Turbine engine module equipped with a propeller and stator vanes carried by two casings and corresponding turbine engine

Abstract

The invention relates to a turbomachine module having a longitudinal axis X, comprising: a ductless propeller (2) intended to be driven in rotation about the longitudinal axis X by a power shaft (10, 11) connected to at least one rotor member (5, 6); at least one airflow straightener (3) comprising a plurality of stator vanes (28) extending along a radial axis Z; at least one first casing (17) mounted upstream of the rotor member (5, 6) along the longitudinal axis and at least one second casing (33) mounted downstream of the rotor member along the longitudinal axis. According to the invention, the stator vanes (28) each comprise a root (30) housed in a sleeve (37) connected to the first casing (17) and to the second casing (33).

Description

Technical Field

[0001] This invention relates to the field of turbine engines, and more particularly to a turbine engine module comprising a ductless propeller and a straightener with stator blades. The invention is also applicable to corresponding turbine engines. Background Technology

[0002] A turbine engine that includes at least one ductless propeller is called an "open rotor" or "ductless fan." Among these turbine engines, there are engines with two ductless, counter-rotating propellers (called "Unducted Dual Fan" (UDF)) and engines with a single ductless propeller and a straightener (comprising multiple stator blades) (called "Unducted Single Fan" (USF)). One or more propellers forming the propulsion section can be positioned at the rear of the gas generator (or engine) for a propeller-type configuration, or one or more propellers forming the propulsion section can be positioned at the front of the gas generator for a tractor-type configuration. These turbine engines are turboprop engines, which differ from turbojet engines in that they use an externally mounted (ductless) propeller instead of an internal fan. This allows for a significantly increased bypass ratio without being affected by the mass of the casing or nacelle designed to surround the propeller or fan blades. Examples of this turbine engine are described in documents EP-A1-3093437, EP-A1-3093443 and EP-A1-3225813.

[0003] Currently, this type of turbine engine (especially the USF turbine engine) has a considerable length along its longitudinal axis of rotation, which affects mass and generates significant noise. This noise is caused by the gas generator, but primarily by the interaction of wake and vortices, generated by the entanglement of airflow lines at the tips of the propeller blades and the straightener blades. The closer the stator blades are to the propeller blades, the greater the noise. In practice, the turbine engine stator blades are typically mounted on the inlet casing, which carries the splitter nose of the main and secondary flows, which circulate in the main bypass duct and around the inlet casing, respectively. However, removing the straightener stator blades from the propeller blades is detrimental to mass and overall size optimization; compressing the turbine engine as much as possible is also a problem. Summary of the Invention

[0004] The purpose of this invention is to provide a turbine engine module with stator blades arranged to reduce the acoustic impact of a ductless turbine engine while avoiding the need for an extended turbine engine.

[0005] According to the invention, this objective is achieved by a turbine engine module having a longitudinal axis X, the turbine engine module comprising: a ductless propeller intended to be driven by a power shaft to rotate about the longitudinal axis X, the power shaft being connected to at least one rotor member; at least one straightener comprising a plurality of stator blades extending along a radial axis Z; at least one first housing and a second housing, the at least one first housing being mounted upstream of the rotor member along the longitudinal axis, the second housing being mounted downstream of the rotor member along the longitudinal axis, each stator blade comprising a root received in a sleeve connected on one side to the first housing and on the other side to the second housing.

[0006] Therefore, this solution enables the aforementioned objectives. Specifically, the fact that the straightener blades are offset between the first and second housings, rather than being carried by the inlet housing as in the prior art, allows for a reduction in noise generated by this type of turbine engine, as the distance between the propeller and the straightener has increased. Using this arrangement, where the straightener blades are carried by two housings, the integration of auxiliary devices in the inlet housing (e.g., lubricant aids for lubrication and cooling the deceleration device, or pitch-changing systems for changing the blade pitch, etc.) is facilitated. Since the first and second housings are already present in the turbine engine, arranging the devices for supporting the stator blades between these two housings avoids lengthening the turbine engine. Furthermore, the center of gravity has shifted downstream of the turbine engine, meaning less overhang for the suspension used on the aircraft. Finally, maintenance of the straightener blades and components located near the blades (such as compressors) is improved, for example, by disassembling and pivoting one or more blades and / or lifting the connecting rods.

