavity around the X axis.

[0011] The incorporation of a second web at a distance from the first web not only makes it possible to meet the requirements of the specifications in terms of stiffness (radial stiffness, rotational stiffness and combined stiffness) but also to limit the impact in terms of mass.

[0012] The ducted fan according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: - the body comprises an outer rim which carries the annular row of blades and an inner bulb, the rim and the bulb being connected to each other by a stilt, the first and second webs each connecting the bulb and the flange; - the first web connects an outer end of the bulb and an outer end of the flange, and the second web connects an inner end of the bulb and an inner end of the flange; - the first and second veils flare from the bridle to the body; - the distance dr, dn between the first and second sails is constant; - the cavity has a parallelogram shape in cross-section; - the first and second sails are parallel to each other in cross-section; - the radial dimension Dr of the cavity is at least equal to twice the radial thickness Er of the first web or the second web; - the first and second sails are in one piece with the body and the bridle; - the first veil is in one piece with the body and the bridle, and the second veil is reported and fixed to both the body and the flange, the second web preferably being strapped to the body and the flange.

[0013] The present invention also relates to an aircraft turbomachine comprising: - a gas generator which is powered by an air inlet; - a power turbine which is independent of the gas generator; - an unducted fan which is rotated by the power turbine; - an unshrouded rectifier which is fixed in rotation; - a ducted fan as described above, the ducted fan being placed in the air inlet and driven in rotation by the power turbine.

[0014] The turbomachine according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: - the turbomachine comprises a low-pressure compressor comprising a rotor, the ducted fan and the rotor of the low-pressure compressor being jointly driven in rotation by the power turbine via a compressor shaft; - the rotor of the low pressure compressor comprises a drum which has a flange, the compressor shaft comprising a collar which carries a flange, the flange of the shrouded fan, the flange of the drum and the flange of the compressor shaft being secured to each other via an annular row of bolts; - the free ends of the blades of the shrouded fan are surrounded by a shroud which carries the unshrouded rectifier; - the unducted fan is rotated by the power turbine via a speed reducer, the unducted fan comprising an annular row of variable-pitch blades and the unducted rectifier comprising an annular row of variable-pitch guide vanes. Brief description of the figures

[0015] The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:

[0016] [Fig-1] [Fig.l] is a schematic view in longitudinal half-section of a tur aircraft machine according to the invention;

[0017] [Fig.2] [Fig.2] is a detail view of [Fig.l] which illustrates the connection between the ducted fan, the rotor of the low pressure compressor and the compressor shaft;

[0018] [Fig.3] [Fig.3] is a view similar to [Fig.2] which represents an alternative embodiment. Detailed description of the invention

[0019] In [Fig.l] is shown a turbomachine 1 for an aircraft 2, such as an airplane.

[0020] The turbomachine 1 comprises: - a gas generator 3 which is supplied by an air inlet 4; - a power turbine 5 which is independent of the gas generator 3, namely that it is associated with a shaft 20 which rotates without direct rotational connection with rotating elements, such as a shaft, of the gas generator; - an unducted fan 6 which is driven in rotation by the power turbine 5; - an unshrouded rectifier 7 which is fixed in rotation; - a ducted fan 8 (more commonly called “Mid-Fan”) which is placed in the air inlet 4 and driven in rotation by the power turbine 5.

[0021] The term “unducted” associated with the fan 6 means that the blades 9 of the fan 6 are not surrounded at their free end by a fairing.

[0022] Furthermore, the term “unshrouded” associated with the rectifier 7 means that the guide vanes 10 of the rectifier 7 are not surrounded at their free end by a shroud.

[0023] Furthermore, the term “faired” associated with the fan 8 means that the blades 11 of the fan 8 are surrounded at their free end 48 by a fairing (here a nacelle 12).

[0024] Finally, the term “independent” associated with the power turbine 5 means that the power turbine 5 is not linked in rotation with the gas generator 3.

