Discharge device for an aircraft turbomachine with at least two flows.

Abstract

The present invention relates to a discharge device (3, 3') for an aircraft turbomachine with at least two flows, comprising a discharge duct (4) for an air flow provided with an inlet mouth (41) and an outlet mouth (42).This device is remarkable in that it comprises an inner ferrule segment (5), an outer ferrule segment (6) and a structural arm (8) fixed between the two, in that this arm (8) comprises two lateral flanks (81, 82), which delimit with the two ferrule segments (5, 6), an interior space (84) of the arm (8), at least one of the two flanks being pierced with a lateral air extraction opening (810), which opens into said interior space (84), in that the inner ferrule segment (5) is pierced with an air extraction orifice (50) opening into said interior space (84) and in that the air outlet mouth (42) is connected to the air extraction orifice (50), so as to put the air inlet mouth (41) into air communication with said lateral air extraction opening (810). Figure for abstract: Fig. 3.

Description

Title of the invention: Discharge device for an aircraft turbomachine with at least two flows. FIELD OF THE INVENTION

[0001] The invention lies in the field of aircraft turbomachines with at least two flows and more precisely in the field of discharge devices which make it possible to reduce the pressure downstream of the low pressure compressor of such turbomachines.

[0002] The present invention relates more particularly to a discharge device for an aircraft turbomachine with at least two flows as well as an aircraft turbomachine with at least two flows, equipped with such a discharge device.

[0003] Turbomachines with at least two flows designate in particular more particularly the turbomachines known under the name of “double flow turbomachine” or “triple flow turbomachine”. STATE OF THE ART

[0004] In the attached [Fig. 1], a diagram of a dual-flow turbomachine 1 with a longitudinal central axis X-X' can be seen. In the remainder of the description and claims, the terms "radially internal" and "radially external" refer to the radial position of an element relative to this axis.

[0005] Conventionally, this turbomachine comprises from upstream to downstream, relative to the direction of flow of the air and gases in the turbomachine, a ducted fan 10 called a "fan", a low pressure compressor 11, a high pressure compressor 12, a combustion chamber 13, a high pressure turbine 14 and a low pressure turbine 15.

[0006] The compressors 11 and 12, the combustion chamber 13 and the turbines 14 and 15 are housed in an internal casing 16 with a central axis X-X' and together form a gas generator 160. This internal casing 16 thus delimits a first air flow channel 161.

[0007] An external casing 100 or nacelle surrounds the blower 10 and the gas generator 160 and delimits with the internal casing 16, a second air flow channel 101.

[0008] Several structural arms 17 connect the radially external face 162 of the inner casing 16 to the radially internal face 102 of the outer casing 100. These arms 17 extend radially relative to the axis X-X' and are therefore arranged across the second air flow channel 101.

[0009] The air (flow F) sucked in by the blower 10 is divided between a primary air flow I, which circulates in the first air flow channel 161 of the gas generator 160 and a secondary air flow II, which circulates in the second air flow channel 101, which surrounds the gas generator. The two concentric flows meet downstream at the exhaust nozzle of the turbomachine.

[0010] Furthermore, such a turbomachine generally comprises a discharge device which makes it possible to avoid the phenomenon of pumping or stalling of the low pressure compressor 11.

[0011] In a compressor in general, and more specifically in the low pressure compressor 11, the air is compressed so that it leaves the compressor at a higher pressure than the inlet pressure.

[0012] However, similar to an airplane wing which can lose its lift and "stall" when it is at a high angle of attack and the airplane is at low speed, a compressor can experience a similar phenomenon.

[0013] Thus, at reduced flow rate, the compressor no longer pushes the air flow downstream and the air at high pressure downstream of the compressor empties towards the compressor inlet which is at a lower pressure. A reversal of the air flow direction may even occur. When sufficient air discharge has occurred, the compressor can return to normal operating conditions and restore the air flow in the correct direction (from upstream to downstream).

