Turbomachine module provided with a propeller and biased stator vanes

Abstract

The invention relates to a turbomachine module having a longitudinal axis X, comprising an unducted propeller (2) rotating about the longitudinal axis X by means of a power shaft (9, 10) connected at least to a compressor rotor (5), and at least one straightener (25) comprising a plurality of stator vanes extending from a fixed casing along a radial axis Z perpendicular to the longitudinal axis X, the straightener being arranged downstream of the propeller. According to the invention, the fixed casing is an inter-compressor casing (30) arranged along the longitudinal axis downstream of the low-pressure compressor, the inter-compressor casing (30) comprising a ring (31) having a longitudinal axis, the ring being provided with sleeves (37) for supporting the stator vanes (26), the inter-compressor casing (30) and the ring (31) being monolithic.

Description

TECHNICAL FIELD

[0001] The present invention relates to the field of turbomachines, in particular to a turbomachine module comprising an unducted propeller and stator vanes with variable pitch. The invention also applies to corresponding turbomachines. BACKGROUND

[0002] The technical background is described in document US-A1-2018105278.

[0003] Turbomachines comprising at least one unducted propeller are called "open rotor" or "ducted fan". Among this type of turbomachines, there are turbomachines with two unducted and counter-rotating propellers (called Unducted Dual Fan, UDF), or turbomachines with a single unducted propeller and a straightener comprising a plurality of stator vanes (called Unducted Single Fan, USF). The propeller(s) forming the propulsion section can be arranged at the rear of the gas generator (or engine) so that the gas generator is of the propeller type, or at the front of the gas generator so that the gas generator is of the tractor type. These turbomachines are turboprop engines, which differ from turbojet engines in that they use a propeller (unducted) outside the nacelle, instead of an internal fan. This makes it possible to increase the bypass ratio very significantly, without being affected by the mass of the casing or nacelle intended to surround the blades of the propeller or fan.

[0004] Currently, turbomachines of this type, in particular USF turbomachines, generate considerable noise. This noise is caused by the gas generator, but mainly by the interaction of the wake and the vortices generated by the flow lines of the top of the propeller vanes and the straightener vanes. The closer the stator vanes are to the vanes of the propeller, the greater the noise. In practice, the stator vanes of the turbomachine are usually mounted on an intake casing which carries the splitter nose of the primary flow and the secondary flow which circulate respectively in the main duct and around the intake casing. In the case of a turbofan engine with a fan, although the stator vanes are close to the vanes of the fan to limit the elongation of the fan fairing and the influence of its drag, the fairing of the fan makes it possible to install soundproofing panels to reduce the noise. SUMMARY

[0005] The aim of the present invention is to provide a turbomachine module with stator vanes arranged to reduce the acoustic impact of an unducted turbomachine, while avoiding significant structural modifications.

[0006] According to the invention, this is achieved by means of a turbomachine module having a longitudinal axis X, comprising an unducted propeller, the propeller being driven in rotation about the longitudinal axis X by a power shaft, the power shaft being connected to at least one compressor rotor, and at least one straightener, the straightener comprising a plurality of stator vanes extending from a fixed casing along a radial axis Z perpendicular to the longitudinal axis X, the straightener being arranged downstream of the propeller, the fixed casing being an intercompressor casing arranged along said longitudinal axis downstream of the low-pressure compressor, the intercompressor casing comprising an annulus having a longitudinal axis, the annulus being provided with a sleeve for carrying the stator vanes, the intercompressor casing and the annulus being monolithic.

[0007] This solution thus makes it possible to achieve the objectives mentioned above. In particular, by mounting the stator vanes of the straightener on the intercompressor casing, the distance between the vanes of the propeller and the stator vanes is lengthened, which makes it possible to reduce the noise. The fact that the stator vanes are offset or axially moved also makes it possible to displace the center of gravity of the turbomachine, which rebalances the assembly and facilitates the restitution of forces. Indeed, the ring gear of the straightener vanes weighs around 200 kg. The center of gravity is closer to the hooking system on the aircraft. Such a configuration also makes it possible to free up space in this confined environment for the installation of other components or elements.

[0008] The module also comprises one or more of the following features, taken individually or in combination:

[0009] - the inner casing and the intake casing at least partially delimit a main duct in which the main airflow circulates.

[0010] - the intercompressor casing comprises a radial inner casing and a radial outer casing, coaxial with the longitudinal axis X, and at least one radial structural arm extends between the radial inner casing and the radial outer casing.

