TURBOMACHINE EQUIPPED WITH AN ELECTRIC ENGINE AND A COOLING DEVICE

Abstract

The invention relates to a turbomachine (1) for an aircraft comprising: - a propulsion unit configured to participate in the propulsion of the aircraft, - a low-pressure shaft rotating the propulsion unit, - a combustion chamber through which a primary flow generated by the rotating propulsion unit passes, - an electric machine (20) mounted downstream of the combustion chamber and swept by the primary flow, and a cooling device (35) for the electric machine (20). According to the invention, the cooling device (35) comprises a housing (36) mounted on the stator of the turbomachine and preferably opposite the electric machine, the housing comprising an air inlet (37) and a plurality of air outlets (38) configured to create several axial cooling air jets towards the electric machine (20). Figure for the abstract: Fig. 2

Description

Title of the invention: TURBOMACHINE EQUIPPED WITH AN ELECTRICAL MACHINE AND A COOLING DEVICE Technical field of the invention

[0001] The present invention relates to the aeronautical field. It relates in particular to a turbomachine equipped with an electric machine disposed downstream of the turbomachine and a cooling device for the electric machine. Technological background

[0002] Aircraft turbomachinery is increasingly equipped with one or more electric machines. An electric machine is an electromechanical device based on electromagnetism that converts electrical energy, for example, into mechanical energy (generator mode) or, reversibly, produces electricity from mechanical energy (motor mode). The electric machine can operate in both generator and motor modes.

[0003] Electric machines make it possible to meet the environmental challenge by reducing fuel consumption, particularly kerosene, providing a significant gain in electrical power for increasingly growing aircraft functions in conjunction with the number of equipment and improving the efficiency of the conversion of mechanical power into electrical power.

[0004] Document FR3132731 describes an example of a hybrid turbomachine with an electric machine installed on the low-pressure shaft and within an enclosure of the turbomachine's exhaust tail cone. The low-pressure turbine is generally subjected to gas flows having a high temperature, sometimes close to the temperature limits of the materials arranged in the low-pressure turbine area, and the tail cone is also an area with a thermally demanding environment.

[0005] The electrical machine is therefore exposed to these high temperatures, and its electrical components must be cooled during operation. Most of the electrical machine is cooled via an internal oil circulation system inherent in the design of the electrical machine.

[0006] However, the upstream and / or downstream face of the electric machine, which is / are exposed to radiation from the hot parts in the low-pressure turbine area, must be cooled by a ventilation device to prevent the risk of local overheating. For this purpose, a ventilation device is mounted to rotate directly onto the shaft of the electric machine.

[0007] The rear cone enclosure is supplied with air that is cooler than the primary airflow circulating around the rear cone. The ventilation element consists of fins or blades connected to the shaft of the electric machine via a coupling device (or not) depending on the rotational speed. The fins are positioned upstream and / or downstream of the electric machine and allow for the circumferential distribution of the airflow circulating within the rear cone enclosure. The ventilation element can be coupled or decoupled from the shaft, depending on the cooling requirement and the operating conditions. The added fins thus generate an airflow that passes axially through the enclosure and is homogenized azimutally by the rotation of the device.

[0008] However, this arrangement encumbers the rear cone enclosure and necessitates a modification of the electrical machine. Furthermore, the rotation of the ventilation unit causes the airflow to circulate around the electrical machine, which does not generate effective cooling of the most exposed parts of the electrical machine, namely the upstream face of the electrical machine.

[0009] There is a need to resolve all or part of the aforementioned drawbacks. Summary of the invention

[0010] The objective of the present invention is to provide a simple and economical solution for efficiently cooling and protecting from thermal radiation the electrical machine integrated into the turbomachine, particularly in a hot zone.

