FR3047526A1 - OPTIMIZED GEOMETRY JET TROMPE, DEVICE, TURBOMACHINE, AND METHOD THEREOF - Google Patents

Abstract

The horn (18) comprises: - a mixer (34); - a primary flow injection assembly (30) in the mixer (34) comprising at least one injector, the primary flow injection assembly (30) having a downstream free edge (54); a secondary flow supply duct (32) surrounding the primary flow injection assembly (30) and opening into the mixer (34) at an upstream edge (42). The supply duct (32) and the injection assembly (30) define, in a median plane passing through the main axis (A-A '), a central flow injection axis (84). secondary in the mixer (34). In the median plane, the angle (β) formed by the central axis (84) of injection, and the straight line (86) connecting the free edge downstream (54) of the injection assembly (30) to the edge upstream (42) of the mixer (34) is between 80 ° and 100 °. Application to the limitation of oil consumption in a turbomachine.

Description

Optimized geometry jet trumpet, device, turbomachine, and method thereof

The present invention relates to a jet pump, intended to be connected to a vacuum chamber of a turbomachine, comprising: - a mixer, defining a tubular channel of main axis for receiving a primary gas stream under pressure and a flow deoiled secondary, the mixer having an upstream edge; a primary flow injection assembly in the mixer comprising at least one injector, the primary flow injection assembly having a free edge downstream; - A secondary flow supply line surrounding the primary flow injection assembly, and opening into the mixer at the upstream edge, the free edge downstream of the primary flow injection assembly being set back in the supply line; the feed pipe and the primary flow injection assembly defining between them, in at least one median plane passing through the main axis, on either side of the main axis, a central injection axis secondary flow in the mixer.

The horn is intended to be disposed in a device for depressurizing a lubrication chamber of an aircraft turbomachine, in particular a turbojet engine or a turbine engine.

An aircraft turbomachine generally comprises a plurality of rotary shafts, each carrying one or more compressor stages, and one or more turbine stages.

The rotary shafts are mounted in structural housings through bearings on which they rotate. The bearings are lubricated in a conventional manner by means of oil injectors. To avoid oil losses, the bearings and various gears of the engine are generally placed in at least one sealed enclosure vis-à-vis the air stream.

To close the enclosures, seals sealing around the shaft and / or labyrinths are provided.

Seals and labyrinths being at least partially open, they are likely to constitute areas of oil loss. To avoid a significant consumption of oil, it is known to place the speakers in depression, which keeps the oil within them. Generally, the generation of a vacuum is provided by means of a trunk of the aforementioned type, comprising at least one compressed air injector constituting a primary flow. The injector is disposed in a deoiled gas supply line from the enclosure, the deoiled gas constituting a secondary flow. The injector and the gas supply pipe open into a mixer, then into a diffuser having a divergent. The compressed air drives the de-oiled gas coming from the chamber at high speed, thus causing the vacuum in the chamber. FR 3,011,583 describes a horn of the aforementioned type, comprising a primary injector intended to be used continuously, and a secondary injector intended to be used only when the turbomachine is operating at low speed. The secondary injector extends around the primary injector.

In some cases, especially in certain relative positions of the secondary injector relative to the primary injector, the horn has degraded performance. The use of this horn can cause a significant oil consumption cruise, the depression generated in the speakers being insufficient.

An object of the invention is therefore to improve the performance of a jet pump connected to a lubrication chamber of an aircraft turbomachine, in order to limit the oil consumption in the turbomachine. For this purpose, the subject of the invention is a trunk of the aforementioned type, characterized in that in the median plane, the angle formed by the central injection axis, and the straight line connecting the free edge downstream of the assembly. primary flow injection at the upstream edge of the mixer is between 80 ° and 100 °; in particular between 85 ° and 95 ° and advantageously between 88 ° and 92 °.

