Aircraft turbine engine comprising an unducted fan and an unshrouded stator

Abstract

The invention relates to a turbine engine (1) of an aircraft (2), comprising: - a gas generator (3) of longitudinal axis (X1) which comprises a power turbine (4); - an unducted fan (5) which is movable about a longitudinal axis (X2) which is parallel to the axis (X1) and offset radially with respect to the axis (X1), the fan (5) being driven by the power turbine (4) via a speed reducer (6) which is arranged radially above an air inlet (7) of the gas generator (3); - an unshrouded stator (8) which is rotationally fixed and arranged axially downstream of the unducted fan (5); characterized in that the stator (8) comprises a ring (9) which supports vanes (10, 11) and which jointly surrounds a casing (12) of the speed reducer (6) and the air inlet (7), the ring (9) being fastened to the casing (12) of the speed reducer (6).

Description

[0001] DESCRIPTION

[0002] TITLE: AIRCRAFT TURBOMACHINE COMPRISING AN UNFACED FAN AND AN UNFACED STABLER

[0003] Technical field of the invention

[0004] The present invention relates to an aircraft turbomachine comprising an unfaired fan and an unfaired stator, and to an aircraft comprising such a turbomachine.

[0005] Technical background

[0006] An open-fan turbomachine typically comprises at least one unfaired, movable fan and one unfaired, fixed stator, which together produce the majority of the thrust required to propel the aircraft. The stator is configured to straighten at least a portion of the airflow generated by the unfaired fan.

[0007] Such a high bypass ratio turbomachine has the advantage of excellent efficiency, including reduced fuel consumption and carbon dioxide emissions.

[0008] The blower of such a turbomachine is driven into rotation by a power turbine of a gas generator via a speed reducer, so that the rotational speed of the blower is less than the rotational speed of the power turbine.

[0009] It is known to incorporate an offset mechanism in the speed reducer to offset the rotation axis of the blower relative to that of the gas generator. Such an offset offers several advantages.

[0010] First, it is easier to modularize such a turbomachine since it comprises parts that are offset from each other. This modular design notably facilitates turbomachine maintenance. Second, the upward offset of the fan's rotation axis not only allows for a greater proportion of the fan to be positioned in front of the aircraft's wing but also enables the installation of a larger diameter fan with the same integration of the turbomachine on the aircraft's wing (without altering the landing gear height).

[0011] Thirdly, the offset mechanism offers the opportunity to easily integrate an inverter so as to have so-called "right" motors and so-called "left" motors, and in other words right motors whose blower has a first direction of rotation and left motors whose blower has a second direction of rotation which is opposite to the first direction of rotation.

[0012] Traditionally, the rectifier comprises an annular row of guide vanes also known by the English acronym OGV for "Outlet Guide Vane", the rectifier being directly fixed to the structure of the turbomachine, and more specifically usually to an inlet casing of the turbomachine.

[0013] Engine manufacturers are now seeking to perfect and realize the turbomachine described above, which is currently under development.

[0014] The objective of the present invention is therefore to provide a simple, effective, and economical solution to the aforementioned problem. Prior art also includes documents US2020 / 247528A1, FR3130874A1, and US2021 / 396244A1.

[0015] Summary of the invention

[0016] The invention thus proposes an aircraft turbomachine comprising:

[0017] - a gas generator with longitudinal axis X1 which includes a mobile power turbine rotating around the axis X1;

[0018] - an unfaired blower which is mobile in rotation around a longitudinal axis X2 which is parallel to the axis X1 and radially offset from the axis X1, the blower being driven in rotation by the power turbine via a gear speed reducer which is arranged radially above an air inlet of the gas generator;

[0019] - an unfaired straightener which is fixed in rotation and arranged axially downstream of the unfaired blower;

[0020] characterized in that the rectifier comprises a ring which supports blades and which jointly surrounds a housing of the speed reducer and the air inlet of the gas generator, the ring of the rectifier being fixed to the housing of the speed reducer.

[0021] Such an architecture and such a positioning of the rectifier makes it possible to optimize not only the compactness of the turbomachine but also the mass of the turbomachine.

