Turbomachine nacelle equipped with an active ventilation vent
The turbomachine nacelle integrates rotating fins and rings to force air aspiration, addressing ventilation insufficiency at low speeds and maintaining cooling efficiency without increasing mass or size, ensuring independent operation.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-05-17
- Publication Date
- 2026-05-22
AI Technical Summary
Existing turbomachine nacelles face insufficient ventilation during low aircraft speeds, leading to overheating issues due to the chimney effect, and adding active ventilation systems increases nacelle mass and size, which is undesirable.
A turbomachine nacelle with integrated ventilation vents featuring rotating rings and fins that pivot or close to force air aspiration, utilizing a drive motor and return springs for orientation, allowing independent active ventilation without increasing mass or size.
Provides sufficient ventilation at all aircraft speeds with a low-mass and low-profile active system, ensuring cooling autonomy independent of turbomachine operation.
Smart Images
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Abstract
Description
Title of the invention: Turbomachine nacelle equipped with an active ventilation vent technical field
[0001] The present invention relates to the field of turbomachinery. It relates more particularly to the ventilation of a turbomachine nacelle. Previous technique
[0002] Turbomachine nacelles are usually equipped with a ventilation system for the turbomachine compartments to ensure a sufficiently cool thermal environment compatible with the operation of the turbomachine components in nominal mode. Indeed, overheating can lead to the deterioration or even the breakage of certain parts.
[0003] It is therefore common to implement air circulation through the nacelle, for example through the fan compartment and the central compartment. For a sufficient aircraft speed, outside air enters the compartment to be cooled through an inlet on the nacelle called a "scoop," circulates within the compartment to be cooled, and then exits the nacelle through an outlet including a grille also present on the nacelle.
[0004] When the aircraft is at insufficient speed to achieve ventilation as described above, for example during idle speed on the ground or engine shutdown, the thermal draft effect known as the "chimney effect" tends to push air from the cooling circuit outlet towards the scoop. In this situation, the ventilation may prove insufficient to ensure the cooling of the compartments.
[0005] To ensure sufficient ventilation of the compartments at all aircraft speeds, one solution is to add an active ventilation system to the passive ventilation circuit, such as a fan installed in the nacelle. However, such an active system increases the mass of the nacelle and the size of the ventilation system, while the available space in the nacelle compartments is already very limited.
[0006] It is therefore desirable to have a solution that provides sufficient ventilation of the nacelle at all aircraft speeds, while minimizing the bulk of the compartments. Description of the invention
[0007] To this end, the present invention proposes, according to one embodiment, a turbomachine nacelle comprising at least one ventilation vent, characterized in that each ventilation vent comprises: - a first ring defining a ventilation opening, - a plurality of fins extending into the ventilation opening of the first ring, each fin comprising a fixed section and a pivoting section, - a second rotating ring, the first ring being rotationally meshed with the second ring, - a drive motor for rotating the second ring, and in that, when rotating the second ring, the pivoting sections of the fins of the plurality of fins are oriented in a different direction from the direction of the fixed sections.
[0008] The invention thus proposes a nacelle equipped with a vent capable of forcing the aspiration of air into the nacelle when the aircraft has an insufficient speed to achieve passive ventilation of the nacelle and when the ventilation of the nacelle by chimney effect is not sufficient.
[0009] The invention also has the advantage of introducing a low-mass and low-profile active ventilation system. Indeed, by integrating an active fan function into the ventilation vent, the invention offers a highly integrated supplementary ventilation solution.
[0010] An additional advantage of the invention is the autonomy of the active ventilation achieved by the ventilation vent which with its independent motor can be implemented independently of the operation of the turbomachine.
[0011] According to a particular feature of the nacelle of the invention, the second ring is rotationally meshed with the first ring, with an angular displacement between the first ring and said second ring. The at least partial filling of this angular displacement during the rotation of the second ring causes the pivoting sections of the fins to orient themselves in a direction different from that of the fixed sections. The orientation of the pivoting sections of the fins is thus automatically achieved as soon as the second ring begins to rotate.
[0012] According to another particular feature of the nacelle of the invention, at least one return spring is interposed between the first and second rings, said at least one spring being compressed during the rotation of the second ring. Thus, when the rotation of the second ring is stopped, the return spring(s) are released to return the second ring to its initial position and orient the pivoting sections of the fins in the same direction as the fixed sections.