[0011] We achieve this objective in accordance with the invention by means of a turbomachine for an aircraft comprising, centered on a longitudinal axis: - a propulsion unit configured to participate in the propulsion of the aircraft, - a low-pressure shaft driving the propulsion unit in rotation, - a combustion chamber traversed by a primary flow generated by the rotating propulsion unit, - an electric machine mounted downstream of the combustion chamber, the electric machine comprising a rotor fixed in rotation to the low-pressure shaft and a stator attached to a stator of the turbomachine, and - a cooling device for the electric machine, the cooling device comprising a housing mounted on the stator of the turbomachine and preferably axially facing the electric machine, the housing comprising at least one cooling air inlet port which is connected to a cooling air supply source and a plurality of cooling air outlet ports configured to create several impact cooling air jets in the direction of the electric machine.

[0012] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, the integration of a cooling unit allows for the cooling and limiting of heating of at least one face of the electric machine by axial jet impact. The unit, supplied with cooling air, redistributes the air axially in the form of high-velocity jets to maximize the heat exchange coefficient between the air and the wall of the electric machine. The integration of such a unit is simple and robust. Implementation of the unit does not require substantial modifications to the downstream side of the turbomachine.

[0013] The turbomachine also includes one or more of the following features, taken alone or in combination:

[0014] - the casing is annular and centered on the longitudinal axis, the air jets of cooling elements being oriented so as to be parallel to the longitudinal axis.

[0015] - each outlet orifice comprises a diameter between 0.5 and 1.5 mm.

[0016] - the housing comprises a first wall, in which the plurality outlet ports, which are arranged axially at a predetermined distance from the electrical machine.

[0017] - the predetermined distance is defined by a ratio dl / D which is between 2 and 10, D being the diameter of an outlet orifice.

[0018] - the housing includes a second wall which is located axially opposite the first wall and which is covered with thermal insulation.

[0019] - each outlet orifice has a predetermined diameter and in that a The circumferentially measured spacing between two axes of two circumferentially adjacent outlet ports is at least twice the diameter of an outlet port.

[0020] - the inlet port is connected to a conduit which is in fluidic communication with a pressurized air supply source.

[0021] - the turbomachine includes a high-pressure compressor mounted upstream of the combustion chamber and forming the source of pressurized air supply.

[0022] - the turbomachine includes a primary channel in which the primary flow circulates and a secondary vein in which a secondary flow generated by the propulsive organ circulates and bypasses the primary vein, the secondary vein forming the source of pressurized air supply.

[0023] - the outlet ports are arranged in rows and the rows are arranged in in order to form even rows and odd rows, the outlet ports of the even rows being radially aligned, and the outlet ports of the odd rows being radially aligned and circumferentially offset from the outlet ports of the even rows.

[0024] - the number of rows of outlet ports is between two and ten.

[0025] - the cooling device is arranged axially between a housing exhaust and the electrical machine, and on the other hand radially below the exhaust casing, several structural arms extending radially from the exhaust casing which extends to a downstream end of a low pressure turbine, the casing being fixed to the exhaust casing, radially below the exhaust casing.

[0026] - at least one structural arm of the exhaust housing has a housing which passes through it radially and is in fluidic communication with the cooling air supply source.

[0027] - the turbomachine includes a ferrule which is mounted in a cavity located radially under the exhaust casing, the electric machine and the housing being radially mounted under the ferrule.

[0028] - - the electric machine is mounted downstream of the low pressure turbine.

[0029] - - the cooling device is disposed at least partially upstream of the electric machine.

[0030] The invention also relates to an aircraft equipped with such a turbomachine. Brief description of the figures

[0031] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which:

[0032] - Figure 1 illustrates a section along the longitudinal axis of an example of turbomachine according to the invention;

[0033] - Figure 2 is a rear axial cross-sectional view of an example of a turbomachine with an electric machine installed in a downstream cone according to the invention;

[0034] - Figure 3 is a detailed axial cross-sectional view of an example of a device cooling of the electrical machine according to [Fig.3];

[0035] - Figure 4 shows an example of a portion of a wall of a device cooling with a plurality of outlet ports according to the invention;

[0036] - Figure 5 illustrates one embodiment of the arrangement of the outlet ports in a wall of a cooling device according to the invention; and

[0037] - Figure 6 illustrates another embodiment of the arrangement of the orifices of outlet in a wall of a cooling device according to the invention. Detailed description of the invention

[0038] In this description, identical or substantially identical elements and / or elements with the same functions are represented by the same numerical references.