[0011] - the intercompressor casing comprises a radial annular wall extending radially from a first side of the annulus, and connected to the radial outer casing of the intercompressor casing.

[0012] - the stator vanes have variable pitch, and the module comprises a pitch variation system for varying the pitch of the blades of the stator vanes.

[0013] - the stator vanes of the straightener are unducted.

[0014] - at least one rotational guide bearing of the stator vane root is housed in a housing of the sleeve.

[0015] - the stator vanes are uniformly distributed about the longitudinal axis X and extend radially into the secondary airflow.

[0016] - the intercompressor casing is produced by an additive manufacturing method.

[0017] - the inter-compressor casing and the ring are manufactured integrally.

[0018] - the inter-compressor casing and the ring are assembled together by welding.

[0019] - the ratio S / C between the distance S between the trailing edge of the propeller blades and the leading edge of the stator blades and the chord C of the propeller blades is 3.

[0020] - the pitch change system comprises at least one control device comprising a fixed body and a body that can move axially relative to the fixed body, and a connection mechanism connecting each stator blade to the movable body of the control device.

[0021] - the control device of the pitch change system is mounted in the intake casing between the splitter nose for separating the intake flow of the turbomachine into a primary flow and a secondary flow and the inter-compressor casing.

[0022] - the control device of the pitch change system is mounted in the intake casing upstream of the inter-compressor casing.

[0023] - the control device of the pitch change system is mounted in the inter-bypass casing extending downstream from the intake casing carrying a splitter nose for separating the intake flow of the turbomachine into a primary flow and a secondary flow, the control device being located downstream of the sleeve and downstream of a radial wall of the inter-compressor casing connecting the ring to the radial outer casing.

[0024] - the control device is intended to be located radially above the high-pressure compressor.

[0025] The application also relates to a turbomachine of an aircraft comprising at least one module as described above and a gas generator for driving the rotation of the unducted propeller. BRIEF DESCRIPTION OF DRAWINGS

[0026] The application will be better understood and other objects, details, features, and advantages of the application will become more apparent from reading the detailed description of an embodiment of the application, given purely by way of illustrative and non-limiting example, to be read with reference to the accompanying drawings in which:

[0027] [ Figure 1 ] Figure 1 is an axial and partial cross-sectional view of an example of a turbomachine with a single unducted propeller to which the application applies;

[0028] [ Figure 2 ] Figure 2 is a perspective view of an inter-compressor casing for carrying the stator blades;

[0029] [Figure 3 ] Figure 3 A perspective view showing a pitch changing system for changing the pitch of blades of a stator vane of a turbine having a single unducted propeller to which the present invention is applied; and

[0030] [ Figure 4 ] Figure 4 Another embodiment of a turbine stator blade root is shown in axial and partial cross section, which is mounted in a compressor inter-housing and cooperates with a pitch variation system according to the invention. DETAILED DESCRIPTION

[0031] The present invention is applicable to a turbomachine 1 comprising an unducted propeller 2 for installation on an aircraft. Figure 1 A turboprop engine is shown. As mentioned above, this type of turbine is called an "open rotor" or "unducted fan."

[0032] In the present invention, the terms "upstream", "downstream", "axial" and "axially" are generally used with respect to the flow of gas in the turbine and here along the longitudinal axis X (even in the Figure 1 Similarly, the terms "radial," "inner," and "outer" are defined relative to a radial axis Z perpendicular to the longitudinal axis X and relative to a distance from the longitudinal axis X. Furthermore, identical or substantially identical elements and / or elements having identical functions are denoted by identical reference numerals.

[0033] To facilitate their manufacture and assembly, turbines are typically modular, meaning they consist of multiple modules that are manufactured independently and then assembled together. Turbine modularity also facilitates turbine maintenance. In this application, a "turbine module" refers to a module that specifically includes the fan and its power shaft, which drives the propeller.

[0034] Turbine 1 includes a gas generator or engine 3, which generally comprises, from upstream to downstream, a low-pressure compressor 4, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7, and a low-pressure turbine 8. The low-pressure compressor 4 and low-pressure turbine 8 are mechanically connected by a low-pressure shaft 9 to form the low-pressure main body. The high-pressure compressor 5 and high-pressure turbine 7 are mechanically connected by a high-pressure shaft 10 to form the high-pressure main body. The high-pressure shaft 10 extends inside the low-pressure shaft 9, and the high-pressure and low-pressure shafts are coaxial.