[0025] The turbomachine 1 is defined along a longitudinal axis X which corresponds in particular to the axis of rotation of the unducted fan 6, of the ducted fan 8, and of the rotors 18 of the compressors 13, 14 and turbines 5, 16.

[0026] According to the embodiment illustrated in [Fig.l], the turbomachine 1 further comprises a low pressure compressor 13 (more commonly called a “booster”) which is driven in rotation by the power turbine 5.

[0027] The low pressure compressor 13 is arranged upstream of the gas generator 3, and the power turbine 5 is arranged downstream of the gas generator 3.

[0028] The gas generator 3 is supplied with air by the air inlet 4 which opens between the unducted fan 6 and the rectifier 7. Conventionally, the gas generator 3 comprises in particular at least one high-pressure compressor 14, a combustion chamber 15 and at least one expansion turbine 16 (or high-pressure turbine). The rotors of the high-pressure compressor 14 and of the expansion turbine 16 are linked in rotation by one or more transmission shafts 17.

[0029] The ducted fan 8 and the rotor 18 of the low-pressure compressor 13 are jointly driven in rotation by the power turbine 5 via a compressor shaft 19 and a turbine shaft 20.

[0030] More specifically, as illustrated in [Fig.l], the low pressure compressor 13 here comprises two axial compression stages. The low pressure compressor 13 comprises a rotor 18 comprising a drum 21 on which two annular rows of blades 22 are attached. The drum 21 comprises a flange 23 at its upstream end which is secured to a flange 24 of the compressor shaft 19. The flange 24 of the compressor shaft 19 is carried by a collar 25 which extends substantially radially relative to a longitudinal body 26 of the shaft 19.

[0031] The high-pressure compressor 14 here comprises five axial compression stages.

[0032] The combustion chamber 15 is supplied with compressed air via the compressor high pressure 14, and fuel via several injectors. The air / fuel mixture is burned under the action of several ignition devices. The exhaust gases from the combustion chamber 15 are expanded in the expansion turbine 16 and then in the power turbine 5.

[0033] The expansion turbine 16 here comprises two axial expansion stages.

[0034] The power turbine 5 here comprises four axial expansion stages. The power turbine power 5 is driven in rotation by the exhaust gases leaving the expansion turbine 16, the exhaust gases then being evacuated via a nozzle 27.

[0035] The embodiment illustrated in [Fig.l] is in no way limiting. The compressors 13, 14 and the turbines 5, 16 could, for example, comprise a different number of stages. Generally speaking, a compressor may comprise one or more axial and / or centrifugal compression stages. A turbine may comprise one or more axial and / or centripetal expansion stages.

[0036] As illustrated in [Fig.l], the unducted fan 6 is rotatable about the axis X. The unducted fan 6 comprises an annular row of variable-pitch blades 9, each blade 9 being pitched about an axis of rotation Y1 which is substantially perpendicular to the axis X. The unducted fan 6 comprises a system 28 for adjusting the pitch of the blades 9, this adjustment system 28 being able to be common to all the blades 9 or specific to each of the blades 9.

[0037] According to an exemplary embodiment, the adjustment system 28 comprises an actuator common to all the blades 9 and a mechanism specific to each of the blades 9, this mechanism making it possible to transform the movement initiated by the actuator into a rotational movement of the corresponding blade 9.

[0038] The unducted fan 6 is driven in rotation by the power turbine 5 via a speed reducer 29. The speed reducer 29 makes it possible to reduce the rotation speed of the unducted fan 6 relative to that of the power turbine 5, while increasing its torque.

[0039] More precisely, the compressor shaft 19 is rotationally connected to an input element 30 of the speed reducer 29 and the unducted fan 6 is rotationally connected to an output element 31 of the speed reducer 29.

[0040] Advantageously, the speed reducer 29 is a gear train reducer, and preferably an epicyclic train reducer. An epicyclic train reducer has the advantage of having a high reduction ratio while being compact.

[0041] An epicyclic gear reducer comprises at least one reduction stage comprising a sun (or planetary), a crown, satellites and a planet carrier. An epicyclic gear reducer can be configured in different ways.