[0022] This method of attaching the stator ring is particularly advantageous because it reduces the structural forces affecting, in particular, the gearbox housing and the cradle that secures the turbomachine to the aircraft pylon. Indeed, the torque generated by the fan on the gearbox housing is at least partially counteracted by the opposing torque generated by the stator on the gearbox housing. This reduction in structural forces ultimately leads to a reduction in the overall mass of the turbomachine.

[0023] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0024] - the rectifier ring supports at least one variable pitch blade and at least one fixed pitch blade;

[0025] - the variable pitch blade is located on a first portion of the ring which is opposite the speed reducer housing, and the fixed pitch blade is located on a second portion of the ring which is opposite the air inlet;

[0026] - the rectifier ring is fixed to the gearbox housing via at least one clevis fixing, the clevis fixing comprising a clevis integral with the ring and a clevis integral with the gearbox housing, the clevises being linked to each other by a connecting element; - the rectifier ring is fixed to the gearbox housing via at least one connecting rod fixing, the connecting rod fixing comprising a connecting rod which has a first end fixed to the ring and a second end fixed to the gearbox housing;

[0027] - the rectifier ring includes first and second ferrules which are connected to each other by studs supporting the blades;

[0028] - the rectifier ring includes reinforcing elements which each connect the first and second ferrules;

[0029] - the ring is circumferentially divided into several sections which are fixed to each other;

[0030] - the turbomachine includes an electric machine arranged in a compartment above and downstream of the speed reducer, the electric machine being linked in rotation with the speed reducer;

[0031] - the turbomachine includes a lower air stream which is eccentric with respect to the X1 axis, the stream housing a heat exchanger for a cooling circuit.

[0032] The present invention also relates to an aircraft comprising a turbomachine as described above.

[0033] Brief description of the figures

[0034] The invention will be better understood and other details, features and advantages of the invention will become more apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings in which:

[0035] [Fig.1] Figure 1 is a schematic longitudinal cross-sectional view of an aircraft turbomachine according to the invention;

[0036] [Fig.2] Figure 2 is a front view of the turbomachine illustrated in Figure 1; [Fig.3] Figure 3 is a detailed and perspective view of a rectifier of the turbomachine illustrated in Figures 1 and 2;

[0037] [Fig.4] Figure 4 is a detailed front view of the rectifier illustrated in Figure 3;

[0038] [Fig.5] Figure 5 is a detailed top view of the rectifier illustrated in Figures 3 and 4;

[0039] [Fig.6] Figure 6 is another detailed and perspective view of the rectifier illustrated in Figures 3 to 5;

[0040] [Fig.7] Figure 7 is a schematic front view of a rectifier according to one variant embodiment;

[0041] [Fig.8] Figure 8 is a schematic front view of a rectifier ring according to a first example of embodiment;

[0042] [Fig.9] Figure 9 is a schematic front view of a rectifier ring according to a second embodiment.

[0043] Detailed description of the invention

[0044] Figure 1 schematically represents a turbomachine 1 for an aircraft 2, such as an airplane.

[0045] Aircraft turbomachine 1 comprises:

[0046] - a gas generator 3 with longitudinal axis X1 which includes a power turbine 4 mobile in rotation around the axis X1;

[0047] - an unfaired blower 5 which is mobile in rotation about a longitudinal axis X2 which is parallel to the axis X1 and radially offset with respect to the axis X1, the blower 5 being driven in rotation by the power turbine 4 via a gear speed reducer 6 which is arranged radially above an air inlet 7 of the gas generator 3;

[0048] - an unfaired straightener 8 which is fixed in rotation and arranged axially downstream of the unfaired blower 5.

[0049] According to the invention, the rectifier 8 comprises a ring 9 which supports blades 10, 11 and which jointly surrounds a housing 12 of the speed reducer 6 and the air inlet 7 of the gas generator 3. The ring 9 of the rectifier 8 is fixed to the housing 12 of the speed reducer 6.