[0039] Figure 1 represents a turbomachine 1 intended to be mounted on an aircraft (not shown). The aircraft comprises, for example, a fuselage and two wings extending on either side of the fuselage relative to the fuselage axis. Each wing can carry at least one turbomachine.

[0040] The turbomachine 1 can be a turbojet or a turboprop.

[0041] The turbomachine 1 may include at least one propulsion unit 2 configured to participate in the propulsion of the aircraft. The propulsion unit 2 may be a propeller or a fan, whether shrouded or unshrouded.

[0042] The turbomachine 1 has a longitudinal axis X, which is here the axis of rotation of the rotors of the turbomachine.

[0043] In the present invention, and more generally, the terms "upstream," "downstream," "axial," and "axially" are defined with respect to the gas flow in the turbomachine and with respect to the longitudinal axis X of the turbomachine. Similarly, the terms "radial," "radially," "internal," and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X.

[0044] The turbomachine 1 generally comprises, from upstream to downstream, a compressor assembly 3, a combustion chamber 4 and a turbine assembly 5 which preferably forms a gas generator 6.

[0045] The turbomachine 1 is in particular a twin-spool, twin-flow turbomachine. The compressor assembly 3 comprises a low-pressure compressor 3a and a high-pressure compressor 3b. The turbine assembly 5 comprises a low-pressure turbine 5a and a high-pressure turbine 5b. The rotors of the low-pressure compressor 3a and the low-pressure turbine 5a are connected to each other by a low-pressure shaft 7 (illustrated in [Fig. 2]) so as to form a low-pressure housing. The rotors of the high-pressure compressor 3b and the high-pressure turbine 5b are connected, for example, by a high-pressure shaft so as to form a high-pressure housing. Without limitation, the high-pressure shaft extends inside the low-pressure shaft 7.

[0046] The propulsion unit 2 is advantageously mounted in this embodiment upstream of the compressor assembly 3. The propulsion unit 2 advantageously, but not exclusively, comprises movable blades (not shown) extending radially outwards from a hub (not shown). The hub is optionally coupled to the low-pressure shaft 7. In this example, the movable blades are surrounded by a blower housing 8. The latter is optionally centered on the longitudinal axis X.

[0047] The turbomachine 1 also advantageously, but not exclusively, comprises a nacelle 9 extending around the fan (propulsion element) of the turbomachine. The nacelle 9 is preferably supported by the fan housing 8.

[0048] The turbomachine 1 advantageously comprises a primary flow V1 through which a primary flow Fl circulates. The primary flow Fl is advantageously generated by the propulsion unit 2 when the latter is driven in rotation. The primary flow Fl passes through the gas generator and in particular the combustion chamber 4.

[0049] The propulsion unit 2 also advantageously generates a secondary flow F2 which circulates in a secondary stream V2. This secondary flow bypasses the primary stream VL. Advantageously, the turbomachine 1 includes a separation nozzle 10 which divides an airflow F entering the turbomachine into the primary flow Fl and the secondary flow F2. The primary stream VI and the secondary stream V2 are advantageously coaxial. The secondary flow F2 is ejected by a secondary nozzle 11 terminating the nacelle, while the primary airflow Fl is ejected outside the turbomachine via an ejection nozzle 12 located downstream of the gas generator 6. The primary flow Fl advantageously circulates around a downstream cone 13 enclosed by the ejection nozzle 12. The primary flow Fl and the secondary flow F2 rejoin at the outlet of their respective nozzles.