[0013] According to another particular feature of the nacelle of the invention, at least one pivoting section of a fin in the plurality of fins is connected to a mechanism of orientation said at least one pivoting section being connected to the pivoting sections of the other fins of the plurality of fins by a servo rod.
[0014] The invention proposes, according to another embodiment, a turbomachine nacelle comprising at least one ventilation vent, characterized in that each ventilation opening comprises: - a first ring defining a ventilation opening, - a plurality of first fins extending into the ventilation opening of the first ring, each fin being mounted on the first ring in a pivotal manner between an open position of the ventilation opening and a closed position of the ventilation opening, - a second rotating movable ring extending around the first ring, the second ring comprising an air intake ring having a lower ferrule, an upper ferrule and a plurality of second fins extending between the lower and outer ferrules, - a drive motor for rotating the second outer ring, and in that, when rotating the second ring, the first fins are oriented in the closing position of the ventilation opening so as to channel the air into the suction ring.
[0015] The invention thus proposes a nacelle equipped with a vent capable of forcing the aspiration of air into the nacelle when the aircraft has an insufficient speed to achieve passive ventilation of the nacelle and when the ventilation of the nacelle by chimney effect is not sufficient.
[0016] The invention also has the advantage of introducing a low-mass and low-size active ventilation system. Indeed, by integrating a compressor function into the ventilation vent, the invention offers a highly integrated supplementary ventilation solution.
[0017] An additional advantage of the invention is the autonomy of the active ventilation achieved by the ventilation vent which with its independent motor can be implemented independently of the operation of the turbomachine.
[0018] According to another particular feature of the nacelle of the invention, the second ring is rotationally meshed with the first ring, with an angular displacement between the first ring and said second ring. At least partial closure of this angular displacement during the rotation of the second ring causes the first fins to orient themselves in the closed position of the ventilation opening. The orientation of the pivoting sections of the fins is thus automatically achieved as soon as the second ring begins to rotate.
[0019] According to another particular feature of the nacelle of the invention, at least one return spring is interposed between the first ring and the second ring, said at least one spring being compressed during the rotation of the second ring. Thus, when the rotational drive of the second ring is stopped, the return spring(s) are released to return the second ring to its initial position and orient the pivoting sections of the fins in the same direction as the fixed sections.
[0020] According to another particular feature of the nacelle of the invention, at least one first fin of the plurality of first fins is connected to an orientation mechanism, said at least one first fin being connected to the other fins of the plurality of fins by a servo rod.
[0021] The invention also relates to an aircraft comprising at least one nacelle according to the invention. Brief description of the drawings
[0022] [Fig-1] Fig. 1 is a schematic cross-sectional view of a gondola of a turbomachine,
[0023] [Fig.2] Fig.2 is a schematic perspective view of a ventilation vent in passive configuration according to an embodiment of the invention,
[0024] [Fig.3] Fig.3 is a schematic perspective view of the ventilation vent of Fig.2 in active configuration,
[0025] [Fig.4] [Fig.4] is a schematic detail view of [Fig.2] showing the position of a mechanism for orienting a pivoting section of a ventilation vent fin in passive configuration,
[0026] [Fig.5] [Fig.5] is a schematic detail view of [Fig.3] showing the position of a orienting mechanism for a pivoting section of a ventilation vent fin in active configuration,
[0027] [Fig.6] Fig.6 is a schematic top perspective view of a ventilation vent in passive configuration according to another embodiment of the invention,
[0028] [Fig.7] [Fig.7] is a schematic perspective view from below of a ventilation vent in a passive configuration according to an embodiment of the invention,
[0029] [Fig.8] Fig.8 is a schematic top perspective view of a ventilation vent in active configuration according to one embodiment of the invention,
[0030] [Fig.9] [Fig.9] is a schematic perspective view from below of a ventilation vent in active configuration according to an embodiment of the invention,
[0031] [Fig. 10] [Fig. 10] is a schematic detail view of [Fig. 6] showing the position of a mechanism for orienting a pivoting section of a ventilation vent fin in passive configuration,
[0032] [Fig. 11] The [Fig. 11] is a schematic detail view of the [Fig.8] showing the position of a slewing mechanism of a pivoting section of a ventilation vent fin in active configuration. Description of the implementation methods
[0033] The invention is now described by means of figures, which are present for descriptive purposes to illustrate certain embodiments of the invention and which should not be interpreted as limiting the latter.