[0042] According to a first configuration, the solar is the input element 30 of the reducer 29, the crown is the output element 31 of the reducer 29, and the planet carrier is fixed or immobile. In other words, the solar is linked in rotation with the compressor shaft 19, and the crown is linked in rotation with the unducted fan 6.

[0043] According to a second configuration, the solar is the input element 30 of the reducer 29, the crown is fixed or immobile, and the planet carrier is the output element 31 of the reducer 29. In other words, the solar is linked in rotation with the compressor shaft 19, and the planet carrier is linked in rotation with the unducted fan 6.

[0044] The two configurations explained above are in no way limiting, other configurations are obviously conceivable depending in particular on the desired reduction ratio.

[0045] Similarly, the gear train reducer may comprise one or more reduction stages.

[0046] The unducted blower 6 internally defines an enclosure 32 in which the gear train reducer is housed and lubricated here.

[0047] When the turbomachine 1 is in “propulsor” mode, the unducted fan 6 generates an air flow F which flows from upstream to downstream around the outer fairings of the streamlined body of the turbomachine 1, so as to generate the majority of the thrust which will propel or move the aircraft 2 forward. The turbomachine 1 can also operate in “reverser” mode, so as to brake the aircraft 2 at the time of its landing.

[0048] By convention in the present application, the terms “upstream” and “downstream” are defined relative to the direction of circulation of the air flow F, when the turbomachine 1 is in “propulsor” mode.

[0049] As illustrated in [Fig.l], the unducted rectifier 7 is fixed in rotation about the axis X and is configured to straighten at least a portion of the air flow F generated by the unducted fan 6. The rectifier 7 is arranged here directly downstream of the unducted fan 6. The rectifier 7 is carried by a nacelle 12 of the turbomachine 1. The rectifier 7 comprises an annular row of guide vanes 10 (or stator vanes or OGV vanes for “Outlet Guide Vane”), the guide vanes 10 being arranged regularly around the nacelle 12.

[0050] The guide vanes 10 are variable-pitch, each guide vane 10 being set around an axis of rotation Y2 which is substantially perpendicular to the X axis.

[0051] The rectifier 7 comprises a system 33 for adjusting the timing of the guide vanes 10, this adjustment system 33 being able to be common to all the guide vanes 10 or specific to each of the guide vanes 10. The adjustment system(s) 33 are located in an interior compartment 34 of the nacelle 12.

[0052] According to an exemplary embodiment, the adjustment system 33 comprises an actuator common to all the guide vanes 10 and a mechanism specific to each of the guide vanes 10, this mechanism making it possible to transform the movement initiated by the actuator into a rotational movement of the corresponding guide vane 10.

[0053] In the remainder of the description, we will focus more particularly on the ducted fan 8.

[0054] The ducted fan 8 comprises a disc 35 carrying an annular row of blades 11. The disc 35 is annular (or of revolution) around the longitudinal axis X. The disc 35 comprises a body 36 and a flange 37 connected to each other by a first web 38. The flange 37 is secured to a compressor shaft 19.

[0055] According to the invention, the disc 35 comprises a second web 39 which connects the body 36 and the flange 37, the second web 39 being distant from the first web 38 so as to form between them an annular cavity 40 around the axis X.

[0056] The incorporation of a second web at a distance from the first web not only makes it possible to meet the requirements of the specifications in terms of stiffness (radial stiffness, rotational stiffness and combined stiffness) but also to limit the impact in terms of mass.

[0057] In the same way as the turbomachine 1, the ducted fan 8 is defined along the longitudinal axis X.

[0058] Advantageously, the body 36 comprises an external rim 41 which carries the annular row of blades 11 and an internal bulb 42. The rim 41 and the bulb 42 are connected to each other by a stilt 43. The first and second webs 38, 39 each connect the bulb 42 and the flange 37. Such an arrangement of the webs is favorable to increasing the stiffness of the disk.