[0007] The module also includes one or more of the following features, individually or in combination:

[0008] - The module includes multiple connecting rods that extend between a first housing and a second housing, each connecting rod carrying a sleeve.

[0009] - Each connecting rod includes a first end and a second end, the first end being mounted on a first radial outer cover of a first housing via a ball joint type connector, and the second end being mounted on a second radial outer cover of a second housing via an embedded type connector.

[0010] - Each connecting rod and sleeve are made as a single piece.

[0011] - The stator blades of the straightener are variable in pitch setting, and the module includes a pitch changing system for changing the pitch of the stator blades, which is radially arranged outside the second housing.

[0012] - The stator blades of the straightener are without ducts.

[0013] - At least one rotary guide bearing for guiding the root rotation of the stator blades is housed in the contents of the sleeve.

[0014] - The stator blades are evenly distributed around the longitudinal axis X and extend radially into the secondary airflow.

[0015] - The first housing is an inlet housing that carries a splitter nose for splitting an airflow into a primary airflow and a secondary airflow. The inlet housing includes a first radial inner shield and a first radial outer shield, and at least one first radial structural arm extends between the first radial inner shield and the first radial outer shield.

[0016] - The second housing is a compressor inter-housing housing arranged downstream of the low-pressure compressor along a longitudinal axis. The compressor inter-housing housing includes a second radial inner shroud and a second radial outer shroud, which are coaxial with the longitudinal axis X, and at least one second radial structural arm extends between the second radial inner shroud and the second radial outer shroud.

[0017] - The ratio S / C corresponding to the chord C of the propeller blade is on the order of 3. This distance is the distance between the trailing edge of the propeller blade and the leading edge of the stator blade.

[0018] - The rotor assembly is a low-pressure compressor.

[0019] - The straightener is located downstream of the propeller.

[0020] - The connecting rod is made of titanium.

[0021] - A pitch changing system for changing the pitch of propeller blades includes at least one control device, which includes a fixed body and an axially movable body that is axially movable relative to the fixed body. The pitch changing system also includes a connecting mechanism that connects each stator blade to the movable body of the control device.

[0022] - The first housing and the second housing are separated by rotor components along the longitudinal axis X.

[0023] - The first and second shells are continuous.

[0024] The present invention also relates to an aircraft turbine engine comprising at least one module having any of the foregoing features and a gas generator downstream of a propeller. Attached Figure Description

[0025] The invention will be better understood by reading the following detailed explanatory description of embodiments of the invention given as purely illustrative and non-limiting examples with reference to the accompanying drawings, in which other objects, details, features, and advantages of the invention will become clearer:

[0026] [ Figure 1 ] Figure 1 This is a schematic diagram of a partial axial cross-section of an example of a turbine engine with a single ductless propeller to which the present invention is applied.

[0027] [ Figure 2 ] Figure 2 A perspective view is shown of the inlet housing connected to the compressor housing by a set of connecting rods, each of which carries a sleeve designed to receive the root of the straightener stator blades according to the invention;

[0028] [ Figure 3 ] Figure 3 A partial axial cross-section of an embodiment of a stator blade root mounted in a sleeve in a turbine engine according to the present invention is shown; and

[0029] [ Figure 4 ] Figure 4 A rear perspective view of an embodiment of the compressor housing according to the present invention is shown. Detailed Implementation

[0030] This invention applies to a turbine engine 1, which includes a single ductless propeller 2 and a straightener 3 located downstream of the propeller 2. The turbine engine is intended for installation on an aircraft. This turbine engine is as follows... Figure 1 The turboprop engine shown is described above as a "ductless single-fan" engine. Of course, the invention is also applicable to other types of turboprop engines.

[0031] In this invention, generally speaking, the terms "upstream," "downstream," "axial," and "axially" refer to the flow of gas in a turbine engine and here along the longitudinal axis X (even in...). Figure 2 The terms "radial," "inner," and "outer" are defined relative to the radial axis Z perpendicular to the longitudinal axis X and relative to the distance from the longitudinal axis X.