[0050] Such an architecture and such a positioning of the rectifier 8 makes it possible to optimize not only the compactness of the turbomachine 1 but also the mass of the turbomachine 1.

[0051] Such a fixing of the ring 9 of the rectifier 8 proves particularly advantageous because it reduces the intensity of the design forces, notably on the housing 12 of the speed reducer 6 and the cradle that secures the turbomachine 1 to the aircraft pylon 2. Indeed, the torque generated by the fan 5 on the housing 12 of the speed reducer 6 is at least partially countered by the opposing (or inverse) torque generated by the rectifier 8 on the housing 12 of the speed reducer 6. This reduction in design forces generally reduces the mass of the turbomachine 1.

[0052] The turbomachine 1 illustrated in Figure 1 is better known by the English acronym USF for "Unducted Single Fan" since it comprises a single unshod fan 5, the fan 5 being driven in rotation by the power turbine 4 of the gas generator 3.

[0053] As illustrated in Figure 1, the gas generator 3 includes, from upstream to downstream following the flow of the gases, an air inlet 7 (air intake or air scoop), a low pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a power turbine 4 (or low pressure turbine), and an exhaust nozzle 17.

[0054] The gas generator 3 is defined along the longitudinal axis X1 which corresponds in particular to the axis of rotation of the compressors 13, 14 and the turbines 4, 16.

[0055] As illustrated in Figure 1, the turbomachine 1 comprises a fixed structure 20 which includes various housings, notably an inlet housing 21, an intermediate housing 22, an inter-turbine housing 23, and an exhaust housing 24. As illustrated in Figure 1, the unshod fan 5 is rotatable about the axis X2, which is parallel to the axis X1 and radially offset upwards with respect to the axis X1. This offset of the fan 5 renders the turbomachine 1 asymmetrical, being symmetrical only about a longitudinal-vertical median plane. The unshod fan 5 includes a shaft 25 carrying an annular row of variable-pitch blades 26, each blade 26 being calibrated about an axis of rotation Y2 which is substantially perpendicular to the axis X2. The blower 5 includes a blade pitch adjustment system 27 26 better known by the English acronym PGM for "Pitch Change Mechanism".The adjustment system 27 can be common to all the blades 26 or specific to each of the blades 26. According to one embodiment, the adjustment system 27 comprises an actuator common to all the blades 26 (for example a hydraulic actuator) and a mechanism specific to each of the blades 26, this mechanism allowing the movement initiated by the actuator to be transformed into a rotational movement of the corresponding blade 26.

[0056] The blower 5 is driven in rotation by the power turbine 4 via the gear speed reducer 6. The speed reducer 6 allows the rotational speed of the blower 5 to be reduced relative to that of the power turbine 4.

[0057] More specifically, the speed reducer 6 includes a movable input shaft rotating about the axis X1 which is rotationally linked with a low pressure shaft 19 and a movable output shaft rotating about the axis X2 which is rotationally linked with the blower shaft 25.

[0058] The reduction gear 6 includes an offset mechanism 28 and an epicyclic gear train 29. The offset mechanism 28 shifts the axis of rotation while forming a first reduction stage. The epicyclic gear train 29 includes at least one sun gear (or planet gear), a ring gear, satellites, and a planet carrier. The epicyclic gear train 29 can be configured in various ways, including a first configuration commonly called "epicyclic" and a second configuration commonly called "planetary."

[0059] In the "planetary" configuration, the solar element is the input element of the epicyclic gear train 29, the ring gear is the output element which is rotationally linked to the fan shaft 25, and the planet carrier is fixed. In the "epicyclic" configuration, the solar element is the input element of the epicyclic gear train 29, the ring gear is fixed, and the planet carrier is the output element which is rotationally linked to the fan shaft 25.

[0060] The two configurations described above are by no means limiting; other configurations are obviously possible depending in particular on the desired reduction ratio.

[0061] The gearbox housing 12 of the speed reducer 6 is connected to the input housing 21 and structurally to the cradle which connects the turbomachine 1 to the aircraft pylon 2. The fan shaft 25 is guided in rotation relative to a cover 30 of the gearbox housing 12 of the reducer 6 via one or more roller bearings 31.