[0050] With reference to [Fig. 2], and advantageously, the downstream cone 13 is centered on the longitudinal axis X. The downstream cone 13 is further fixed to an exhaust housing 14 which is centered on the longitudinal axis X. The downstream cone 13 includes at one end an upstream flange 15 which is fixed to a downstream flange 16 of the exhaust housing 14. Bolts not shown allow the connection between the upstream and downstream flanges 15, 16. Advantageously, the exhaust housing 14 is arranged downstream of the low-pressure turbine 5b.

[0051] Advantageously, at least one structural arm 17 extends radially from the exhaust casing 14. The structural arm 17 is, for example, located downstream of the turbine assembly 5. In the present example, several structural arms 17 extend radially from the exhaust casing 14, which advantageously extends to a downstream end of the low-pressure turbine 5b. In other words, the structural arms 17 are advantageously located at a downstream end of the low-pressure turbine 5b.

[0052] Advantageously, the turbomachine 1 comprises at least one electric machine 20 which provides additional electrical power. The electric machine 20 can operate as a generator and / or as a motor. In the latter case, the electric machine 20 provides a propulsive function in addition to the propulsion element 2. In generator mode, the electric machine 20 supplies additional electrical power, for example, of at least one hundred kilowatts.

[0053] Still on [Fig. 2], the electric machine 20 is mounted downstream of the turbomachine 1. Preferably, the electric machine 20 is mounted downstream of the combustion chamber 4 and is swept by the primary flow Fl. More precisely, the electric machine 20 is mounted downstream of the low pressure turbine 5a.

[0054] In the present embodiment, the electric machine 20 is arranged in the downstream cone 13 of the turbomachine. The downstream cone 13 includes an enclosure 21 forming a space sufficient for the installation of the electric machine 20.

[0055] The electric machine 20 comprises a rotor 22 and a stator 23. Advantageously, the stator 23 extends radially outside the rotor which rotates relative to the stator 23 along the longitudinal axis X.

[0056] The rotor 22 of the electric machine 20 is rotationally fixed to the low-pressure shaft 7. For this purpose, advantageously, the rotor 22 of the electric machine 20 comprises a shaft 24 which is coupled, for example, to the low-pressure shaft 7. The coupling can be achieved using splines (not shown).

[0057] The stator 23 of the electric machine 20 is fixed to a stator of the turbomachine 1. In particular, the turbomachine 1 includes a ferrule 25 which is installed in a cavity 26 of the exhaust housing 14 and is integral with the exhaust housing 14. The ferrule 25 is optionally annular and centered on the longitudinal axis X. The stator 23 of the electric machine 20 includes, for example, a housing 27 provided with an upstream flange 28 which is fixed to a downstream flange 29 of the ferrule 25. In other words, the electric machine 20 is advantageously mounted on the ferrule 25. Bolts (not shown) allow the upstream flanges 28 and downstream flanges 29 to be fixed, for example. Advantageously, the forward flange 29 of the ferrule 25 is fixed to the downstream flange 16 of the exhaust housing 14.

[0058] The electric machine 20 includes at least one bearing 30 allowing the rotation of the shaft 24 of the rotor 22 relative to the stator 23 of the electric machine 20.

[0059] The turbomachine 1 advantageously includes a cooling device 35 configured to cool at least part of the electric machine 20. Indeed, the primary flow Fl also sweeps through the downstream cone 14, which increases the temperature inside the enclosure of the downstream cone 14, where the electric machine 20 is installed, to over 500°C, or even 600°C on some turbomachines. The temperature of the components of the electric machine (electrical conductors, electrical insulators, magnetic circuits, temperature sensors, exciters) must generally not exceed this value. The heat must be dissipated to ensure proper operation of the electric machine 20.

[0060] With reference to [Fig.2], the cooling device 35 is advantageously mounted at least partly upstream of the electric machine 20. The cooling device 35 is in particular mounted axially between the exhaust housing 14 and the electric machine 20.