[0032] To facilitate manufacturing and assembly, turbine engines are typically modular; that is, a turbine engine comprises multiple modules that are manufactured independently of each other and then assembled together. Modularity also facilitates turbine engine maintenance. In this application, "turbine engine module" specifically refers to a module including a fan and a power shaft for driving the propeller.

[0033] exist Figure 1 In this turbine engine 1, a gas generator 4 is included, which typically comprises, from upstream to downstream, a low-pressure compressor 5, a high-pressure compressor 6, a combustion chamber 7, a high-pressure turbine 8, and a low-pressure turbine 9. The low-pressure compressor 5 and the low-pressure turbine 9 are mechanically connected via a low-pressure shaft 10, forming a low-pressure main body. The high-pressure compressor 6 and the high-pressure turbine 8 are mechanically connected via a high-pressure shaft 11, forming a high-pressure main body. The high-pressure shaft 11 extends radially outward from the low-pressure shaft 10 and is coaxial with the low-pressure shaft.

[0034] In another configuration, not shown, the low-pressure unit includes a low-pressure compressor connected to an intermediate-pressure turbine. A free-drive turbine is mounted downstream of the intermediate-pressure turbine and connected via a power drive shaft to a propeller, as described below, to drive the propeller's rotation.

[0035] The ductless propeller 2 is formed by a movable blade ring 12 extending from a rotating housing 13, which is centrally located and rotatable about a longitudinal axis X. The rotating housing 13 is movably mounted relative to an inner housing 14 extending downstream of the rotating housing 13. Figure 1 In the example shown, propeller 2 is mounted upstream of gas generator 4 (tractioner configuration). Alternatively, propeller 2 is mounted downstream of gas generator (thruster configuration). The blades of propeller 2 can be variable in pitch setting via pitch changing system 15.

[0036] The airflow F entering the turbine engine is split into a primary airflow F1 and a secondary airflow F2 at the splitter nose 16. The splitter nose is supported by an inlet housing 17 centered on the longitudinal axis. The inlet housing 17 extends downstream through an outer housing or duct housing 18. Figure 2 (Seen more specifically in the image) includes a radially inner shield 19 and a radially outer shield 20 centered on axis X. A plurality of structural arms 21 extend radially between the radially inner shield 19 and the radially outer shield 20. The arms 21 are fixed and integral with the inner shield 19 and the outer shield 20.

[0037] The main airflow F1 flows through the main duct 22 of the gas generator 4. Specifically, the main airflow F1 enters the gas generator 4 through the annular air inlet 23 and exits through the main nozzle 24 located downstream of the gas generator 4. The air inlet 23 is at least partially defined radially by the radially inner wall 16a of the splitter nose 16 and the radially outer wall 13a of the rotating housing 13, the radially inner wall of the splitter nose being annular and centered on the axis X.

[0038] The main duct 22 (through which air inlet 23 opens) is radially defined by a radially inner wall 25 and a radially outer wall 26. The radially inner wall 25 is formed at least partially by a radially inner shroud 19 of the inlet housing 17. The radially outer wall 26 is formed at least partially by a radially outer shroud 20 of the inlet housing 17. As for the secondary flow F2, the secondary flow flows around the inlet housing 17.

[0039] A power shaft or low-pressure shaft 10 (for a free-powered turbine and a low-pressure turbine, respectively) drives a propeller 2, which compresses the airflow outside the outer casing and provides most of the thrust. Alternatively, as... Figure 1 As shown, the reduction gear 27 is inserted between the propeller 2 and the drive shaft. The reduction gear 27 can be a planetary gear system or a planetary gear system.

[0040] The straightener 3 includes multiple stator blades 28 (or fixed blades), referred to as outlet guide vanes (OGVs). The stator blades 28 are uniformly distributed around the longitudinal axis X and extend radially into the secondary airflow F2. The stator blades 28 of the straightener 3 are arranged downstream of the blades 12 of the propeller 2 to straighten the airflow generated by the propeller blades. Each stator blade 28 includes a blade 29 that extends radially from its root 30. Also... Figure 1 As shown, it can be understood that the stator blades 28 of the straightener are ductless. The turbine engine shown is a USF, without a propeller and a fairing for the straightener. Each blade 29 also includes an axially opposed leading edge 31 and trailing edge 32. The stator blades also extend radially outside the duct housing 18. There are six to fourteen stator blades 28 surrounding the inlet housing 17 and the duct housing 18.