[0014] Such cyclical fluctuations in flow rate are called "pumping."

[0015] Such a phenomenon can however be destructive for the compressor blades and cause their destruction or at the very least cause vibrations in them.

[0016] In order to avoid these problems, it is known to install at least one discharge device 2, downstream of the low pressure compressor 11 and upstream of the high pressure compressor 12.

[0017] This discharge device 2 comprises an air discharge conduit 20, configured to be connected to a discharge valve 163, known by the English acronym VBV (for “Variable Bleed Valve”) or by the French acronym VDV (for “Vanne de déscharge variable”). This discharge valve 163 is positioned in the first air flow channel 161.

[0018] The radially inner end (or inlet mouth 201) of the air discharge duct 20 opens into the first air flow channel 161 and the radially outer end (or outlet mouth 202) of this same duct opens into the second air flow channel 101. The discharge valve 163 is installed at the radially inner end of the duct 20.

[0019] The discharge device 2 thus makes it possible, in situations of reduced flow rates and by controlling the opening or closing of the discharge valve 163, to be able to take or not take air downstream of the low pressure compressor 11 and to cause the pressure to drop there, so as to avoid backflow and therefore pumping of the compressor.

[0020] However, depending on the types of gas generator, it sometimes happens that a problem is encountered in integrating the discharge device into the turbomachine, due to a problem of size. Thus, and as shown in [Fig.l], the outlet mouth 202 of an air discharge duct 20 may be located at the leading edge of a structural arm 17. This particular positioning is problematic because the presence of the arm 17 in the second air flow channel 101 generates a stopping point and therefore a rise in static pressure near the outlet mouth 202. The discharge device then no longer fulfills its function and again, there is a risk of observing a pumping phenomenon of the low pressure compressor 11.

[0021] Currently, the only known solution to solve this problem consists of arranging the air discharge duct 20 so that its outlet mouth 202 is not located in the azimuthal zone “blocked” by the structural arm 17.

[0022] However, in certain cases, integration constraints do not allow the outlet mouth 202 to be shifted azimuthally to avoid the higher pressure zone located in front of the arm 17.

[0023] Furthermore, such an arrangement can prove costly due to the complex geometry that must then be given to the air discharge duct 20 and can result in a significant pressure loss due to the changes in direction imposed on the air in this modified duct.

[0024] The same problems can be encountered with a triple-flow turbomachine.

[0025] In the attached [Fig.2], we can see a diagram of a triple flow turbomachine 1' with central axis X-X'.

[0026] This turbomachine 1' has elements identical to those of the double-flow turbomachine, which will not be described again in detail and which bear the same numerical references.

[0027] The triple-flow turbomachine 1' differs from the double-flow turbomachine 1 in that it comprises an intermediate casing 18, with a central axis X-X', interposed radially between the internal casing 16 and the external casing 100.

[0028] The turbomachine 1' thus comprises a first air flow channel 161 of the gas generator 160, arranged as described in connection with the turbomachine 1, between the inner casing 16 and the central axis X-X', a second air flow channel 181, arranged between the inner casing 16 and the intermediate casing 18 and a third air flow channel 103, arranged between the intermediate casing 18 and the outer casing 100.

[0029] With this architecture, the air (flow F) sucked in by the blower 10 is divided between a primary air flow I (radially internal), which circulates in the first air flow channel 161, a secondary air flow II, which circulates in the third channel air flow 103 and a tertiary air flow III, which circulates in the second air flow channel 181.

[0030] As previously explained for the double-flow turbomachine 1, pumping phenomena of the low-pressure compressor 11 may also occur in the triple-flow turbomachine 1'.