The trunk according to the invention may comprise one or more of the following characteristics, taken separately or in any technically possible combination: the primary flow injection assembly comprises a central injector for primary flow and at least one primary flow peripheral injector disposed around the central injector, the peripheral injector defining the free edge downstream of the primary flow injection assembly; the peripheral injector extends around the central injector, coaxially with the central injector; - The central injector and the peripheral injector defining between them, an intermediate space having on either side of the main axis in the median plane, a central axis of injecting primary flow supplement in the mixer, the angle formed by the central axis for injecting primary and auxiliary flow and the straight line connecting the downstream edge of the peripheral injector to the downstream edge of the central injector being between 80 ° and 100 °, advantageously between 85 ° and 95 ° and in particular between 88 ° and 92 °; the supply line has an outer wall converging along the main axis towards the mixer, the primary flow injection assembly having a peripheral partition converging along the main axis towards the mixer, the axis central injection being defined in the median plane, on either side of the main axis by the bisector of the angle formed between the outer wall and the peripheral wall; the tubular channel of the mixer has a constant cross section; the length of the tubular channel of the mixer is between 6 and 8 times its maximum transverse dimension; it comprises a diffuser disposed at the end of the mixer, the diffuser defining a downstream channel diverging, the tubular channel of the mixer opening into the downstream channel diverge; the divergent downstream channel diverges from a half angle greater than 2 °, for example between 2.5 ° and 3.5 ° with respect to the main axis; at least one injector of the primary flow injection assembly is a supersonic injector; the supersonic injector defines a primary flow circulation light having an upstream region converging towards the main axis, an intermediate restriction, and a downstream region diverging from the main axis; the length of the upstream region is less than the length of the downstream region; the angle of divergence of the downstream region is between 1 ° and 5 °; the angle of convergence of the upstream region is between 10 ° and 50 °; the primary flow circulation light comprises a cylindrical output region; the length of the cylindrical outlet region is less than 50% of the length of the downstream region; the supersonic injector extends along the main axis; it comprises a secondary primary flow injector disposed around the supersonic injector. The subject of the invention is also a device for depression of an enclosure of an aircraft turbomachine comprising: a trunk as defined above; a supply assembly for a primary pressure stream, comprising a source of pressurized fluid connected downstream to a primary flow injection assembly; - A set of supply of a secondary oil flow, intended to be connected upstream to at least one chamber of the turbomachine, and connected downstream to the supply line.

The device according to the invention may comprise one or more of the following characteristics, taken separately or in any technically possible combination: it comprises a de-oiler interposed between the enclosure and the supply line. The invention also relates to an aircraft turbomachine comprising: at least one enclosure containing oil; - A device as defined above, connected to the enclosure. The subject of the invention is also a method of placing a chamber of an aircraft turbomachine under vacuum, comprising the following steps: providing a device as defined above, connected to the enclosure; - feeding a primary stream under pressure through the primary flow supply assembly to the injection assembly; - Driving the secondary flow by the primary flow through the supply assembly of the secondary flow, and through the supply line; mixing the primary flow and the secondary flow in the mixer; wherein in at least one median plane passing through the main axis, on either side of the main axis, the secondary flow is injected along a central injection axis in the mixer and, in the median plane, angle formed by the central injection axis, and the straight line connecting the free edge downstream of the primary flow injection assembly to the upstream edge of the mixer is between 80 ° and 100 °, in particular between 85 ° and 95 ° And advantageously between 88 ° and 92 °.

The method according to the invention may comprise one or more of the following characteristics, taken separately or in any technically possible combination: at least one injector of the primary flow injection assembly is a supersonic injector, the primary flow flowing through the supersonic injector is supersonic at least at the exit of the supersonic injector; the number of Mach of the primary flow at the outlet of the supersonic injector is greater than 1, and in particular between 2.5 and 3. The invention will be better understood on reading the description which follows, given solely to As an example, and with reference to the accompanying drawings, in which: - Figure 1 is a schematic view of an aircraft turbine engine, provided with a first horn according to the invention; - Figure 2 is a schematic view of the different parts of the horn of Figure 1; FIG. 3 is a view of the end of the primary flow injection assembly of the first horn according to the invention; - Figure 4 is a simplified view similar to Figure 3 of a second horn according to the invention; - Figure 5 is a view similar to Figure 3 of a third horn according to the invention.