[0041] As in Figure 1 As can be seen, the root 30 of the stator blades of the straightener is mounted between the first housing and the second housing along the longitudinal axis. In this example, the first housing is the inlet housing 17, and the second housing is the compressor intercom housing 33.

[0042] The compressor housing 33 is arranged downstream of the low-pressure compressor 5. More specifically, the compressor housing 33 extends axially between the low-pressure compressor 5 and the high-pressure compressor 6. More precisely, referring to... Figure 1 The first housing (inlet housing 17) and the second housing (here, the compressor intercom housing 33) are axially separated by rotor components (here, the low-pressure compressor). Each compressor includes at least one rotor stage and at least one stator stage arranged along the longitudinal axis X. Furthermore, as... Figure 2As shown, the compressor housing 33 includes a radially inner shroud 34 and a radially outer shroud 35, which are coaxial and centered on the axis X. At least one radial structural arm 36 extends radially between the radially inner shroud 34 and the radially outer shroud 35. Specifically, a plurality of radial arms 36 are attached to the radially inner shroud 34 and the radially outer shroud 35. The radial arms 36 are also evenly distributed around the longitudinal axis X. There are six to ten radial arms to optimize the mechanical strength of the compressor housing 33. These arms 36 are fixed and integral with the inner shroud 34 and the outer shroud 36. The radially inner shroud 34 at least partially forms the radially inner wall 25 of the main duct 22, while the radially outer shroud 35 at least partially forms the radially outer wall 26 of the main duct 22. The main flow F1 flows between the first radial arm 21 of the inlet housing 17 and the second radial arm 36 of the compressor housing 33.

[0043] Reference Figure 1 and Figure 2 The stator blades 28 are supported by sleeves 37, which are connected to the inlet housing 17 on one side and the compressor housing 33 on the other. Each sleeve 37 is supported by a connecting rod 38, which allows the transmission of aerodynamic forces acting on the stator blades 28 and the thrust transmitted by the compressor housing 33. Each sleeve 37 is cylindrical and extends radially outward. The bottom of each sleeve 37 is rounded. In particular, each sleeve 37 includes a cylindrical skirt 39, the axis A of which is parallel to the radial axis Z. The cylindrical skirt 39 extends radially between a first boundary 40 and a second boundary 41. Each sleeve 37 includes a hole 42 that passes through the cylindrical skirt 39 on both sides along the axis A of the cylindrical skirt. Each hole 42 forms an inner accommodating portion for receiving the root 30 of the stator blades 28.

[0044] As in Figure 2 As can be seen, each connecting rod 38 is elongated and extends approximately along an axis B parallel to the longitudinal axis X. Specifically, each connecting rod 38 includes a first end 43 and a second end 44, which are opposite each other along the axis B of the connecting rod. The first end 43 of each connecting rod 38 is mounted on the radially outer shroud 20 of the inlet housing 17 via a ball joint type connector 45. Figure 3As shown, the spherical connector 45 is formed by a spherical head and a housing with a shape complementary to the spherical head. In this example, each first end 43 includes a spherical head 43a for this purpose. Each head 43a is received in a housing 20a with a generally complementary shape. The housing 20a serves as a receiving portion for the spherical head 43a. The housing 20a is carried by a radially outer shield 20. In particular, the housing 20a extends from an annular radial partition 20b of the radially outer shield 20. The spherical head 43a is mounted such that it is rotatably movable about axis B on the one hand, and pivotally movable about axis B at a predetermined pivot angle on the other hand. The pivot angle can be between 5° and 30°. Of course, the spherical connector 45 can be made such that the first end 43 includes the housing, and the radially outer shield 20 carries the spherical head.