[0061] Advantageously, the cooling device 35 advantageously comprises a housing 36 including at least one cooling air inlet 37 and a plurality of air outlet 38 configured to create several cooling air jets parallel to the longitudinal axis X in the direction of the electric machine 20. Advantageously, the inlet 37 is connected to a supply source 46 of preferably pressurized air.

[0062] According to an advantageous, but not limiting, feature, the housing 36 is mounted on the stator of the turbomachine. Preferably, the housing 36 is mounted on the ferrule 25, which allows the housing 36 to be positioned substantially at the same radial level as the electric machine 20. Advantageously, the housing 36 is mounted radially under the exhaust casing 14. In other words, the housing 36 is fixed to the downstream flange 16 of the exhaust casing 14.

[0063] The housing 36 is advantageously mounted opposite the electrical machine 20. In the illustrated example, the housing 36 is mounted opposite an upstream face 39 of the electrical machine 20. In this way, at least the upstream face 39 is cooled by the cooling air jets. Of course, the housing 36 can also be mounted downstream of the electrical machine 20.

[0064] Advantageously, but not limitingly, the housing 36 is annular and is centered on the longitudinal axis X. According to the illustrated example, the entire upstream face 39 of the electrical machine 20 is cooled.

[0065] As shown in [Fig. 3], the housing 36 comprises a first wall 40 and a second wall 41 which are advantageously arranged opposite each other. The second wall 41 is preferably arranged axially opposite the first wall 40. The housing 36 comprises, but is not limited to, a peripheral wall 42 connecting the first wall 40 and the second wall 41.

[0066] Advantageously, and as illustrated in [Fig. 4], a plurality of air outlets 38 are provided in the first wall 40. Each air outlet 38 passes through the first wall 40 from both sides. The outlets 38 open both inside and outside the housing 36. In other words, the housing 36 is hollow. The outlets 38 allow the high-speed ejection of air onto the wall of the electrical machine 20.

[0067] The outlet ports 38 are preferably circular and each has a central axis C. The circular shape makes it possible to produce cooling air jets of an efficient shape for cooling the electrical machine 20. The circular shape also advantageously implies a simple and inexpensive manufacturing of the air outlet ports 38. Alternatively, the air outlet ports 38 may have another shape such as oblong, etc.

[0068] According to an advantageous, but not limiting, feature, each air outlet 38, in the case of a circular shape, has a diameter D between 0.5 mm and 1.5 mm. These examples of diameters D allow for the optimization of a predetermined distance dl with the electric machine 20 (described below) and the spacing between the different outlet orifices 38, as well as the exit velocity of the cooling air jets.

[0069] Advantageously, but not exclusively, the first wall 40 is positioned at a predetermined distance dl from the electrical machine 20. This allows for better distribution of the cooling jets. The predetermined distance dl is defined by a ratio dl / D which is between 2 and 10. D is the diameter of an air outlet 38.

[0070] The second wall 41 advantageously includes the air inlet orifice 37.

[0071] Following the illustrated example, the second wall 41 is coated with thermal insulation 43. Advantageously, the bottom of the housing 36 formed by the second wall 41 also acts as insulation. For example, the second wall 41 is thick enough to partially block the radiation from the hot parts located directly opposite the electrical machine 20. The thermal insulation 43 can cover part or all of the internal surface of the second wall 41. The thermal insulation 43 improves the insulation efficiency through the thickness of the second wall 41. The thermal insulation 43 can include silica, for example.

[0072] The housing 36 can be made of a metallic material or a metallic material alloy. According to one embodiment, the metallic material or metallic material alloy is steel-based.

[0073] Preferably, the housing 36 is made in one piece. In the case of one-piece manufacturing, the housing 36 can be produced by additive manufacturing. Alternatively, the housing 36 is manufactured in several separate parts that are then assembled.