[0062] An inverter can be integrated into the shifting mechanism 28 so as to have so-called "right" motors and so-called "left" motors, without impacting the overall architecture of the turbomachine 1.

[0063] In "propulsion" mode, the fan 5 generates an airflow F which flows upstream to downstream around the fairings of the nacelle 32 of the turbomachine 1. The airflow F generated by the fan 5 is straightened by the straightener 8 in order to generate most of the thrust which propels the aircraft 2. Part of the airflow F is captured by the air inlet 7 to supply the gas generator 3. The air inlet 7 is located radially below the speed reducer 6.

[0064] More specifically, as illustrated in the figures, the air inlet 7 is located at 6 o'clock with reference to the face of a clock. The air inlet 7 is oblong and curved. Alternatively, the air inlet 7 could be bilobed and distributed on either side of the 6 o'clock position. The air inlet 7 is part of an air inlet housing 33 (or air inlet sleeve) which includes, downstream, an upper outlet 34 that feeds the annular stream of the gas generator 3 and a lower outlet 35 that expels or evacuates the particles entering through the air inlet 7. By convention in this application, the terms "upstream" and "downstream" are defined with respect to the direction of airflow F when the turbomachine 1 is in "propeller" mode.

[0065] The unfaired straightener 8 is fixed in rotation and arranged axially downstream of the unfaired blower 5. The straightener 8 allows to straighten at least part of the air flow F generated by the blower 5.

[0066] As indicated above, according to the invention, the rectifier 8 comprises a ring 9 which supports blades 10, 11 and which jointly surrounds the housing 12 of the speed reducer 6 and the air inlet 7 of the gas generator 3. The ring 9 of the rectifier 8 is fixed to the housing 12 of the speed reducer 6.

[0067] Ring 9 of the rectifier 8 can only support variable pitch blades 10 or fixed pitch blades 11.

[0068] Alternatively, as illustrated in the figures, the ring 9 of the rectifier 8 can support at least one variable pitch blade 10 and at least one fixed pitch blade 11. In this case, the variable pitch blade 10 can be located on a first portion 36 of the ring 9 which is opposite (at the level or facing) the housing 12 of the speed reducer 6, and the fixed pitch blade 11 can be located on a second portion 37 of the ring 9 which is opposite (at the level or facing) the air inlet 7.

[0069] The blades 10, 11 of the rectifier 8 can have different dimensional and geometric characteristics depending on their angular position on the ring 9.

[0070] The general shape of the ring 9 can vary depending in particular on the size of the speed reducer 6 and the air inlet 7, but also on the need or not to install variable pitch blades 10, or even on the required stiffness or mechanical strength. The ring 9 can thus, for example, have a general shape that is circular, rectangular, trapezoidal, oblong, or elliptical.

[0071] Advantageously, ring 9 of rectifier 8 is symmetrical along a longitudinal-vertical median plane.

[0072] The area defined (or covered) by the rectifier 8 is at least partly included or included in the area defined (or swept) by the blower 5. The area defined by the rectifier 8 can obviously be totally included in the area defined by the blower 5.

[0073] The ring 9 of the rectifier 8 can be fixed to the housing 12 of the speed reducer 6 via at least one clevis fixing 38. The clevis fixing 38 comprises a clevis 39 integral with the ring 9 and a clevis 40 integral with the housing 12 of the speed reducer 6, the clevises 39, 40 being linked to each other by a connecting element 41.

[0074] The ring 9 of the rectifier 8 can be fixed to the housing 12 of the speed reducer 6 via at least one connecting rod attachment 42. The connecting rod attachment 42 comprises a connecting rod 43 which has a first end 44 fixed to the ring 9 and a second end 45 fixed to the housing 12 of the speed reducer 6.

[0075] The ring 9 of the rectifier 8 may include first and second ferrules 46a, 46b, 59a, 59b which are connected to each other by studs 47 (or platforms) supporting the blades 10, 11. The first and second ferrules 46a, 46b of the ring 9 may be axially offset from each other. The first and second ferrules 59a, 59b of the ring 9 may be radially offset from each other. The first and second ferrules of the ring 9 could be both axially and radially offset from each other.