[0034] Figure 1 schematically illustrates a turbomachine 100 comprising, in a known manner, a fan 110 and an engine section comprising successively at least one low-pressure compressor stage 120, at least one high-pressure compressor stage 130, a combustion chamber 140, at least one high-pressure turbine stage 150, and at least one low-pressure turbine stage 160. The turbomachine 100 also comprises a nacelle 170. The nacelle 170 has an annular shape and defines an annular flow channel for a secondary flow. The nacelle 170 has an internal surface 170a defining said annular flow channel and an external surface 170b in contact with the ambient air. The nacelle includes, between the inner face and the outer face, an internal compartment 171, in which are housed equipment such as electronic accessory boxes, pumps and oil and fuel tanks, and others (not shown).The nacelle 170 is further equipped with a ventilation system comprising an air inlet 172 and an air outlet 173 fitted with a ventilation vent 200 located on the external surface 170b of the nacelle. The air inlet 172 may, for example, be a scoop. When the aircraft has sufficient speed, cooling air enters compartment 171 through the air inlet 172. After circulating through compartment 171, the cooling air is discharged through the air outlet 173, which includes the ventilation vent 200.
[0035] Figure 2 schematically illustrates a ventilation vent 200 in accordance with a embodiment of the invention. The ventilation vent 200 includes in particular a first ring 210, fins 220 and a second ring 230. The first ring 210 defines a ventilation opening 211 in which the fins 220 extend.
[0036] The second ring 230 is rotatable in a direction of rotation SR ([Fig. 3]). For this purpose, the second ring 230 is, for example, connected to the outer wall of the nacelle by bearings or any other means allowing rotation of the second ring. The second ring 230 is driven in rotation in the direction SR ([Fig.3]) by a drive motor (not shown in figures 2 and 3).
[0037] The first crown 210 is in rotational engagement with the second crown 230, the rotational drive of the second crown 230 causing the rotation of the first crown 210. In the example described here, the first crown 210 has on its external periphery teeth 212 which cooperate with teeth 232 present on the internal periphery of the second crown 230, which allows the first crown to engage with the second crown.
[0038] The fins 220 are mounted on the first ring 210. Each fin 200 has a fixed section 221 and a pivoting section 222.
[0039] Figure 2 illustrates the ventilation vent 200 in its passive configuration, that is, when the aircraft is at sufficient speed to perform passive ventilation of the nacelle by drawing fresh air from the inlet (scoop) of the ventilation circuit, the air being exhausted through the ventilation vent after circulating in the nacelle compartment. In this configuration, the ventilation vent 200 is fixed and the fixed 221 and pivoting 221 sections of each fin are oriented in the same first direction Dp
[0040] Figure 3 illustrates the ventilation vent 200 in its active configuration, i.e., when the aircraft is at an insufficient speed to achieve passive ventilation of the nacelle and when nacelle ventilation by chimney effect is insufficient. In this configuration, the ventilation vent 200 is driven in rotation in a direction SR while the pivoting section 222 of each fin 220 is oriented in a second direction D2 different from the first direction Dp. The pivoting section 222 of each fin 220 is pivotally mounted between the first ring 210 and / or the second ring 230, on the one hand, and the fixed section 221 of the fin in question, on the other hand.
[0041] The orientation of the pivoting sections 222 in the second direction D2 is achieved in the initial moments of the rotation of the second ring 230. In the example described here and illustrated in Figures 4 and 5, a first end 2220 of a pivoting section 222 of a fin 220 is connected to a first axis 2223, itself connected to the first ring 210, while a second end 2221 of the pivoting section 222 of the fin is connected to a second axis 2224, itself connected to the second ring 230. Also in the example described here and illustrated in Figures 2 and 3, only one pivoting section 222 of a fin from the plurality of fins 220, referred to as the "master fin," is thus connected by its ends 2220 and 2221 respectively to the first and second crowns 210 and 230, a servo rod 223 connecting the pivoting section of this fin to the sections pivoting 222 of the other fins 220 of the ventilation vent 200, called "servo fins". In this case, only the first end of the pivoting section 222 of the servo fins is connected to the first ring 210 by an axis similar to the first axis 2223, the second end of the servo fins being connected to the servo rod 223. According to an alternative, several fins or all of the fins can be master fins as described above.
[0042] The ventilation vent 200 is not limited to the orientation mechanism of the master fin(s) described here in relation to figures 4 and 5. Any other type of mechanism allowing the pivoting sections to be oriented in the direction D2 from the beginning of the rotation of the second ring can be considered.