[0059] Advantageously, the first web 38 connects an external end 44 of the bulb 42 and an external end 45 of the flange 37, and the second web 39 connects an internal end 46 of the bulb 42 and an internal end 47 of the flange 37. Such an arrangement of the webs makes it possible to maximize the distance between the webs, and consequently the stiffness of the disc.

[0060] Advantageously, the first and second webs 38, 39 flare from the flange 37 to the body 36, so as to reduce the mass of the disc.

[0061] When the flange 37 is arranged downstream of the body 36, the first and second webs 38, 39 widen from downstream to upstream from the flange 37 to the body 36. Conversely, when the flange 37 is arranged upstream of the body 36, the first and second webs 38, 39 flare from upstream to downstream from the flange 37 to the body 36.

[0062] The distance dr, dn between the first and second webs 38, 39 may be constant. In such a case, the first and second webs 38, 39 are then parallel to each other in cross-section. Alternatively, the distance dr, dn between the first and second webs 38, 39 could decrease from the body 36 to the flange 37.

[0063] The “distance” stated above can be for example the radial distance dr (with reference to the X axis) or the normal distance dn (with reference to the measured surfaces).

[0064] The cavity 40 may have a quadrilateral shape in cross section, and more particularly a parallelogram shape.

[0065] Advantageously, the radial dimension Dr of the cavity 40 is at least equal to twice the radial thickness Er of the first web 38 or of the second web 39. Such dimensioning of the cavity makes it possible to meet the stiffness criterion defined in the specifications.

[0066] The first and second webs 38, 39 may be in one piece with the body 36 and the flange 37, the disc then being a single piece. In such a case, the blades 11 may also be in one piece with the disc to form a single-piece bladed disc. The single-piece disc or the single-piece bladed disc are advantageously obtained by additive manufacturing (for example by selective powder bed fusion). Alternatively, the blades 11 may of course be added and fixed to the single-piece disc.

[0067] The first web 38 may be integral with the body 36 and the flange 37, while the second web 39 is attached and fixed to both the body 36 and the flange 37. In such a case, the blades 11 may be attached to the body 36 or be integral with the body 36. The second web 39 is preferably hooped to the body 36 and to the flange 37. Hooping allows the second web 39 to be assembled via a tight fit. Hooping may be achieved by contraction of the second web 39 (with a cooling device that uses, for example, liquid nitrogen), or by expansion of the assembly comprising the body 36, the first web 38 and the flange 37 (with a heating device), or even by a combination of the two.

[0068] The inner end 64 of the second web 39 can be hooped not only to the flange 37 but also to a directly adjacent element such as the flange 23 of the drum 21.

[0069] The second veil 39 may comprise different slots distributed around the axis X, so as to locally access the cavity 40. These slots are for example used to allow the passage of a tool (tool used for example for the installation and tightening of a bolt) and / or the evacuation of the surplus powder located in the cavity 40 when the disc 35 is obtained partially or totally by manufacturing additive.

[0070] As illustrated in Figures 1 to 3, the ducted fan 8 is placed in the air inlet 4, the free ends 48 of the blades 11 being surrounded by the nacelle 12. The ducted fan 8 is arranged upstream of the low-pressure compressor 13. The ducted fan 8 is rotatable about the axis X.

[0071] The ducted fan 8 and the rotor 18 of the low-pressure compressor 13 are jointly driven in rotation by the power turbine 5 via the compressor shaft 19 and the turbine shaft 20.

[0072] More precisely, the flange 37 of the ducted fan 8, the flange 23 of the drum 21 and the flange 24 of the compressor shaft 19 are secured to each other via an annular row of bolts 49 around the axis X.

[0073] Each bolt 49 comprises a screw 50 and a nut 51, the rod 52 of the screw 50 passing simultaneously through a through hole 53 formed in the flange 24 of the compressor shaft 19, a through hole 54 formed in the flange 23 of the drum 21 and a through hole 55 formed in the flange 37 of the ducted fan 8.