[0076] Ring 9 can be perforated at various points to minimize its mass. Ring 9 of the rectifier 8 can include reinforcing elements 48 which each connect the first and second ferrules 46a, 46b, 59a, 59b.

[0077] The reinforcing elements 48 can be interwoven to strengthen the structure of the ring 9. The first and second ferrules 46a, 46b, 59a, 59b of the rectifier 8 can be connected locally or totally by a core or a veil.

[0078] The ring 9 of the rectifier 8 can be circumferentially (or angularly) divided into several sections 49a, 49b (sectors or parts) which are fixed to each other.

[0079] The turbomachine 1 may include an electric machine 50 disposed in an upper compartment 51 and downstream of the speed reducer 6, the electric machine 50 being rotationally linked with the speed reducer 6. Such an electric machine 50 may be used to propel the blower 5, so as to complement the gas generator 3.

[0080] Such an implantation of the electric machine 50 is possible because of the architecture of the turbomachine 1, and in particular the positioning of the local air inlet 7 under the speed reducer 6 (and not an annular air inlet), the radial offset of the blower 5, and the positioning of the heat exchanger(s) 52 under the gas generator 3.

[0081] Such an installation of the electric machine 50 allows for shorter electrical harnesses, placement of the electric machine 50 in a cold environment and does not negatively impact the position of the center of gravity of the turbomachine 1.

[0082] Turbomachine 1 can obviously include several electrical machines.

[0083] The electrical machine(s) can be directly attached to a downstream face of the speed reducer 6.

[0084] Compartment 51 can be used to house other equipment for turbomachine 1.

[0085] The turbomachine 1 may include a lower air stream 53 which is eccentric with respect to the axis X1, the stream 53 housing a heat exchanger 52 of a cooling circuit.

[0086] The cooling circuit can be used for example to cool the lubricating oil of the turbomachine 1 and / or the electrical machine(s). According to the embodiments illustrated in the figures, the ring 9 of the rectifier 8 supports variable pitch vanes 10 and fixed pitch vanes 11, these vanes 10, 11 being known by the English acronym OGV for "Outlet Guide Vane".

[0087] More specifically, the ring 9 comprises a first portion 36 which is opposite and at a distance from the housing 12 of the speed reducer 6, and a second portion 37 which is opposite and in the immediate vicinity (or in contact) of the air inlet 7.

[0088] The variable pitch blade 10 or the variable pitch blades 10 are located on the first portion 36 of the ring 9, and the fixed pitch blade 11 or the fixed pitch blades 11 are located on the second portion 37 of the ring 9. Having only fixed pitch blades 11 under the air inlet 7 reduces the radial bulk under the air inlet 7 and thus limits drag, but also reduces mass and simplifies maintenance.

[0089] The fixed pitch blade setting 11 is chosen to achieve the best compromise between performance and acoustics.

[0090] The variable-pitch blades 10 are each calibrated around a rotation axis Y2' which is substantially perpendicular to the axis X2. The straightener 8 includes a system for adjusting the pitch of the variable-pitch blades 10. The adjustment system may be common to all the blades 10 or specific to each individual blade 10.

[0091] According to one embodiment, the adjustment system includes an actuator common to all the blades 10 (for example a hydraulic actuator) and a mechanism specific to each of the blades 10, this mechanism allowing the movement initiated by the actuator to be transformed into a rotational movement of the corresponding blade 10.