[0031] Consequently, it would also be interesting to provide a discharge device, downstream of the low pressure compressor 11, allowing air to be discharged between the first air flow channel 161 and the second air flow channel 181. Presentation of the invention

[0032] The invention therefore aims to maintain the efficiency of the flow discharge device of the low-pressure compressor, despite the presence of a structural arm in the second air circulation channel, in which the secondary flow circulates in the case of a double-flow turbomachine or the tertiary flow in the case of a triple-flow turbomachine, and this, despite the fact that this arm generates a pressure rise at its leading edge, which is detrimental to the aerodynamic behavior of this discharge device.

[0033] To this end, the invention relates to a discharge device for an aircraft turbomachine with at least two flows, comprising a first discharge duct for an air flow, which comprises an air inlet mouth and an air outlet mouth.

[0034] According to the invention, this discharge device comprises an inner shell segment and an outer shell segment, which delimit between them an air flow channel, it comprises a structural arm fixed between said inner shell segment and said outer shell segment, this structural arm comprises two lateral flanks, which delimit with the inner shell segment and the outer shell segment, an interior space of the arm, at least one of the two lateral flanks of the structural arm is pierced with a first lateral air extraction opening, which opens into said interior space of the arm, the inner shell segment is pierced with an air extraction orifice, which also opens into said interior space of the arm, the air inlet mouth of the first discharge duct is configured to be able to be connected to a discharge valve of the turbomachine,and the air outlet of the first discharge duct is connected to the air extraction port, so as to put the air inlet of the first discharge duct into air communication with said first lateral air extraction opening.

[0035] Thanks to these features of the invention, a primary air flow which enters the discharge duct of the discharge device emerges on the lateral flank of the structural arm, then can flow into the air flow channel downstream of the arm, without disturbing the flow of air which arrives upstream of the arm, at the edge of attack of the latter, and without creating air turbulence. In other words, the air flow flows in a lateral zone of the structural arm not subject to the increase in static pressure which prevails at the leading edge of this arm.

[0036] According to other advantageous and non-limiting characteristics of the invention, taken alone or in combination:

[0037] -the discharge device comprises a second discharge duct for discharging an air flow, this second discharge duct comprising an air inlet and an air outlet, at least the other of the two lateral flanks of the structural arm is pierced with a second lateral air extraction opening, which opens into said interior space of the arm, the air inlet of the second discharge duct is configured to be able to be connected to a discharge valve of the turbomachine and the air outlet of the second discharge duct is connected to the air extraction orifice, so as to put the air inlet of the second discharge duct into air communication with said second lateral air extraction opening.

[0038] -the inner shell segment comprises at least one fixing lug, configured to allow the fixing of this inner shell segment on a radially inner wall of a second air flow channel of the turbomachine.

[0039] -the outer shell segment comprises at least one fixing flange, configured to allow the fixing of this outer shell segment on a radially outer wall of a second air flow channel of the turbomachine.

[0040] -the first discharge duct comprises a radially outer wall, a radially inner wall and two side walls, one of the side walls having a notch at its upper part and the first discharge duct is positioned in the structural arm, so that the radially outer edges respectively of the radially outer wall, of the other of the two side walls and of the radially inner wall are fixed in a gas-tight manner to the outer shell segment and that the notch is opposite the first lateral air extraction opening.

[0041] -the second discharge duct comprises a radially outer wall, a radially inner wall and two side walls, one of the side walls having a notch at its upper part, and the second discharge duct is positioned in the structural arm, so that the radially outer edges respectively of the radially outer wall, of the other of the two side walls and of the radially inner wall are fixed in a gas-tight manner to the outer shell segment and the notch of the side wall is opposite the second lateral air extraction opening.

[0042] The invention also relates to an aircraft turbomachine with at least two flows, comprising a first air flow channel and a second flow channel. air, a low pressure compressor and a high pressure compressor arranged in said first air flow channel, the turbomachine also comprising at least one discharge valve, mounted in the first air flow channel between the low pressure compressor and the high pressure compressor.