In what follows, the terms "upstream" and "downstream" refer to the normal direction of circulation of a fluid.

A first aircraft turbine engine 10 according to the invention is illustrated schematically in FIG. 1. The turbomachine 10 is for example a turbojet engine or a turbine engine.

The turbomachine 10 comprises at least one rotary shaft (not shown) and at least one support bearing of the rotary shaft.

The turbomachine 10 comprises in known manner at least one enclosure 12, 14 for sealingly containing at least one element to be lubricated, in particular a bearing. In this example, the turbomachine 10 comprises at least one front chamber 12 and at least one rear chamber 14, arranged at different stages of the turbomachine 10.

At least one oil injector (not shown) opens into each chamber 12, 14. Each chamber 12, 14 is advantageously closed by at least one seal and / or a labyrinth.

To limit the oil consumption, the turbomachine 10 comprises a device 16 of depression of each chamber 12, 14.

The vacuum device 16 comprises a jet pump 18 according to the invention, a set 20 for supplying a primary flow under pressure into the horn 18, and a set 22 for supplying a secondary flow from the speakers 12 , 14 in the trunk 18.

The vacuum device 16 further comprises at least one de-oiler 24 and an assembly 26 of oil recirculation.

With reference to FIGS. 2 and 3, the horn 18 comprises a primary flow injection assembly 30, a secondary flow supply conduit 32 receiving the primary flow injection assembly 30 and a mixer 34 intended to receive and mix the primary stream and the secondary stream.

The horn 18 further comprises a diffuser 36, mounted at the downstream end of the mixer 34.

The supply line 32 comprises a housing 40 of axis A-A 'receiving the injection assembly 30, the housing 40 being connected to an upstream edge 42 of the mixer 34.

The casing 40 here comprises an outer peripheral wall 44 converging towards the axis A-A 'in the direction going towards the mixer 34, up to the upstream edge 42.

The feed line 32 is connected upstream to the secondary flow supply assembly 22. The primary flow injection assembly 30 comprises at least one injector 50, 52 of primary flow. The assembly 30 is set back relative to the mixer 34, in the casing 40 of the supply duct 32. For this purpose, the primary flow injection assembly 30 defines at least one downstream edge 54 which is totally contained in the supply line 32, upstream of the upstream edge 42 of the mixer 34.

In this example, the primary flow injection assembly 30 comprises a first central injector 50 of primary flow, intended to be permanently supplied by a primary flow and a second peripheral flow injector 52, intended to be supplied temporarily by primary flow, especially when the turbine engine 10 runs at low speed. The central injector 50 has a peripheral wall 60 defining a primary flow circulation 62.

In the example shown in Figure 3, the central injector 50 is a supersonic injector.

The peripheral wall 60 thus delimits, in the light 62, a convergent upstream region 64, an intermediate restriction 66, and a divergent downstream region 68. Light 62 further advantageously defines a cylindrical outlet region 70. It has a downstream edge 71.

The upstream region 64 has an angle of convergence towards the axis A-A 'greater than 10 °, advantageously between 15 ° and 45 °.

The length of the upstream region 64 taken along the axis A-A 'is much shorter than the length of the downstream region 68 taken along the same axis. The length of the upstream region 64 is for example less than 50% of the length of the downstream region 68, in particular less than 25% of the length of the downstream region 68.

The intermediate restriction 66 has a maximum transverse extent, taken perpendicular to the axis A-A ', less than 60% of the maximum transverse extent of the upstream region 64.