[0074] The flange 23 of the drum 21 is arranged axially between the flange 37 of the ducted fan 8 and the flange 24 of the shaft 19.

[0075] The flange 23 of the drum 21 comprises an external rim 56 which projects from an upstream face of the flange 23, this external rim 56 makes it easier to position the flange 37 of the ducted fan 8. In addition, the flange 23 of the drum 21 comprises an internal rim 57 which projects from a downstream face of the flange 23, this internal rim 57 makes it easier to position the flange 24 of the compressor shaft 19.

[0076] The air flow generated by the ducted fan 8 is divided, by a separation nozzle 58 of a profiled and fixed structure 59 of the turbomachine 1, into a primary air flow fl which enters a primary vein 60 intended to supply the gas generator 3, and into a secondary air flow f2 which flows in a secondary vein 61 defined between the profiled structure 59 and the nacelle 12. The secondary air flow f2 contributes in a minor way to the thrust provided by the turbomachine 1. The profiled structure 59 simultaneously surrounds the low-pressure compressor 13, the gas generator 3 and the power turbine 5.

[0077] As illustrated in the figures, and in particular figures 2 and 3, the body 36 of the disc 35 comprises an external rim 41 which carries the annular row of blades 11 and an internal bulb 42, the rim 41 and the bulb 42 being connected to each other by a stilt 43.

[0078] The bulb 42 is a swollen or widened internal portion of the body 36 which is commonly called the “leek”. The stilt 43 (or web or core) is a tapered or thinned intermediate portion which forms the connection between the rim 41 and the bulb 42.

[0079] The flange 37 is arranged downstream of the body 36 and is connected to the body 36 by a web external 38 (first veil) and an internal veil 39 (second veil).

[0080] More precisely, the outer web 38 connects an outer end 44 of the bulb 42 and an outer end 45 of the flange 37, and the inner web 39 connects an inner end 46 of the bulb 42 and an inner end 47 of the flange 37.

[0081] The outer and inner webs 38, 39 here flare from downstream to upstream from the flange 37 to the body 36. The radial distance dr or normal dn between the outer and inner webs 38, 39 is constant, and in other words the outer and inner webs 38, 39 are parallel to each other in cross-section. The outer and inner webs 38, 39 each have a radial thickness Er which is constant. The radial thicknesses Er of the outer and inner webs 38, 39 are equal.

[0082] The cavity 40 has a parallelogram shape in cross section. The radial dimension Dr of the cavity 40 is here equal to three times the radial thickness Er of the external web 38 or of the internal web 39.

[0083] According to the embodiment illustrated in Figures 1 and 2, the external and internal sails 38, 39 are in one piece with the body 36 and the flange 37, the disc 35 then being in one piece.

[0084] As indicated above, the single-piece disc 35 is advantageously obtained by additive manufacturing.

[0085] The internal veil 39 comprises several slots distributed around the X axis, each slot being arranged at the level of a bolt 49 to allow its installation and tightening.

[0086] According to the embodiment variant illustrated in [Fig. 3], the external web 38 is in one piece with the body 36 and the flange 37, while the internal web 39 is hooped to the body 36, to the flange 37 of the disc 35 and to the flange 23 of the drum 21.

[0087] As indicated above, the hooping can be obtained by contraction of the internal web 39 (with a cooling device which uses for example liquid nitrogen), or by an expansion of the assembly comprising the body 36, the external web 38 and the flange 37 (with a heating device), or even by a combination of the two.

[0088] Once the internal web 39 is hooped, the external end 62 of the internal web 39 is in radial support on the internal face 63 of the bulb 42. Furthermore, the internal end 64 of the internal web 39 is in radial support on the internal face 65 of the flange 37 of the disc 35 and on the internal face 66 of the flange 23 of the drum 21.

[0089] The bolts 49 can be put in place and tightened before the inner web 39 is hooped. Alternatively, the inner web 39 comprises several slots distributed around the X axis, each slot being arranged at the level of a bolt 49 to allow it to be put in place and tightened, after the inner web 39 is hooped.