[0074] Figures 5 and 6 show various embodiments of the arrangement of the outlet orifices 38 in the first wall 40. The outlet orifices 38 are arranged in several rows. The number of rows of orifices is variable and depends on the size of the first wall 40. By way of example, the number of rows of outlet orifices 38 is between two and ten.

[0075] The outlet ports 38 can be arranged in concentric rows to facilitate their positioning and control their relative spacing. The outlet ports 38 are advantageously distributed over the entire surface of the face of the housing 36, so as to ensure homogeneous cooling on the upstream face of the electrical machine 20.

[0076] Advantageously, but not limitingly, the outlet ports 38 of the rows are spaced radially and the outlet ports 38 are spaced circumferentially.

[0077] In [Fig. 5], the rows are arranged in a staggered pattern relative to one another. Advantageously, the outlet ports 38 are arranged to form even rows rp and odd rows ri. The outlet ports 38 of the odd rows ri are circumferentially offset with respect to the outlet ports 38 of the even rows rp. More precisely, the outlet ports 38 of the even rows are advantageously aligned radially. Similarly, the outlet ports 38 of the odd rows ri are advantageously aligned radially.

[0078] Advantageously, a spacing d2 is measured circumferentially between two central axes C of two circumferentially adjacent air outlet orifices 38. The spacing d2 is measured between two orifices 38 of the same row and also between two orifices 38 of different adjacent rows. Advantageously, the spacing d2 is at least twice the diameter D of an air outlet orifice 38.

[0079] In [Fig. 6], the orifices 38 are arranged in the same direction. In other words, the outlet orifices 38 are aligned and not staggered. The spacing d2 is identical between the outlet orifices 38 of the same row and of a radially adjacent row.

[0080] The turbomachine 1 advantageously comprises at least one conduit 45 which is connected, on the one hand, at least to the air inlet 37 and, on the other hand, to the pressurized air supply 46. Figures 2 and 3 show examples of conduit 45. In this non-limiting example, the conduit 45 passes through the exhaust housing 14. Advantageously, the conduit 45 passes through the cavity 26 of the exhaust housing 14 and extends through the structural arm 17. Each structural arm 17 comprises, without limitation, a housing which passes radially through it and which is in fluidic communication with the cooling air supply 46.

[0081] Several pipes 45 can, for example, be connected to an inlet port 37 depending on the air flow rate, integration constraints, the size of the housing 36, or the pressure level to be achieved. Several pipes 45 could allow for a homogeneous distribution of the air temperature and the supply pressure of the jets at the outlet of the housing 36.

[0082] According to one embodiment, the power supply 46 is formed by the high-pressure compressor 3b. The latter is arranged upstream of the combustion chamber 4. Sampling means (not shown) are arranged at the high-pressure compressor 3b. The primary flow Fl circulating at the high-pressure compressor 3b is colder than the primary flow Fl circulating downstream from the combustion chamber 4. Sampling can also be carried out at the low pressure compressor 3a.

[0083] According to another embodiment, the supply source 46 is formed by the secondary vein V2. Sampling means (not shown) may also be provided at the level of the secondary vein V2 to sample a portion of the secondary airflow F2 circulating in the secondary vein V2.

[0084] In this way, the static, annular housing 36 allows for axial redistribution of the air in the form of high-speed jets to maximize the heat exchange coefficient between the air and the wall of the electric machine 20. The housing 36 also prevents the electric machine 20 from overheating, notably by protecting the upstream face of the electric machine 20 from thermal radiation from the turbine components. The cooling device therefore has a dual role.