The downstream region 68 diverges progressively from the axis A-A 'to the mixer 34. The angle of divergence of the downstream region 68 with respect to the axis A-A' is, for example, greater than 1 °, and especially understood between 2 ° and 4 °.

The cylindrical region 70 has a constant cross section along the axis A-A '. The maximum transverse extent of the cylindrical region 70 is less than the maximum transverse extent of the upstream region 64, for example between 90% and 60% of the maximum transverse extent of the upstream region 64.

The length of the cylindrical region 70 is less than the length of the upstream region 64 and the length of the downstream region 68. It is for example between 10% and 30% of the length of the downstream region 68. The injector device 52 is coaxial with the central injector 60. It comprises an outer peripheral wall 80 of axis A-A 'extending around the peripheral wall 60 of the central injector 50.

The outer peripheral wall 80 converges towards the axis A-A 'in the direction towards the mixer 34. It has a frustoconical shape of axis A-A'.

The outer peripheral wall 80 delimits, with the peripheral wall 60, an intermediate space 82 for passing a primary flow supplement.

In this example, the outer peripheral wall 80 defines the downstream edge 54 of the injection assembly 30, at its free edge.

In at least one medial axial plane passing through the axis A-A ', here in each median axial plane, the peripheral wall 60 of the central injector 50 and the outer peripheral wall 82 of the peripheral injector 52 define between them, on either side of the axis A-A 'in the intermediate space 82, a central axis 71A for injecting primary flow into the mixer 34. The central axis 71A extends along the bisector the angle Θ defined between the section of the peripheral wall 60 and the section of the outer peripheral wall 80 in the median plane. The angle formed by the central axis 71A for injecting primary and auxiliary flow and the straight line connecting the downstream edge 54 of the peripheral injector 52 to the downstream edge 71 of the central injector 50 is between 80 ° and 100 °, advantageously between 85 ° and 95 ° and in particular between 88 ° and 92 °.

The downstream edge 71 of the central injector 50 is thus set back from the downstream edge 54 of the peripheral injector 52. The primary flow injection assembly 30 defines externally with respect to the axis A-A ' , in the casing 40 of the secondary flow supply line 32, an annular channel 56 for circulation of the secondary flow to the mixer 34.

In the example shown in Figure 3, the annular channel 56 is defined between the outer peripheral wall 80 of the peripheral injector 52 and the outer peripheral wall 44 of the housing 40.

In at least one median axial plane passing through the axis A-A ', here in each median axial plane, the feed pipe 32 and the injection assembly 30 define between them, on either side of the A-A 'axis in the channel 56, a central axis 84 secondary flow injection in the mixer 34. The central axis 84 extends along the bisector angle defined between the section of the outer wall 80 and the section of the outer wall 44 in the median plane. The central axis 84 is inclined with respect to the axis A-A '. In the example shown in Figure 3, the inclination angle of the central axis 84 is for example between 5 ° and 45 °. This angle is minimized as a function of the space available in the zone for the installation of the horn 18. The angle β formed by the central axis 84 of secondary flow injection and by the line 86 connecting the downstream edge 54 of the injection unit 30 at the upstream edge 42 of the mixer 34 is between 80 ° and 100 °, advantageously between 85 ° and 95 ° and in particular between 88 ° and 92 °.

The mixer 34 extends along the axis A-A '. It comprises a cylindrical outer wall 90 defining internally a tubular channel 92 of axis A-A ', for mixing the primary flow and the secondary flow.

The tubular channel 92 preferably extends at least to the position of the intersection between a diverging cone section from the downstream edge 54 of the injection assembly 30, with a half opening angle included between 2.5 ° and 3.5 ° and preferably equal to 3 °, and a cylinder of diameter corresponding to the internal diameter of the tubular channel 92.