[0043] According to the invention, this turbomachine comprises at least one discharge device as mentioned above, the air inlet mouth of said first discharge duct of an air flow is connected to said at least one discharge valve, the air inlet mouth of said second discharge duct of an air flow if the latter is present, is connected to said at least one discharge valve, and said inner shell segment and said outer shell segment are connected respectively to the radially inner wall and to the radially outer wall of said second air flow channel, so that said first lateral air extraction opening of the structural arm and said second lateral air extraction opening if the second discharge duct of an air flow is present, open into said second air flow channel.

[0044] According to other advantageous and non-limiting characteristics of the invention:

[0045] - this turbomachine is a double-flow turbomachine and said second channel airflow is a channel in which the secondary air flow II circulates.

[0046] - this turbomachine is a triple flow turbomachine and said second channel airflow is a channel in which the tertiary air flow III circulates. DESCRIPTION OF FIGURES

[0047] Other characteristics, aims and advantages of the invention will emerge from the following description, which is purely illustrative and non-limiting, and which must be read in conjunction with the appended drawings in which:

[0048] [Fig. 1] is a diagram showing a dual-flow turbomachine.

[0049] [Fig.2] is a diagram representing a triple-flow turbomachine.

[0050] [Fig. 3] is a perspective view of a first embodiment of the device discharge according to the invention.

[0051] [Fig.4] is a perspective view of a second embodiment of the discharge device according to the invention.

[0052] [Fig.5] is a partial cross-sectional view of the discharge device of [Fig.4], taken along section line VV in [Fig.4].

[0053] [Fig.6] is a perspective view of the discharge conduit of the discharge device according to [Fig.3]. DETAILED DESCRIPTION OF THE INVENTION

[0054] A first embodiment of the discharge device according to the invention and referenced 3 will now be described in connection with [Fig.3].

[0055] Generally speaking, the discharge device 3 comprises a discharge duct 4 for an air flow, called the “first discharge duct”, an inner shell segment 5 and an outer shell segment 6, which delimit between them an air flow channel 7, and a structural arm 8, fixed between said inner shell segment 5 and said outer shell segment 6.

[0056] In the dual-flow turbomachine 1 of [Fig.l], the discharge device 3 is intended to replace the discharge device 2 of the state of the art. In other words, the duct 4 replaces the duct 20 and the structural arm 8 replaces the structural arm 17.

[0057] In the triple-flow turbomachine 1' of [Fig.2], the discharge device 3 according to the invention has been shown in the place it occupies.

[0058] It will also be noted that it is possible to have several discharge devices in accordance with the invention, distributed at several points on the circumference of the first channel 161.

[0059] The discharge device 3 has a longitudinal axis Xl-X' 1.

[0060] The discharge duct 4 comprises at its two ends, an air inlet mouth 41 and an air outlet 42.

[0061] The discharge duct 4 is advantageously bent, so as to allow the connection between the first air flow channel 161 and the second air flow channel 101, 181, which is located radially further out than the first channel. Preferably, the section of the air inlet mouth 41 and the section of the air outlet mouth 42 extend in two planes perpendicular to each other.

[0062] Preferably, this air inlet mouth 41 has a rectangular or substantially rectangular section.

[0063] The air inlet mouth 41 of said first discharge duct 4 is configured to be able to be connected to the discharge valve VDV 163 of the turbomachine 1 or 1', so that the opening of the valve 163 makes it possible to take air downstream of the low-pressure compressor 11 to introduce it into the duct 4 and that the closing of this valve interrupts this circulation of air.

[0064] The inner shell segment 5 and the outer shell segment 6 are each in the form of a plate, the contour of which is preferably square or rectangular or substantially square or rectangular in shape. This plate is preferably slightly curved, so that its concavity is oriented towards the duct 4 and that when the discharge device is in place in the turbomachine 1, 1', its concavity is oriented radially towards the central axis X-X' of the turbomachine.

[0065] The internal ferrule segment 5 is pierced with an air extraction orifice 50, preferably located in its central part.