[0045] Reference Figure 3 Each connecting rod 38 has a second end 44 connected to the radial outer shroud 35 of the compressor housing 33 via an embedded connector 46. Specifically, the second end 44 includes a lug 44a extending the connecting rod along axis B and defined in a plane perpendicular to the radial axis. This lug is mounted on one side of the upstream annular edge 35a of the radial outer shroud 35 of the compressor housing 33. In other words, the edge 35a and the lug 44a are radially superimposed. Furthermore, an attachment member 47 allows the second end 44 to be secured to the edge 35. For this purpose, the lug 44a includes a hole 48 (shown in dashed lines) passing through the wall of the lug on both sides along an axis perpendicular to the plane of the lug (here, the radial axis Z). The edge 35a includes a plurality of radial holes 49 (shown in dashed lines) passing through the wall of the edge on both sides and distributed around axis X. In this example, the attachment member 47 includes screws 50, each having a head and a shank with a radial axis. Each screw 50 passes through a hole 48 formed in a lug of the connecting shank and a corresponding hole 49 in the edge portion 35a. The attachment member 47 also includes a nut 51 for fastening the assembly.

[0046] The ball joint connector 45 (particularly the upstream ball joint connector) allows easy access to the low-pressure compressor compartment for, for example, to inspect the compressor's operation with an endoscope, or to reposition other nearby components (such as the rings of the variable stator impeller). Disassembling the downstream second end 44 will allow the connecting rod to be manipulated via the ball joint connector to pivot the connecting rod 38 for access to the low-pressure compressor.

[0047] Each sleeve 37 is axially located at the center of each connecting rod 38. In other words, each connecting rod 38 extends on both sides of the cylindrical skirt 39. Similarly, the connecting rod 38 is located at approximately one-third of the height of the sleeve 37, measured between the first boundary 40 and the second boundary 41 of the sleeve, and starting from the second boundary 41. In this way, the second boundary 41 is located radially outside the inlet housing 17 and / or the compressor inter-housing housing 33. Similarly, we know that the connecting rods connect the first housing and the second housing via the sleeves. The first housing and the second housing are substantially continuous. This allows for a more compact turbine engine module and turbine engine.

[0048] The connecting rod 38 and the sleeve 37 form an integral part. Advantageously, but not limitingly, the connecting rod 38 and the sleeve 37 are integrally formed (one piece). Advantageously, the connecting rod and sleeve assembly is manufactured by an additive manufacturing method. Alternatively, the connecting rod 38 and the sleeve 37 of the connecting rod are manufactured separately (e.g., by metal casting or machining) and then joined together by welding or other similar attachment methods.

[0049] The connecting rod 38 is made of metal. Advantageously, the connecting rod is made of titanium.

[0050] Due to the geometry of the connecting rod (here, the shape of a slender capital letter I) and the material of the connecting rod (titanium), the torsion angle caused by the force of the stator blade 28 is relatively low.

[0051] Alternatively, each connecting rod may have a Y-shaped or triangular shape. Similarly, other types of embedded connections can be considered.

[0052] Reference Figure 3 Advantageously, the stator blades 28 are variable in pitch setting to optimize the performance of the turbine engine. For this purpose, the turbine engine 1 includes another pitch-changing system 55 for changing the blade pitch of the stator blades 28. We can see that the root 30 of each blade 28 is typically in the form of a pivot 56, which is pivotally mounted in the interior of the sleeve 37 along axis C. Axis A and axis C are coaxial. The pivot 56 of the root 30 is pivotally mounted in the interior of each sleeve 37 via at least one guide bearing 57. In this example, two guide bearings 57, 57' are superimposed along radial axis Z (or axis A of the sleeve 37). These bearings 57, 57' are preferably, but not limited to, rolling bearings. Due to the available space in the sleeve 37 and the position of the sleeve in the annular space between the inlet housing and the compressor housing 33, the diameter of the bearings 57, 57' can be larger than usual.

[0053] Each bearing 57, 57' includes an inner ring 58 and an outer ring 59, the inner ring being rotatably fixed to a pivot 56, and the outer ring surrounding the inner ring 58. The bearing includes a rolling element 60 mounted between the inner surfaces of the inner and outer rings forming a raceway. The rolling element 60 includes balls. Advantageously, the bearings 57, 57' ensure that the impeller 28 is retained within the receiving portion of the sleeve 37.