[0035] In another configuration, not shown, the low-pressure body comprises a low-pressure compressor connected to an intermediate-pressure turbine. A free power turbine is installed downstream of the intermediate-pressure turbine and is connected to a propeller as described below via a power transmission shaft to drive the propeller in rotation.

[0036] The turbomachine comprises a rotating casing 11 centered on a longitudinal axis X and rotating around the longitudinal axis X. The rotating casing 11 carries an annular gear forming movable blades 12 of an unducted propeller 2. The rotating casing 11 is movably mounted with respect to an inner casing 13 extending downstream of the rotating casing 11. In Figure 1 In the example shown, the propeller 2 is mounted upstream of the gas generator 3 (tractor configuration).

[0037] The gas flow F entering the turbomachine passes through the blades 12 of the propeller and is divided by a splitter nose 14 to form a primary gas flow Fl and a secondary gas flow F2. The splitter nose 14 is supported by an intake casing 15 centered on the longitudinal axis. The intake casing 15 extends downstream by means of an outer casing or interduct casing 16. The intake casing 15 is coaxial with the inner casing 13. Furthermore, the intake casing 15 extends radially outward from the inner casing 13.

[0038] The primary gas flow Fl circulates in a primary duct 17 by means of the gas generator 3. In particular, the primary gas flow Fl enters the gas generator 3 by means of an annular air inlet 18 and exits by means of a primary nozzle 19 provided downstream of the gas generator 3. The primary duct 17 is radially delimited by a radial inner wall 20 and a radial outer wall 21. The radial inner wall 20 is carried by the inner casing 13. The radial outer wall 21 is at least partially carried by the intake casing 15. For the secondary flow F2, the secondary flow circulates around the intake casing 15.

[0039] Each blade 12 of the propeller 2 comprises axially opposite leading and trailing edges 22a, 22b. The blade also comprises a root 23 from which the blade extends radially outward.

[0040] The power shaft or low-pressure shaft 9 (power shaft or low-pressure shaft of the free power turbine and low-pressure turbine, respectively) drives the propeller 2 by means of a reduction gear 24 which compresses the air outside the rotating casing 11 and the intake casing 15 and provides most of the thrust. The reduction gear 24 can be of the planetary or epicyclic type.

[0041] As in the case of the free power turbine, the low-pressure turbine is driven by the low-pressure shaft 9. The low-pressure turbine is mounted upstream of the free power turbine. Figure 1As seen in the figures, the turbomachine 1 comprises a straightener 25 comprising a plurality of stator vanes 26 (or fixed vanes), known as Outlet Guide Vanes (OGV for short). The stator vanes 26 are uniformly distributed around the longitudinal axis X and extend radially into the secondary airflow. There are six to eight stator vanes 26 around the intake casing and the inter-bypass casing. Of course, there can be a greater number of stator vanes around the longitudinal axis X. There can be six to fourteen stator vanes 26 distributed around the longitudinal axis. The stator vanes 26 of the straightener 25 are disposed downstream of the propeller 2, to straighten the airflow generated by the propeller 2. Each stator vane 26 comprises a blade 27 extending radially from a root 28. It will be understood that, as shown, Figure 1 The stator vanes 26 of the straightener are unshrouded, as shown. The turbomachine shown is a USF, without propeller and without fairing of the straightener. The blade 27 also comprises an axially opposite leading edge 29a and trailing edge 29b. The stator vanes 26 also extend radially outwards from the inter-bypass casing.

[0042] The stator vanes 26 are mounted on a fixed casing of the turbomachine. In particular, the stator vanes 26 are mounted on an inter-compressor casing 30 forming the fixed casing. The inter-compressor casing 30 is arranged downstream of the low-pressure compressor 4. More particularly, the inter-compressor casing 30 extends axially between the low-pressure compressor 4 and the high-pressure compressor 5.

[0043] With reference to Figure 2 , the stator vanes 26 are carried by an annular piece 31 having a longitudinal axis X. In the case of a circular annular piece, the longitudinal axis X is the axis of revolution of the annular piece. In the case of a polygonal annulus, the longitudinal axis is the centre of the polygon. The annular piece 31 is integral with the inter-compressor casing 30. In particular, the annular piece 31 and the inter-compressor casing 30 are integrally made in one piece (monolithic piece). Alternatively, the annular piece and the inter-compressor casing are manufactured separately (for example by casting or a plurality of welded castings), then assembled together by welding.