[0092] The variable-pitch blades 10 and the fixed-pitch blades 11 have different dimensional and geometric characteristics. The fixed-pitch blades 11, for example, are truncated to accommodate the air inlet 7. According to the embodiment illustrated in Figures 1 to 6, the ring 9 of the stator 8 is generally rectangular or trapezoidal in shape. The ring 9 of the stator 8 is symmetrical about a longitudinal-vertical median plane. According to the variant illustrated in Figure 7, the ring 9 is generally bilobed in shape and comprises an upper lobe (or bulb) 54a and a lower lobe 54b superimposed on one another, the lobes 54a and 54b being laterally connected by concave cheeks 55 (or sides). A ring 9 of general bilobed shape allows for an annular row of variable pitch blades 10, and thus promotes the pitching of the variable pitch blades 10 located in the concave cheeks 55.Indeed, these variable pitch blades 10 thus present, like the other variable pitch blades located on other areas, an axis that is generally perpendicular to the said concave cheek 55.

[0093] As illustrated in Figures 3 to 6, the ring 9 is fixed transversely to the housing 12 of the speed reducer 6 via two clevis brackets 38 positioned angularly, preferably but not exclusively, at approximately 10 o'clock and approximately 2 o'clock relative to a clock face. The two clevis brackets 38 resist the torsional torque. Each clevis bracket 38 comprises a yoke 39 integral with the ring 9 and a yoke 40 integral with the housing 12 of the speed reducer 6, the yokes 39 and 40 being connected to each other by a connecting element 41. The yokes 39 and 40 are oriented in a transverse-vertical plane. The connecting element 41 of the fixing 38 at approximately 10 o'clock comprises two attachment points, namely an attachment point with the clevis 39 of the ring 9 and an attachment point with the clevis 40 of the housing 12 of the reducer 6.The connecting element 41 of the fastener 38 at approximately 2 o'clock comprises three attachment points: one attachment point with the yoke 39 of the ring 9 and two attachment points with the yoke 40 of the housing 12 of the gearbox 6. These two fasteners 38 can be located at different time positions and interchanged according to the mechanical strength requirements during the optimization of the turbomachine. The ring 9 is also longitudinally fixed to the housing 12 of the gearbox 6 via a connecting rod 42 positioned angularly at 12 o'clock relative to a clock face. The connecting rod 42 allows for the absorption of axial forces. The connecting rod 42 comprises a connecting rod 43 which has a first end 44 fixed to the ring 9 and a second end 45 fixed to the housing 12 of the gearbox 6. The connecting rod 43 is oriented in a longitudinal-vertical plane.The connecting rod 43 extends radially from the outside in from its first end 44 to its second end 45. The first end 44 of the connecting rod 43 is fixed to a yoke 56 of the ring 9 and the second end 45 of the connecting rod 43 is fixed to a yoke 57 of the housing 12 of the reducer 6. Depending on the position of the ring 9, the connecting rod 43 will have a greater or lesser angle with respect to the motor axis.

[0094] According to the embodiments illustrated in the figures, the ring 9 of the rectifier 8 comprises first and second concentric ferrules 46a, 46b, 59a, 59b which are spaced apart and connected to each other by studs 47 supporting the blades 10, 11. According to the embodiment illustrated in Figures 1 to 6, the first and second ferrules 46a, 46b are axially offset from each other, with the second ferrule 46b located downstream of the first ferrule 46a. According to the embodiment examples illustrated in Figures 8 and 9, the first and second ferrules 59a, 59b are radially offset from each other, with the second ferrule 59b located outside the first ferrule 59a.

[0095] Each pad 47 associated with a variable pitch blade 10 includes an orifice in which the foot of the blade 10 is guided via one or more bearings.

[0096] Each pad 47 associated with a fixed-position blade 11 receives the inner end of the blade 11.

[0097] According to the embodiment illustrated in Figure 9, the ring 9 of the straightener 8 comprises oblique reinforcing beams 48, each connecting the ferrules 59a, 59b, so as to form a truss structure. According to the embodiments illustrated in Figures 8 and 9, the ring 9 of the straightener 8 is circumferentially divided into an upper section 49a and a lower section 49b. The upper and lower sections 49a, 49b are fixed to each other via coplanar fastening interfaces 58, which are located radially just above the air inlet 7. This positioning of the fastening interfaces 58 allows the ring 9 of the straightener 8 to be disassembled without having to remove the air inlet 7.