For a subsonic flow at the outlet of the injection assembly, at the end of the injectors, the length of the tubular channel 92, taken between the upstream edge 42 of the mixer 34 and a downstream edge 93 of the mixer 34 located at the diffuser 36 along the axis A-A 'is thus generally between 6 and 8 times the maximum transverse extent of the tubular channel 92, taken along the axis A-A'.

In the case of a sonic or supersonic flow, the starting point of the diverging cone is offset downstream in the tubular channel 92 to the point where the shock waves generated in the flow at the outlet of the assembly of injection 30 disappear.

The diffuser 36 defines a divergent downstream channel 94 into which the tubular channel 92 opens.

The divergent downstream channel 94 diverges from the axis A-A 'in the direction away from the mixer 34 along the axis A-A'. The diverging half-angle y of the divergent downstream channel 94, taken between the axis A-A 'and the lateral edge of the downstream channel 94 is greater than 2 °, and is for example between 2.5 ° and 3.5 ° with respect to the axis A-A '.

The divergent downstream channel 94 has a length sufficient to transform the high speeds at the outlet of mixer 34 into pressure. This length depends on the space available to accommodate the trunk 18.

Preferably, the divergent downstream channel 94 is connected to an outlet located in the air stream of the turbomachine 10, for example at the helix.

With reference to FIG. 1, the primary flow supply assembly 20 comprises a source 100 of primary flow under pressure, a first line 102 for supplying primary flow from the source 100 to the central injector 50 and a second line 104 supplying primary flow from the source 100 to the peripheral injector 52.

The source 100 is for example formed by a compressor of the turbomachine 10.

The line 102 is stitched on the source 100. It is permanently open to supply the central injector 50. The line 104 is also stitched on the source 100. It comprises a valve 106 that can be opened when the turbomachine 10 is running down diet. The secondary flow supply assembly 22 comprises, for each chamber 12, 14, a sampling branch 120, 122 connected to the de-oiler 24.

It comprises, downstream of the de-oiler 24, a line 114 for supplying the supply line 32

The de-oiler 24 is suitable for collecting the drops of oil present in the fluids collected by the branches 120, 122. It is suitable for dispensing the collected oil into a reservoir of the recycling assembly 26 which communicates with each chamber 12, 14.

The operation of the vacuum device 16, when the turbine engine 10 is active, will now be described.

During the operation of the turbomachine 10, oil is continuously injected into the enclosures 12, 14. To limit oil leakage from each chamber 12, 14, a vacuum is generated in each chamber 12, 14 by suction through the branches 120, 122 of the secondary flow supply assembly 22. For this purpose, a primary flow under pressure, in particular a compressed air flow, is taken from the source 100 and is conveyed continuously through the line 102 to the central injector 50. At low speed, when the expansion ratio between the source 100 and the outside of the horn 18 is less than a value between 2.5 and 3, the valve 106 is open . The central injector 50 and the peripheral injector 52 are jointly supplied with primary flow. At higher speeds, only the central injector 50 is powered, the valve 106 on the line 104 is then closed.

The primary flow is introduced into the central injector 50. In the example illustrated in FIG. 2, the central injector 50 is a supersonic injector.

The primary flow thus accelerates successively through the convergent upstream region 64, through the restriction 66, and accelerates further in the downstream region 68. It then passes into the cylindrical region 70, which has the effect of adapting its pressure to the surrounding pressure and to generate a substantially isentropic flow.

The primary flow therefore undergoes a complete relaxation, without shock wave, with an expansion rate greater than 10, especially between 12 and 30. The primary flow is thus introduced into the mixer 34 at high speed. The Mach number of the primary flow at the downstream edge of the injection assembly 30 is greater than 1, advantageously greater than 2, and is in particular between 2 and 3.

The primary flow thus causes the secondary flow that is introduced into the mixer 34 through the secondary channel 56 between the injection assembly 30 and the casing 40 of the supply line 32.