[0044] Advantageously, in the case where the inter-compressor casing 30 is integral with the annular piece 31, the inter-compressor casing 30 (and the annular piece 31) is manufactured by an additive manufacturing method.

[0045] In Figure 2In particular, the inter-compressor casing 30 comprises a radially inner shell 32 and a radially outer shell 33 centered on the longitudinal axis X. At least one structural radial arm 34 extends radially between the radially inner collar 32 and the radially outer shell 33. In particular, a plurality of radial arms 34 are attached to the radially inner shell 32 and to the radially outer shell 33. The radial arms 34 are also uniformly distributed around the longitudinal axis X. There are between 6 and 10 radial arms to optimize the mechanical strength of the inter-compressor casing 30. These arms 34 are fixed and integral with the inner shell 32 and the outer shell 33. The number of stator vanes 26, for example between 6 and 10, facilitates the integration of the stator vanes on the inter-compressor casing 30.

[0046] The radially inner shell 32 and the radially outer shell 33 constitute sections of the radially inner wall 20 and of the radially outer wall 21 of the main duct 17. The main flow passes through the radial arms 34.

[0047] The annular piece 31 extends radially outward from the radially outer shell 33. A radial wall 35 (see Figure 3 and Figure 4 ) extending radially from a first side 36a of the annular piece 31 is connected to the radially outer shell 33 of the inter-compressor casing 30. The wall 35 is annular, centered on the axis X, and advantageously solid. This wall 35 is substantially defined in a plane P Figure 3 ) perpendicular to the longitudinal axis X. This plane P can be slightly inclined from the radial axis Z by about 10°. The annular piece 31 comprises a plurality of radially outwardly extending cylindrical sleeves 37. The bottom of each sleeve 37 is circular.

[0048] With reference to Figure 2 and Figure 3 , the sleeves 37 are uniformly distributed around the longitudinal axis X. In particular, the sleeves 37 extend axially from a second side 36b of the annular piece 31. The second side 36b (see Figure 2 ) is axially opposite the first side 36a. Advantageously, but not restrictively, the second side 36b is about two-thirds of the radial height H measured between a first boundary 38a of the sleeve 37 and a second boundary 38b of the sleeve 37 for each sleeve 37. Each sleeve 37 comprises a cylindrical skirt 39, the axis A of which is parallel to the radial axis Z. The cylindrical skirt 39 is delimited by the first boundary 38a and the second boundary 38b. The axis A of the sleeve 37 is defined in a radial plane axially offset from the plane P of the radial wall 35. The sleeve 37 is advantageously radially arranged above the structural radial arms 34 (and taking into account Figure 2 and Figure 3 ), thus enabling to reinforce the mechanical strength of the sleeve 37.

[0049] Each sleeve 37 comprises a bore 40 passing through the cylindrical skirt 39 on both sides along the axis. The bore 40 forms an internal accommodation for receiving the root of a stator vane 26.

[0050] With such a configuration, the ratio S / C of the distance S between the trailing edge 22b of the blade of the propeller 2 and the leading edge 29a of the stator blade 26 to the chord C of the blade of the propeller 2 is improved. This ratio S / C is about 3, whereas in the prior art it is between 1 and 2. The minimum ratio to meet the noise standards is 1.

[0051] With reference to Figure 3 , the pitch of the stator blades 26 is advantageously variable to optimize the performance of the turbine. To this end, the turbine 1 comprises a pitch variation system 45 for varying the pitch of the blades of the stator blades 26. It can be seen that the root 28 of each blade 26 is generally in the form of a pivot 41 pivoted in the housing along an axis B. The axes A and B are coaxial. The pivot 41 of the root is pivoted in the housing of each sleeve 37 by means of at least one guide bearing 42. In the present example, two guide bearings 42, 42' are superimposed along the radial axis Z. These bearings 42, 42 are preferably, but not limitatively, rolling bearings. Due to the space available in the sleeve 37 and the position of the inter-compressor casing 30, the diameter of the bearings can be greater than usual.

[0052] Each bearing 42, 42' comprises an inner ring 43 fixed in rotation to the pivot and an outer ring 44 surrounding the inner ring 42. The rolling elements comprise rolling members 46 mounted between the inner surfaces of the inner and outer rings forming raceways. Here the rolling members 46 comprise balls. The bearings 42, 42' advantageously ensure that the blades 26 remain in the housing of the sleeves 37.