Claims

Demands

1. Turbomachine (1) for an aircraft comprising centrally about a longitudinal axis (X): - a propulsion unit (2) configured to participate in the propulsion of the aircraft; - a low-pressure shaft (7) driving the propulsion unit (2) in rotation; - a combustion chamber (4) through which a primary flow (Fl) generated by the rotating propulsion unit (2) passes; - an electric machine (20) mounted downstream of the combustion chamber (4), the electric machine (20) comprising a rotor (22) rotationally fixed to the low-pressure shaft (7) and a stator (23) attached to a stator of the turbomachine (1);and, - a cooling device (35) for the electric machine (20), characterized in that the cooling device (35) comprises a housing (36) mounted on the stator of the turbomachine (1) and preferably axially opposite the electric machine (20), the housing (36) comprising at least one cooling air inlet (37) which is connected to a cooling air supply source (46) and a plurality of cooling air outlets (38) configured to create several impact cooling air jets in the direction of the electric machine (20).

2. Turbomachine (1) according to the preceding claim, characterized in that the casing (36) is annular and centered on the longitudinal axis (X), the cooling air jets being oriented so as to be parallel to the axis (X).

3. Turbomachine (1) according to any one of the preceding claims, characterized in that each outlet orifice (38) comprises a diameter (D) between 0.5 and 1.5 mm.

4. Turbomachine (1) according to any one of the preceding claims, characterized in that the casing (36) comprises a first wall (40), in which is provided the plurality of outlet ports (38), which is arranged axially at a predetermined distance (dl) from the electric machine (20).

5. Turbomachine (1) according to the preceding claim, characterized in that the predetermined distance (dl) is defined by a ratio dl / D which is between 2 and 10, D being the diameter of an outlet orifice (38).

6. Turbomachine (1) according to any one of the preceding claims, characterized in that the casing (36) comprises a second wall (41) which is located axially opposite the first wall (40) and which is coated with a thermal insulator (43).

7. Turbomachine (1) according to any one of the preceding claims, characterized in that each outlet orifice (38) has a predetermined diameter (D) and in that a circumferentially measured spacing (d2) between two axes (C) of two circumferentially adjacent outlet orifices (38) is equal to at least twice the diameter of an outlet orifice (38).

8. Turbomachine (1) according to any one of the preceding claims, characterized in that the inlet port (37) is connected to a conduit (45) which is in fluidic communication with a pressurized air supply source (46).

9. Turbomachine (1) according to the preceding claim, characterized in that it comprises a high-pressure compressor (3b) mounted upstream of the combustion chamber (4) and forming the pressurized air supply source (46).

10. Turbomachine (1) according to claim 8 or 9, characterized in that it comprises a primary flow (VI) in which the primary flow (F1) circulates and a secondary flow (V2) in which a secondary flow (F2) generated by the propulsion member (2) and bypassing the primary flow (VI) circulates, the secondary flow (V2) forming the pressurized air supply source (46).

11. Turbomachine (1) according to any one of the preceding claims, characterized in that the outlet ports (38) are arranged in rows and the rows are arranged so as to form even rows (rp) and odd rows (ri), the outlet ports (38) of the even rows (rp) being aligned radially and the outlet ports (38) of the odd rows (ri) being aligned radially and circumferentially offset from the outlet ports (38) of the even rows (rp).

12. Turbomachine (1) according to the preceding claim, characterized in that the number of rows of outlet ports (38) is between two and ten.

13. Turbomachine (1) according to any one of the preceding claims, characterized in that the cooling device is arranged on the one hand axially between an exhaust casing (14) and the electric machine (20), and on the other hand radially under the exhaust casing (14), several structural arms (17) extending radially from the exhaust casing (14) which extends to a downstream end of a low pressure turbine (5b), the housing (36) being fixed to the exhaust casing (14), radially under the exhaust casing (14).

14. Turbomachine (1) according to claim 13, characterized in that at least one structural arm (17) of the exhaust casing (14) has a housing which passes radially through it and which is in fluidic communication with the cooling air supply source (46).

15. Turbomachine (1) according to any one of claims 8 and 14, characterized in that it comprises a ferrule (25) which is mounted in a cavity located radially (26) under the exhaust casing (14), the electric machine (20) and the housing (36) being mounted radially under the ferrule (25).

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