[0098] As illustrated in Figure 1, the turbomachine 1 comprises an electric machine 50 arranged in an upper compartment 51 and downstream of the speed reducer 6. The electric machine 50 is rotationally linked with the speed reducer 6.

[0099] The electric machine 50 participates here in the electrical hybridization of the turbomachine 1. The electric machine 50 is used to propel the blower 5, so as to complement the gas generator 3.

[0100] The upper compartment 51 is radially delimited by the gas generator 3 and the fairings of the nacelle 32.

[0101] As illustrated in Figure 1, the turbomachine 1 includes a lower air stream 53 which is eccentric with respect to the axis X1, the stream 53 housing a heat exchanger 52 of a cooling circuit.

[0102] The lower vein 53 is supplied with air by an air intake which is arranged axially downstream of the straightener 8.

Claims

DEMANDS 1. Aircraft turbomachine (1) (2) comprising: - a gas generator (3) with a longitudinal axis (X1) which includes a power turbine (4) that is mobile and rotates around the axis (X1); - an unfaired blower (5) which is mobile in rotation around a longitudinal axis (X2) which is parallel to the axis (X1) and radially offset with respect to the axis (X1), the blower (5) being driven in rotation by the power turbine (4) via a gear speed reducer (6) which is arranged radially above an air inlet (7) of the gas generator (3); - an unfaired straightener (8) which is fixed in rotation and arranged axially downstream of the unfaired blower (5); characterized in that the rectifier (8) comprises a ring (9) which supports blades (10, 11) and which jointly surrounds a housing (12) of the speed reducer (6) and the air inlet (7) of the gas generator (3), the ring (9) of the rectifier (8) being fixed to the housing (12) of the speed reducer (6).

2. Turbomachine (1) according to claim 1, characterized in that the ring (9) of the rectifier (8) supports at least one variable pitch blade (10) and at least one fixed pitch blade (11).

3. Turbomachine (1) according to the preceding claim, characterized in that the variable pitch blade (10) is located on a first portion (36) of the ring (9) which is opposite the housing (12) of the speed reducer (6), and the fixed pitch blade (11) is located on a second portion (37) of the ring (9) which is opposite the air inlet (7).

4. Turbomachine (1) according to any one of the preceding claims, characterized in that the ring (9) of the rectifier (8) is fixed to the housing (12) of the speed reducer (6) via at least one clevis fixing (38), the clevis fixing (38) comprising a clevis (39) integral with the ring (9) and a clevis (40) integral with the housing (12) of the speed reducer (6), the clevises (39, 40) being linked to each other by a connecting element (41).

5. Turbomachine (1) according to any one of the preceding claims, characterized in that the ring (9) of the rectifier (8) is fixed to the housing (12) of the speed reducer (6) via at least one connecting rod attachment (42), the connecting rod attachment (42) comprising a connecting rod (43) which has a first end (44) fixed to the ring (9) and a second end (45) fixed to the housing (12) of the speed reducer (6).

6. Turbomachine (1) according to any one of the preceding claims, characterized in that the ring (9) of the rectifier (8) comprises first and second ferrules (46a, 46b, 59a, 59b) which are connected to each other by studs (47) supporting the blades (10, 11).

7. Turbomachine (1) according to the preceding claim, characterized in that the ring (9) of the straightener (8) comprises reinforcing elements (48) which each connect the first and second ferrules (59a, 59b).

8. Turbomachine (1) according to any one of the preceding claims, characterized in that the ring (9) is circumferentially divided into several sections (49a, 49b) which are fixed to each other.

9. Turbomachine (1) according to any one of the preceding claims, characterized in that the turbomachine (1) comprises an electric machine (50) disposed in an upper compartment (51) and downstream of the speed reducer (6), the electric machine (50) being rotationally linked with the speed reducer (6).

10. Turbomachine (1) according to any one of the preceding claims, characterized in that the turbomachine (1) comprises a lower air duct (53) which is eccentric with respect to the axis (X1), the duct (53) housing a heat exchanger (52) of a cooling circuit.

11. Aircraft (2) comprising a turbomachine (1) according to one of the preceding claims.

Images