[0053] A cylindrical sleeve 48 is mounted in each hole 40 to connect the inner ring 43 of each bearing 42, 42' to the root of each stator blade 26. The sleeve 48 is centered on the pitch axis B of the stator blades. Each sleeve 48 extends between a first end and a second end. Each sleeve 48 is also provided with an internal spline 49 arranged on an inner cylindrical face. The internal spline 49 is intended to cooperate with an external spline provided on the outer surface of the pivot 41 of each root of the stator blades 26. Between each bearing 42, 42', a spacer 50 extends along the radial axis Z to ensure the spacing between the bearings 42, 42' since these must absorb forces and torques. It is therefore necessary to space the two bearings to ensure that the bending torques can be absorbed. This spacer 50 is advantageously, but not limitatively, arranged between the two inner rings of the bearings 42, 42'. A sealing element is provided in each hole 40 to prevent the lubricant from leaking to the outside. From Figure 3It can also be seen that two collars are arranged between the inner wall of each sleeve 37 and the lateral sides of the bearings 42, 42'. The first collar 51 has an L-shaped axial cross-section, with a branch that radially overlaps the (radially) bearing 42', and the second collar 54 has an I-shaped axial cross-section (in the form of a capital letter), with an axial protrusion. The (radially lower) bearing 42 is supported on the axial protrusion. Advantageously, the first and second collars are both annular in shape and nest each other. The collars 51, 54 make it possible to provide radial blocking of the bearings 42, 42'.

[0054] The pitch change system 45 comprises at least one control device 60 (shown diagrammatically) and at least one connection mechanism 61 (shown diagrammatically) connecting each stator vane 26 to the control device 60.

[0055] The pivot 41 of each blade root 27 comprises an arm 52 forming an eccentricity at its lower free end. Advantageously, but not limitingly, the pivot 41 comprises a radial hole that is open at its free end. An attachment member 53, such as a screw, is received in the radial hole to attach the arm 52 to the root of the stator vane 26. In the example shown, there are as many arms as there are stator vanes 26. The arm 52 is connected to a first end of a link rod forming the connection mechanism 61. The first end of the link rod is provided with a spherical joint through which a hinged shaft carried by the arm 52 passes. The axis of the hinged shaft is parallel to the radial axis Z. The second end of the link rod (opposite the first end) is connected to the control device 60.

[0056] The control device 60 is advantageously an actuator, for example a hydraulic jack. The actuator comprises a fixed body and a body that is movable with respect to the first fixed body. The first fixed body is connected to the fixed casing of the turbomachine, so as to be immovable in translation and in rotation. In particular, the fixed casing is mounted on a fixed inter-duct casing. The movable body is axially translated with respect to the fixed body along the longitudinal axis X. The movable body comprises an axial rod, the free end of which is connected to the second end of the link rod. The actuator is connected to a fluid supply source to supply pressurized oil to a chamber (not shown) of the fixed body.

[0057] Advantageously, the pitch change system 45 is arranged in an annular space defined in the inter-duct casing 16.

[0058] In Figure 3The control device, in this case a hydraulic jack, is installed downstream of the inter-compressor casing 30 and in a region called "core region". This "core region" is located in the vicinity of the combustion chamber 6. In this region there is more space to install the pitch change system 45 as well as the oil supply for the pitch change system, the power supply for de-icing of the separator nose 14, auxiliary equipment for pressurized air, etc. Furthermore, the core region is the ignition region. Since the hydraulic jack is typically a fuel-operated jack, the jack can be kept within the ignition region defined by the core region (and limited by the wall 35 of the inter-compressor casing 30). In particular, the control device is located downstream of the wall 35. More particularly, the control device is housed above the high-pressure compressor 5.

[0059] Figure 4 Another embodiment of the pitch change system device 45 is shown. The control device 60 is arranged between the splitter nose 14 and the inter-compressor casing 30. In this case, the control device 60 is installed in the vicinity of the separator nose 14. The control device is arranged upstream of the inter-compressor casing 30. The control device is in particular installed upstream of the roots 28 of the stator vanes 26.