[0054] A cylindrical sleeve 61 with a radial axis is installed in the bore 42 of each sleeve 37 to connect the inner ring 58 of each bearing to the root of each stator blade 28. The sleeve 61 is centered on the pitch axis C of the stator blade 28. Each sleeve 61 is also provided with internal splines arranged on the inner cylindrical surface and intended to engage with external splines on the outer surface of the pivot 56 located at the root 28 of each stator blade. A spacer 62 is also radially arranged between each bearing to ensure radial spacing between the bearings. In practice, the bearings must withstand forces and moments. Therefore, a gap is required between the two bearings to ensure that bending moments can be absorbed. The spacer 62 is advantageously, but not limitingly, arranged between the two inner rings of the bearing. A sealing element is provided in each bore 42 to prevent lubricant leakage from the bearing toward the outer side of the bearing.

[0055] As in Figure 3 It can also be seen that two clamps are arranged between the inner wall of each sleeve 37 and the lateral sides of bearings 57, 57'. The first clamp 63 has an L-shaped axial cross-section with branches radially overlapping with the (radially upward) bearing 57', and the second clamp 64 has an I-shaped axial cross-section with axial protrusions. Bearing 57 (radially lower relative to the radial axis Z, and according to...) Figure 3 The bearing is supported on an axial protrusion. Advantageously, the first hoop 63 and the second hoop 64 each have an annular shape and fit together. Hoops 63 and 64 enable the bearing to be radially blocked.

[0056] The pitch changing system 55 includes at least one control device 66 and at least one connecting mechanism 65 that connects each stator blade 28 to the control device 66. The pitch changing system 55 is arranged in an annular space defined within the duct housing 18. Specifically, the pitch changing system 55 is located radially outward of the compressor housing 33. More specifically, the control device 66 is located downstream of the sleeve 37 and the connecting rod 38. This is because there is more space to install such a mechanism and the attachment device for the root 30 of the blades. We know that the sleeve is also located in this annular space of the duct housing 18, as in... Figure 1 As shown in the image.

[0057] exist Figure 3In this configuration, each root 30 pivot 56 includes an arm 67, which forms an eccentric device at its lower free end. Advantageously, but not limitingly, the pivot 56 includes a radial bore that opens at the free end of the pivot. An attachment member 68 (such as a screw) is received in the radial bore to attach the arm 67 to the root of the stator blade 28. In the example shown, there are as many arms as stator blades 28. The arm 67 is connected to a first end of a link (shown in dashed lines) that forms a connecting mechanism 65. The first end of the link is provided with a ball joint through which a hinge shaft carried by the arm 67 passes. The hinge shaft is parallel to the radial axis Z. A second end of the link (opposite to the first end) is connected to a control device 66.

[0058] Advantageously, the control device 66 is an actuator (such as a hydraulic cylinder). The actuator includes a fixed body and a movable body movable relative to the first fixed body. The first fixed body is connected to a fixed shroud of the turbine engine such that it is immovable in translation and rotation. Specifically, the fixed shroud is mounted on a fixed duct housing. The movable body translates axially relative to the fixed body along a longitudinal axis X. The movable body includes an axial rod, the free end of which is connected to a second end of a connecting rod. The actuator is connected to a fluid supply source to supply pressurized oil to a chamber (not shown) of the fixed body. In this example, the radially outer shroud 35 of the compressor housing 33 includes a plurality of orifices 69 extending along the longitudinal axis X on both sides through the walls of the radially outer shroud. At least a portion of each axial rod is intended to pass through an orifice 69. The number of orifices 69 is as many as the number of rods or connecting rods. The control device 66 is located downstream of the compressor housing 33.

[0059] exist Figure 4 In another embodiment shown, advantageously, the control device 66 includes a plurality of actuators (such as hydraulic cylinders). Each actuator is connected to a linkage that passes at least partially through the orifice.

[0060] Therefore, specifically for mounting the pitch changing system 55 for the straightener, the stator blades 28 are moved away from the propeller blades 2 without affecting the length of the turbine engine or its overall size. The connecting rod 38 allows thrust and aerodynamic forces acting on the blades 28 to pass from the upstream side of the turbine engine through the inlet housing 17 and then through the compressor housing 33. Using this configuration, no additional components are required.