As indicated above, in projection in a median plane passing through the axis A-A ', on either side of the axis A-A', the central injection axis 84 of the secondary flow is substantially perpendicular. at the right 86 connecting the downstream edge 54 of the injection assembly 30 to the upstream edge 42 of the mixer 34. Surprisingly, this improves the introduction of the secondary flow into the mixer 34 and avoids significant variations in pressure static at the inlet of the mixer 34.

The primary flow and the secondary flow then mix optimally in the mixer 34, then are ejected out of the tube 18 through the diffuser 36.

Since the diffuser 36 has a larger opening diverging channel 94, its length can be reduced compared with that of the mixer 34. For the same length of horn 18, this leads to a greater efficiency of the horn 18.

Thus, compared with a trunk 18 of the state of the art, the generated level of depression is higher and / or the compressed primary flow consumption is lower. The vacuum created in each enclosure 12, 14 is therefore adequate to meet the necessary vacuum specifications, without increasing the fuel consumption.

This depression being particularly effective, the oil consumption in the turbomachine 10 is reduced.

In a variant partially illustrated in Figure 4, the injection assembly 30 comprises a plurality of peripheral injectors 52 non-concentric with the central injector 50, each formed by a convergent tube. The peripheral injectors 52 are angularly distributed around the central injector 50, radially spaced from it. The outer wall 44 of the secondary flow supply line 32 extends around the peripheral injectors 52 by defining the outside of the peripheral injectors 52, the channel 56. The channel 56 has, in projection in each median axial plane passing by the axis of a peripheral injector, a central axis 84.

As previously, in projection in the median axial plane, the angle β formed by the central axis 84 of secondary flow injection and by the straight line 86 connecting the downstream edge 54 of the injection assembly 30, to the upstream edge 42 of the mixer 34 is between 80 ° and 100 °, preferably between 85 ° and 95 ° and in particular between 88 ° and 92 °.

Similarly, in this embodiment, an intermediate channel 200 of secondary flow injection is defined between each peripheral injector 52 and the central injector 50. In projection in the median axial plane passing through the axis 202 of the injector 52, the angle formed by the central axis 204 of secondary flow injection in the intermediate channel 202 and the right connecting the downstream edge 54 of the peripheral injector to the downstream edge 71 of the central injector 50 is also between 80 ° and 100 °, preferably between 85 ° and 95 ° and in particular between 88 ° and 92 °.

In a variant, illustrated in FIG. 5, the central injector 50 is a sonic or subsonic injector. The speed of the primary stream at the downstream edge 54 is less than or equal to the speed of sound.

The operation of the horn 18 shown in FIG. 5 nevertheless remains very satisfactory.

In a variant (not shown), the injection assembly 30 is devoid of a peripheral injector 52.

Claims (14)