[0060] With reference to Figure 1 , the turbomachine module can comprise another pitch change system 70 for changing the pitch of the movable blades of the propeller 2. This pitch change system 70 is arranged upstream of the gas generator 3 and radially below the roots of the movable blades of the propeller 2. This pitch change system comprises a second control device comprising a body that is axially movable with respect to a fixed body, the fixed body being installed on a fixed structure fixed to the inner casing 13. The pitch change system also comprises at least one load transmission bearing comprising an inner ring connected to the movable body and an outer ring, and a second connection mechanism for connecting the outer ring to the movable blades 12 of the propeller 2. The pitch change system for changing the pitch of the blades makes it possible to change the pitch of the blades 12 about their pitch axis, so that the blades occupy different angular positions depending on the operating conditions of the turbomachine and the associated flight phase, for example the extreme working position of the blades (reverse thrust position) and the extreme feathering position. The control device is also a hydraulic jack comprising a fixed body and a movable body. Here, the connection mechanism comprises a connecting rod.

Claims

1. A turbomachine module having a longitudinal axis X, comprising an unducted propeller (2) driven in rotation about said longitudinal axis X by a power shaft (9, 10) connected to at least one compressor rotor, and at least one straightener (25) comprising a plurality of stator vanes (26) extending from a fixed casing along a radial axis Z perpendicular to said longitudinal axis X, said straightener (25) being arranged downstream of said propeller (2), characterized in that, The fixed casing is an inter-compressor casing (30) arranged downstream of the low-pressure compressor (4) along the longitudinal axis X, the inter-compressor casing (30) comprising a ring (31) having a longitudinal axis X, the ring being provided with a sleeve (37) for carrying the stator vanes (26), the inter-compressor casing (30) and the ring (31) being monolithic.

2. The turbomachine module according to claim 1, characterized in that, The inter-compressor casing (30) comprises a radially inner shell (32) and a radially outer shell (33) coaxial with the longitudinal axis X and at least one radial structural arm (34) extending between the radially inner shell and the radially outer shell.

3. Turbomachine module according to claim 1 or 2, characterized in that The stator vanes (26) have a variable pitch and comprise a pitch variation system (45) for varying the pitch of the blades (27) of the stator vanes (26).

4. Turbomachine module according to claim 1 or 2, characterized in that At least one rotationally guiding bearing (42, 42') of the root of the stator vanes (26) is housed in a housing of the sleeve (37).

5. Turbomachine module according to claim 1 or 2, characterized in that The stator vanes (26) are uniformly distributed around the longitudinal axis X and extend radially into the secondary air flow (F2).

6. The turbomachine module according to claim 1 or 2, characterized in that, The inter-compressor casing (30) is manufactured by an additive manufacturing method.

7. Turbomachine module according to claim 1 or 2, characterized in that The inter-compressor casing (30) and the ring (31) are manufactured integrally.

8. The turbomachine module according to claim 1 or 2, characterized in that, The inter-compressor casing (30) and the ring (31) are assembled together by welding.

9. Turbomachine module according to claim 1 or 2, characterized in that The ratio S / C of the distance S between the trailing edge (22b) of the vanes of the propeller (2) and the leading edge (29a) of the stator vanes (26) to the chord C of the vanes of the propeller (2) is 3.

10. The turbomachine module of claim 3, wherein, The pitch variation system (45) comprises at least one control device (60) comprising a fixed body and a body axially mobile relative to the fixed body, and a connection mechanism (61) connecting each stator vane (26) to the mobile body of the control device (60).

11. The turbomachine module of claim 10, wherein, The control device (60) of the pitch variation system (45) is mounted in the intake casing (15) upstream of the inter-compressor casing.

12. The turbomachine module of claim 2, wherein, The stator vanes comprise a pitch variation system (45) for varying the pitch of the blades (27) of the stator vanes (26), the control device (60) of the pitch variation system (45) being mounted in an inter-duct casing (16) extending downstream from the intake casing (15) carrying a splitter nose (14) for separating the flow entering the turbomachine into a primary flow and a secondary flow, the control device (60) being located downstream of the sleeve (37) and downstream of a radial wall (35) of the inter-compressor casing (30) connecting the ring (31) to the radially outer shell (33).

13. The turbomachine module of claim 1 or 2, wherein, The stator vanes (26) of the straightener are unshrouded.

14. An aircraft turbomachine comprising at least one turbomachine module according to any one of claims 1 to 13 and a gas generator (3) for driving the unshrouded propeller (2) in rotation.

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