[0066] Preferably, the outer shell segment 6 comprises at least one fixing flange 61 which allows the fixing of this segment 6 on the radially outer wall of the second air flow channel 101, 181.

[0067] If the turbomachine is a double-flow turbomachine 1, then this radially external wall of the second air flow channel 101 is the radially internal face 102 of the external casing 100. If the turbomachine is a triple-flow turbomachine 1', then this radially external wall of the second air flow channel 181 of the turbomachine 1 is the radially internal face 182 of the intermediate casing 18.

[0068] Preferably, the outer ferrule segment 6 comprises two fixing flanges 61, 62 located on either side, as shown in [Fig.4].

[0069] Preferably, this fixing flange 61 extends axially (along the axis Xl-X' 1) and it has for example the shape of an L-shaped profile as can be seen in the figures. The shape and dimensions of this flange 61 are adapted according to the shape and dimensions of the radially external wall of the second air flow channel 101, 181 to which it must be fixed.

[0070] Preferably, the internal shell segment 5 comprises at least one fixing lug 51 which allows the fixing of this segment 5 on the radially internal wall of the second air flow channel 101, 181.

[0071] Whether the turbomachine is a double or triple flow turbomachine, this radially internal wall of the second air flow channel 101, 181 is the radially external face 162 of the internal casing 16 of the turbomachine 1 or 1'.

[0072] Preferably, the internal ferrule segment 5 comprises two fixing lugs 51, 52 located on either side, as shown in [Fig.4].

[0073] Preferably, this fixing lug 51 extends axially (along the axis XI-X' 1) and it has for example the shape of an elongated profile with several different inclination portions, as can be seen in the figures. The shape and dimensions of this fixing lug 51 are adapted according to the shape and dimensions of the internal wall of the second air flow channel 101, 181 to which it must be fixed.

[0074] Once the inner ferrule segment 5 and the outer ferrule segment 6 are fixed respectively to the radially inner wall and to the radially outer wall of the second air flow channel, the air flow channel 7 of the device 3 constitutes a portion of this second air flow channel 101, 181.

[0075] The structural arm 8 ensures the relative positioning of the internal shell segment 5 with respect to the external shell segment 6.

[0076] This structural arm 8 comprises two radially opposed lateral flanks 81 and 82, (see [Fig.4]). They are curved and join upstream (relative to the direction of air circulation in channel 7) at a leading edge 83. They join downstream at a trailing edge (not visible in the figures).

[0077] These two lateral flanks 81 and 82 delimit with the internal ferrule segment 5 and the external ferrule segment 6, an internal space 84 of the arm.

[0078] At least one of the two lateral flanks 81 and 82 (for example the flank 81 in [Fig. 3]) is pierced with a first lateral air extraction opening 810, which opens into said interior space 84 of the arm 8 (and also into the channel 7).

[0079] Furthermore, the air extraction orifice 50 formed in the internal shell segment 5 also opens into the interior space 84 of the arm 8.

[0080] Furthermore, the air outlet 42 of the duct 4 is also connected to the air extraction orifice 50.

[0081] Referring to Figures 3 and 6, it can be seen that the discharge duct 4, which here has a rectangular cross-section, comprises a concave radially external wall 43, a convex radially internal wall 44 and two side walls 45 and 46.

[0082] The side wall 45 is the one which is located in the extension of the flank 81 of the arm 8. This side wall 45 has at its upper part (or radially external part) a notch 450. The side wall 46 does not have one.

[0083] Preferably, the discharge duct 4 is positioned in the structural arm 8, so that the upper (or radially external) edges 430 of the wall 43, 460 of the wall 46 and 440 of the wall 44 are fixed in a gas-tight manner (preferably welded) to the outer shell segment 6, and the notch 450 is opposite the first lateral air extraction opening 810.