[0043] In the passive configuration of the ventilation vent 200 as illustrated in [Fig.2], an angular deflection DA is present between the teeth 232 of the second ring 230 and the teeth 212 of the first ring 210 while the pivoting section 222 of the fin 220 is oriented along the first direction DI ([Fig.4]).
[0044] At the start of the rotation of the second ring 230 in the direction of rotation SR, the displacement of the teeth 232 of the second ring 230 in the angular deflections DA causes the pivoting section 222 to tilt in the second direction D2 as illustrated in [Fig.5].
[0045] Once the angular displacement is filled, the second ring 230 engages with the first ring 210, causing the first ring 210, and consequently the fins 220, to rotate in the direction of rotation SR. With the fixed sections 221 oriented in the first direction Di and the pivoting sections 222 oriented in the second direction D2, the fins 220 act as fan blades that draw an airflow Fl ([Fig. 1]) from outside the nacelle into the nacelle compartment to be cooled. It is thus possible to equip a nacelle with an active ventilation system when the aircraft is at an insufficient speed for passive ventilation of the nacelle and when the nacelle ventilation by the chimney effect is inadequate.
[0046] According to a particular feature, at least one return spring can be interposed between the first and second crowns 210 and 230 in order to replace the second crown in its initial position as illustrated in [Fig.2] and thus orient the pivoting sections 222 of the fins 220 in the same direction DI as that of the fixed sections 221 at the end of the rotation of the ventilation opening 200.
[0047] In the example described here, a return spring 240 is present in each angular travel DA between an adjacent tooth 212 and tooth 232. Thus, when the second ring 230 is rotated as illustrated in [Fig. 3], the return springs 240 are compressed between the teeth 212 and 232 during the The angular displacements DA are filled, with each angular displacement being partially filled here due to the presence of the springs 240. The springs 240 are thus maintained in a compressed position throughout the rotation of the ventilation vent 200. When the rotation of the second ring 230 is stopped, the springs 240 are released to return the second ring to its initial position and orient the pivoting sections 222 of the fins 220 in the direction Di as illustrated in [Fig. 2]. Any other arrangement of one or more return springs between the first and second rings, allowing the second ring and the pivoting sections of the fins to return to their initial position (passive configuration of the ventilation vent in [Fig. 2]), can be considered.
[0048] Figures 6 and 7 schematically illustrate a ventilation vent 300 according to another embodiment of the invention. The ventilation vent 300 includes, in particular, a first ring 310, first fins 320, and a second ring 330. The first ring 310 defines a ventilation opening 311 into which the first fins 220 extend.
[0049] The second ring 330 includes an air intake ring 331 comprising a lower ferrule 3310, an upper ferrule 3311 and second fins 3312 extending between the lower and outer ferrules.
[0050] The second ring 330 is rotatable in a direction of rotation SR (Figures 8 and 9). For this purpose, the second ring 330 is, for example, connected to the outer wall of the nacelle by bearings or any other means enabling the rotation of the second ring. The second ring 330 is driven in rotation in the direction of rotation SR by a drive motor (not shown in Figures 6 to 9).
[0051] The first crown 310 is rotationally meshed with the second crown 330, the rotation of the second crown 330 causing the first crown 310 to rotate. In the example described here, the first crown 310 has teeth 312 on its outer periphery that cooperate with teeth 332 on the second crown 330, thus enabling the first crown to mesh with the second crown. In the embodiment described here, the teeth 312 are located on the upper ferrule 3311 of the suction ring 331 of the second crown 330.
[0052] The first fins 320 are mounted on the first ring 310 in a pivoting manner between an opening position of the ventilation opening 311 (figures 6 and 7) and a closing position of the ventilation opening 310 (figures 8 and 9).
[0053] Figures 6 and 7 illustrate the ventilation vent 300 in its passive configuration, that is, when the aircraft has sufficient speed to achieve passive ventilation of the nacelle by drawing fresh air from the inlet (scoop) of the circuit ventilation, the air being expelled through the ventilation vent after circulating in the nacelle compartment. In this configuration, the ventilation vent 300 is fixed and the first fins 320 are oriented in the same first direction Db
[0054] . Figures 8 and 9 illustrate the ventilation vent 300 in its active configuration, i.e., when the aircraft has insufficient speed to achieve passive ventilation of the nacelle and when nacelle ventilation by chimney effect is insufficient. In this configuration, the ventilation vent 300 is driven in rotation in a direction SR while the first fins 320 are oriented in a second direction D2 parallel to the plane of the upper ferrule 3311. In this configuration, the first fins 320 together form a cover that obstructs the ventilation opening 310.