Claims

Claims

1. Ducted fan (8) for a turbomachine (1) of an aircraft (2), the ducted fan (8) comprising a disc (35) carrying an annular row of blades (11), the disc (35) being annular about a longitudinal axis (X), the disc (35) comprising a body (36) and a flange (37) connected to each other by a first web (38), the flange (37) being intended to be secured to a compressor shaft (19); characterized in that the disc (35) comprises a second web (39) which connects the body (36) and the flange (37), the second web (39) being distant from the first web (38) so as to form between them an annular cavity (40) about the axis (X).

2. Ducted fan (8) according to claim 1, characterized in that the body (36) comprises an external rim (41) which carries the annular row of blades (11) and an internal bulb (42), the rim (41) and the bulb (42) being connected to each other by a stilt (43), the first and second sails (38, 39) each connecting the bulb (42) and the flange (37).

3. Ducted fan (8) according to the preceding claim, characterized in that the first web (38) connects an external end (44) of the bulb (42) and an external end (45) of the flange (37), and the second web (39) connects an internal end (46) of the bulb (42) and an internal end (47) of the flange (37).

4. Ducted fan (8) according to one of the preceding claims, characterized in that the first and second sails (38, 39) flare from the flange (37) to the body (36).

5. Ducted fan (8) according to one of the preceding claims, characterized in that the distance (dr, dn) between the first and second sails (38, 39) is constant.

6. Ducted fan (8) according to one of the preceding claims, characterized in that the cavity (40) has a parallelogram shape in cross section.

7. Ducted fan (8) according to one of the preceding claims, characterized in that the first and second sails (38, 39) are parallel to each other in cross section.

8. Ducted fan (8) according to one of the preceding claims, characterized in that the radial dimension (Dr) of the cavity (40) is at least equal to twice the radial thickness (Er) of the first web (38) or of the second web (39).

9. Ducted fan (8) according to one of the preceding claims, characterized in that the first and second sails (38, 39) are in one piece with the body (36) and the flange (37).

10. Ducted fan (8) according to one of claims 1 to 8, characterized in that the first web (38) is in one piece with the body (36) and the flange (37), and the second web (39) is attached and fixed both to the body (36) and to the flange (37), the second web (39) preferably being shrunk to the body (36) and to the flange (37).

11. Turbomachine (1) of aircraft (2) comprising: - a gas generator (3) which is supplied by an air inlet (4); - a power turbine (5) which is independent of the gas generator (3); - an unducted fan (6) which is driven in rotation by the power turbine (5); - an unducted rectifier (7) which is fixed in rotation; - a ducted fan (8) according to one of the preceding claims, the ducted fan (8) being placed in the air inlet (4) and driven in rotation by the power turbine (5).

12. Turbomachine (1) according to the preceding claim, characterized in that the turbomachine (1) comprises a low pressure compressor (13) comprising a rotor (18), the ducted fan (8) and the rotor (18) of the low pressure compressor (13) being jointly driven in rotation by the power turbine (5) via a compressor shaft (19).

13. Turbomachine (1) according to the preceding claim, characterized in that the rotor (18) of the low pressure compressor (13) comprises a drum (21) which has a flange (23), the compressor shaft (19) comprising a collar (25) which carries a flange (24), the flange (37) of the ducted fan (8), the flange (23) of the drum (21) and the flange (24) of the compressor shaft (19) being secured to each other via an annular row of bolts (49).

14. Turbomachine (1) according to one of claims 11 to 13, characterized in that the free ends (48) of the blades (11) of the shrouded fan are surrounded by a shroud (12) which carries the unshrouded rectifier (7).

15. Turbomachine (1) according to one of claims 11 to 14, characterized in that the unducted fan (6) is driven in rotation by the power turbine (5) via a speed reducer (9), the fan unducted (6) comprising an annular row of variable-pitch vanes (9) and the unducted rectifier (7) comprises an annular row of variable-pitch guide vanes (10).

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