1.-Jet trumpet (18), intended to be connected to a vacuum chamber (12, 14) of an aircraft turbomachine (10), comprising: - a mixer (34), defining a tubular channel (92) a main axis (A-A ') for receiving a primary gas stream under pressure and a deoiled secondary stream, the mixer (34) having an upstream edge (42); - a primary flow injection assembly (30) in the mixer (34) comprising at least one injector (50, 52), the primary flow injection assembly (30) having a downstream free edge (54); a secondary flow supply duct (32) surrounding the primary flow injection assembly (30), and opening into the mixer (34) at the upstream edge (42), the downstream free edge (54); ) the primary flow injection assembly (30) is recessed in the supply line (32); the supply line (32) and the primary flow injection assembly (30) defining therebetween, in at least one median plane passing through the main axis (A-A '), on either side the main axis (A-A '), a central secondary flow injection axis (84) in the mixer (34); characterized in that, in the median plane, the angle (β) formed by the central axis (84) of injection, and the straight line (86) connecting the free edge downstream (54) of the injection assembly primary flow rate (30) at the upstream edge (42) of the mixer (34) is between 80 ° and 100 °. The trumpet (18) according to claim 1, wherein the primary flow injection assembly (30) comprises a central primary flow injector (50) and at least one primary flow peripheral injector (52) disposed therein. around the central injector (50), the peripheral injector (52) defining the downstream free edge (54) of the primary flow injection assembly (30). 3. - Trumpet (18) according to claim 2, wherein the peripheral injector (52) extends around the central injector (50), coaxially with the central injector (50). 4. - Trumpet (18) according to claim 3, wherein the central injector (50) and the peripheral injector (52) define between them, an intermediate space (82) having on either side of the axis main plane (A-A ') in the median plane, a central axis (71 A) for injecting primary flow into the mixer (34), the angle formed by the central axis (71 A) of injection of primary and secondary flow by the right connecting the downstream edge (54) of the peripheral injector (52) to the downstream edge (71) of the central injector (50) being between 80 ° and 100 °, advantageously between 85 ° and 95 ° and in particular between 88 ° and 92 °. 5. - Trumpet (18) according to any one of the preceding claims, wherein the supply line (32) has an outer wall (44) converging along the main axis (A-A ') to the mixer (34), the primary flow injection assembly (30) having a peripheral septum (80) converging along the main axis (A-A ') to the mixer (34), the central axis (84) ) of injection being defined, in the median plane, on either side of the main axis (A-A ') by the bisector of the angle formed between the outer wall (44) and the peripheral wall (80 ). 6. - Trumpet (18) according to any one of the preceding claims, wherein the tubular channel (92) of the mixer (34) has a constant cross section. 7. - Trumpet (18) according to any one of the preceding claims, wherein the length of the tubular channel (92) of the mixer (34) is between 6 and 8 times its maximum transverse dimension. 8. - Trumpet (18) according to any one of the preceding claims, comprising a diffuser (36) disposed at the end of the mixer (34), the diffuser (36) defining a divergent downstream channel (94), the tubular channel (92) of the mixer (34) opening into the divergent downstream channel (94). 9. - Trumpet (18) according to claim 8, wherein the divergent downstream channel (94) diverges from a half-angle greater than 2 °, for example between 2.5 ° and 3.5 ° relative to l main axis (A-A '). The trumpet (18) according to any of the preceding claims, wherein at least one injector (50) of the primary flow injection assembly (30) is a supersonic injector. 11. - Device (16) for depression of an enclosure (12, 14) of an aircraft turbine engine (10) comprising: - a trunk (18) according to any one of the preceding claims; an assembly (20) for supplying a primary pressure stream, comprising a source (100) of pressurized fluid connected downstream to a primary flow injection assembly (30); an assembly (22) for supplying a secondary flow of oil, intended to be connected upstream to at least one chamber (12, 14) of the turbomachine (10), and connected downstream to the supply line (32); ). 12. - Device (16) according to claim 11, comprising a de-oiler (24) interposed between the enclosure (12, 14) and the supply line (32). 13. - turbomachine (10) aircraft, characterized in that it comprises: - at least one enclosure (12, 14) containing oil; - A device (16) according to any one of claims 11 or 12, connected to the enclosure (12, 14). 14. - Method of vacuuming an enclosure (12, 14) of an aircraft turbine engine (10), comprising the following steps: - providing a device (16) according to any one of claims 11 or 12, connected to the enclosure (12, 14); - feeding a primary stream under pressure through the primary flow supply assembly (20) to the injection assembly (30); - Driving the secondary flow by the primary flow through the assembly (22) for supplying the secondary flow, and through the supply line (32); mixing the primary stream and the secondary stream in the mixer (34); wherein in at least one median plane passing through the main axis (A-A '), on either side of the main axis (A-A'), the secondary flow is injected along a central axis (84 ) in the mixer (34) and in which, in the median plane, the angle (β) formed by the central axis (84) of injection, and the straight line (86) connecting the free edge downstream ( 54) of the primary flow injection assembly (30) at the upstream edge (42) of the mixer (34) is between 80 ° and 100 °.