[0061] To address this, the ratio S / C corresponding to the distance S and the chord C of the propeller blade 2 was improved. This distance is the distance between the trailing edge of the propeller blade 2 and the leading edge 31 of the stator blade 28. This ratio is on the order of 3, while in the prior art, this ratio is between 1 and 2. The minimum ratio that meets noise standards is 1.

Claims

1. A turbine engine module having a longitudinal axis X, the turbine engine module comprising: A ductless propeller (2) is intended to be driven by a power shaft (10, 11) to rotate about the longitudinal axis X, the power shaft being connected to at least one rotor member (5, 6); at least one straightener (3) comprising a plurality of stator blades (28) extending along a radial axis Z; at least one first housing (17) and a second housing (33), the at least one first housing being mounted upstream of the rotor member (5, 6) along the longitudinal axis, and the second housing being mounted downstream of the rotor member (5, 6) along the longitudinal axis, characterized in that each of the stator blades (28) comprises a root (30) received in a sleeve (37), the sleeve being connected on one side to the first housing (17) and on the other side to the second housing (33), wherein the first housing (17) and the second housing (33) are different from each other and are connected to the sleeve (37) by a plurality of connecting rods (38).

2. The turbine engine module according to claim 1, characterized in that, The plurality of connecting rods (38) extend between the first housing (17) and the second housing (33), and each connecting rod (38) carries a sleeve (37).

3. The turbine engine module according to claim 2, characterized in that, Each connecting rod (38) includes a first end (43) and a second end (44), the first end being mounted on the first radial outer cover (20) of the first housing (17) via a ball joint type connector, and the second end being mounted on the second radial outer cover (35) of the second housing (33) via an embedded type connector.

4. The turbine engine module according to claim 2 or 3, characterized in that, Each connecting rod (38) is integrally formed with a sleeve (37).

5. The turbine engine module according to any one of claims 1 to 3, characterized in that, The stator blades (28) of the straightener (3) are variable in pitch setting, and the turbine engine module includes a pitch changing system (55) for changing the pitch of the blades of the stator blades (28), the pitch changing system being radially arranged outside the second housing (33).

6. The turbine engine module according to any one of claims 1 to 3, characterized in that, At least one rotary guide bearing (57, 57') for guiding the rotation of the root (30) of the stator blade (28) is housed in the contents of the sleeve (37).

7. The turbine engine module according to any one of claims 1 to 3, characterized in that, The stator blades (28) are evenly distributed around the longitudinal axis X and extend radially into the secondary airflow (F2).

8. The turbine engine module according to any one of claims 1 to 3, characterized in that, The first housing (17) is an inlet housing, the inlet housing including a splitter nose (16) for splitting the airflow into a primary airflow and a secondary airflow, the inlet housing including a first radial inner shield (19) and a first radial outer shield (20), and at least one first radial structural arm (21) extending between the first radial inner shield and the first radial outer shield.

9. The turbine engine module according to claim 3, characterized in that, The second housing is a compressor housing arranged downstream of the low-pressure compressor along the longitudinal axis. The compressor housing includes a second radial inner shield (34) and a second radial outer shield (35), which are coaxial with the longitudinal axis X, and at least one second radial structural arm (36) extends between the second radial inner shield and the second radial outer shield.

10. The turbine engine module according to any one of claims 1 to 3, characterized in that, The ratio S / C corresponding to the distance S and the chord C of the propeller (2) blade is on the order of 3. The distance is the distance between the trailing edge of the propeller (2) blade and the leading edge (31) of the stator blade (28).

11. The turbine engine module according to any one of claims 1 to 3, characterized in that, The first housing (17) and the second housing (33) are separated by the rotor component along the longitudinal axis X.

12. The turbine engine module according to any one of claims 1 to 3, characterized in that, The stator blades (28) of the straightener are ductless.

13. The turbine engine module according to any one of claims 1 to 3, characterized in that, Each sleeve is different from the first housing and the second housing.

14. The turbine engine module according to any one of claims 1 to 3, characterized in that, The first housing and the second housing are each centered on the longitudinal axis.

15. An aircraft turbine engine comprising at least one turbine engine module according to any one of claims 1 to 14, and a gas generator (4) downstream of the propeller (2).

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