[0084] The operation of the discharge device 3 is as follows:

[0085] When the discharge valve 163 opens, the primary air flow I enters in the air inlet mouth 41, rises in the discharge duct 4, passes through the notch 450 and the first lateral air extraction opening 810 to open into the air flow channel 7. Thus, the air inlet mouth 41 is in air communication with said opening 810.

[0086] However, thanks to this structural organization, the air of the primary flow I opens into the air flow channel 7 but in the downstream part of the structural arm 8, that is to say at a point distant from the leading edge 83 thereof. Thus, the air of the primary flow I leaving the discharge duct 4 does not disturb the flow of the secondary air flow II or tertiary air flow III circulating in the second air flow channel 101, 181.

[0087] A second embodiment of the discharge device according to the invention and referenced 3' will now be described in connection with figures 4 and 5.

[0088] This discharge device 3' differs from the device 3 in that it comprises a second discharge conduit 4', arranged next to the first discharge conduit 4.

[0089] Preferably, this discharge device 3' has a plane of symmetry P passing through the leading edge 83 of the structural arm 8 and through its trailing edge. The two conduits 4 and 4' are arranged on either side of this plane of symmetry P. The second conduit 4' is the mirror image of the first conduit 4 with respect to this plane of symmetry P.

[0090] The elements common to the discharge device 3 will not be described again in detail and bear the same numerical references.

[0091] The second discharge duct 4' comprises an air inlet mouth 41', an air outlet mouth 42', a concave radially outer wall 43', a convex radially inner wall 44' and two side walls 45' and 46'.

[0092] The side wall 45' is located in the extension of the flank 82 of the arm 8. The lateral flank 82 of the arm 8 is pierced with a second lateral air extraction opening 820, which opens into said interior space 84 of the arm 8 and into the channel 7.

[0093] The side wall 45' has a notch 450' at its upper part. The side wall 46' does not have one.

[0094] Furthermore, the air outlet mouth 42' of the second discharge duct 4' is also connected to the air extraction orifice 50.

[0095] Preferably, the second discharge duct 4' is positioned in the structural arm 8, so that the upper (or radially external) edges 430' of the wall 43', 460' of the wall 46' and 440' of the wall 44 are fixed in a gas-tight manner (preferably welded) to the outer shell segment 6, and the notch 450' is opposite the second lateral air extraction opening 820.

[0096] Finally, the air inlet mouth 41' is configured to be able to be connected to the discharge valve 163.

[0097] Thanks to this architecture, the air inlet mouth 41' of the second discharge duct 4' is in air communication with the second lateral air extraction opening 820, with the same beneficial effects as those previously explained in connection with the first discharge duct 4.

Claims

Claims

1. Discharge device (3, 3') for an aircraft turbomachine (1, 1') with at least two flows, comprising a first discharge duct (4) for an air flow, which comprises an air inlet (41) and an air outlet (42), characterized in that it comprises an inner shell segment (5) and an outer shell segment (6), which delimit between them an air flow channel (7), in that it comprises a structural arm (8) fixed between said inner shell segment (5) and said outer shell segment (6), in that this structural arm (8) comprises two lateral flanks (81, 82), which delimit with the inner shell segment (5) and the outer shell segment (6), an interior space (84) of the arm (8), in that at least one (81) of the two lateral flanks (81, 82) of the structural arm (8) is pierced with a first lateral air extraction opening (810), which opens into said interior space (84) of the arm,in that the inner shell segment (5) is pierced with an air extraction orifice (50), which also opens into said inner space (84) of the arm (8), in that the air inlet mouth (41) of the first discharge duct (4) is configured to be able to be connected to a discharge valve of the turbomachine (1, 1'), and in that the air outlet mouth (42) of the first discharge duct (4) is connected to the air extraction orifice (50), so as to put the air inlet mouth (41) of the first discharge duct (4) into air communication with said first lateral air extraction opening (810).,

2. Discharge device (3, 3') according to claim 1, characterized in that it comprises a second discharge duct (4') for an air flow, this second discharge duct (4') comprising an air inlet mouth (41') and an air outlet mouth (42'), in that at least the other (82) of the two lateral flanks (81, 82) of the structural arm (8) is pierced with a second lateral air extraction opening (820), which opens into said interior space (84) of the arm (8), in that the air inlet mouth (41') of the second discharge duct (4') is configured to be able to be connected to a discharge valve of the turbomachine (1, 1'), and in that the air outlet mouth (42') of the second discharge duct (4') is connected to the air extraction orifice (50), so as to put the air inlet mouth (41') of the second discharge duct (4') into air communication with said second lateral air extraction opening (820).

3. Discharge device (3, 3') according to claim 1 or 2, characterized in that the internal shell segment (5) comprises at least one fixing lug (51, 52), configured to allow the fixing of this internal shell segment (5) on a radially internal wall of a second air flow channel of the turbomachine (1, 1')-

4. Discharge device (3, 3') according to any one of the preceding claims, characterized in that the outer shell segment (6) comprises at least one fixing flange (61, 62), configured to allow the fixing of this outer shell segment (6) on a radially external wall of a second air flow channel of the turbomachine (1, 1').

5. Discharge device (3, 3') according to any one of the preceding claims, characterized in that the first discharge duct (4) comprises a radially outer wall (43), a radially inner wall (44) and two side walls (45, 46), -in that one of the side walls (45) has at its upper part a notch (450), -and in that the first discharge duct (4) is positioned in the structural arm (8), so that the radially outer edges (430, 460, 440) respectively of the radially outer wall (43), of the other of the two side walls (46) and of the radially inner wall (44) are fixed in a gas-tight manner to the outer shell segment (6) and that the notch (450) is opposite the first lateral air extraction opening (810).

6. Discharge device (3, 3') according to claim 2 or according to claim 2 and any one of the preceding claims, characterized in that the second discharge conduit (4') comprises a radially outer wall (43'), a radially inner wall (44') and two side walls (45', 46'),

7.

8. - in that one of the side walls (45') has a notch (450') at its upper part, -and in that the second discharge duct (4') is positioned in the structural arm (8), so that the radially external edges (430', 460', 440') respectively of the radially external wall (43'), of the other of the two side walls (46') and of the radially internal wall (44') are fixed in a gas-tight manner to the external shell segment (6) and that the notch (450') of the side wall (45') is opposite the second lateral air extraction opening (820). Aircraft turbomachine (1, 1') with at least two flows, comprising a first air flow channel (161) and a second air flow channel (101, 181), a low pressure compressor (11) and a high pressure compressor (12) arranged in said first air flow channel (161), the turbomachine (1, 1') also comprising at least one discharge valve (163), mounted in the first air flow channel (161) between the low pressure compressor (11) and the high pressure compressor (12), characterized in that it comprises at least one discharge device (3, 3') according to any one of the preceding claims, in that the air inlet mouth (41) of said first air flow discharge duct (4) is connected to said at least one discharge valve, in that the air inlet mouth (41') of said second air flow discharge duct (4') if the latter is present, is connected to said at least one discharge valve (163),and in that said inner shell segment (5) and said outer shell segment (6) are connected respectively to the radially inner wall and to the radially outer wall of said second air flow channel (101, 181), so that said first lateral air extraction opening (810) of the structural arm (8) and said second lateral air extraction opening (820) if the second air flow discharge duct (4') is present, open into said second air flow channel (101, 181). Aircraft turbomachine according to claim 7, characterized in that this turbomachine is a double-flow turbomachine (1) and in,

9. that said second air flow channel is a channel (101) in which the secondary air flow (II) circulates. Aircraft turbomachine according to claim 7, characterized in that this turbomachine is a triple flow turbomachine (1') and in that said second air flow channel is a channel (181) in which the tertiary air flow circulates.

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