[0055] The orientation of the first fins 320 in the second direction D2 is achieved in the first moments of the rotation of the second ring 330. A mechanism for orienting the first fins similar to that already described in Figures 4 and 5 can be used here. Thus, as illustrated in Figures 10 and 11, a first end 3220 of a first fin 320 is connected to a first axis 3223 itself connected to the first ring 310, while a second end 3221 of the first fin 320 is connected to a second axis 3224 itself connected to the second ring 330, here by the upper ferrule 3311 of the suction ring 331 of the second ring 330.In the example described here and illustrated in Figures 6 and 7, only one of the first fins of the plurality of first fins 320, called the "first master fin," is thus connected by its ends 3220 and 3221 respectively to the first and second rings 310 and 330. A servo rod 323 connects this first master fin to the other fins 320 of the ventilation vent 300, called the "first servo fins." In this case, only the first end of the first servo fins is connected to the first ring 310 by an axis similar to the first axis 3223, the second end of the first servo fins being connected to the servo rod 323. According to a variant, several fins or all of the first fins can be first master fins as described above.
[0056] The ventilation vent 300 is not limited to the orientation mechanism of the master fin(s) described herein. Any other type of mechanism allowing the first fins to be oriented in the direction D2 from the start of the rotation of the second ring may be considered.
[0057] In its passive configuration as illustrated in [Fig. 6], an angular clearance Da is present between the teeth 332 of the second ring 330 and the teeth 312 of the first crown 310 while the first fins 320 are oriented along the first direction Di ([Fig.7]).
[0058] At the start of the rotation of the second ring 330 in the direction of rotation SR, the displacement of the teeth 332 of the second ring 330 in the angular deflections DA causes the first fins 320 to tilt in the second direction D2 as illustrated in [Fig.8].
[0059] Once the angular displacement is closed, that is, when the first fins close the ventilation opening 311, the rotation of the suction ring 331 of the second ring 330 acts as a compressor that draws an airflow Fl (Figures 1 and 9) from outside the nacelle towards the nacelle compartment to be cooled. It is thus possible to equip a nacelle with an active ventilation system when the aircraft is at an insufficient speed for passive ventilation of the nacelle and when the nacelle ventilation by the chimney effect is insufficient.
[0060] According to a particular feature, at least one return spring can be interposed between the first and second rings 310 and 330 in order to return the second ring to its initial position as illustrated in Figures 6 and 7 and thus orient the first fins 320 in the direction Dh
[0061] In the example described here, a return spring 340 is present in each angular travel DA between an adjacent tooth 312 and tooth 332. Thus, when the second ring 330 is rotated as illustrated in [Fig. 8], the return springs 340 are compressed between the teeth 312 and 332 as the angular travel DA is filled, the filling of each angular travel being partial here due to the presence of the springs 340. The springs 340 are thus maintained in a compressed position throughout the rotation of the ventilation opening 300. When the rotation of the second ring 330 is stopped, the springs 340 are released to return the second ring to its initial position and orient the first fins 320 in the direction Di as illustrated in Figures 6 and 7.Any other arrangement of one or more return springs between the first and second rings allowing the second ring and the first fins to be returned to their initial position (passive configuration of the ventilation opening in Figures 6 and 7) may be considered.
Claims
Demands
1. Turbomachine nacelle (100) comprising at least one ventilation vent (200), characterized in that each ventilation vent comprises: - a first ring (210) delimiting a ventilation opening (211), - a plurality of fins (220) extending into the ventilation opening of the first ring, each fin (220) having a fixed section (221) and a pivoting section (221), - a second ring (230) movable in rotation, the first ring (210) being in rotational mesh with the second ring (230), - a drive motor for rotating the second ring (230), and in that, when the second ring (230) is set into rotation, the pivoting sections (222) of the fins of the plurality of fins (220) are oriented in a direction (D2) different from the direction (DJ) of the fixed sections.
2. Nacelle according to claim 1, wherein the second ring (230) is rotationally engaged with the first ring (210) with an angular deflection (DA) between the first ring and the second ring, the at least partial filling of the angular deflection (DA) when the second ring (230) is rotated causing the pivoting sections (222) of the fins (220) to be oriented in a direction (D2) different from the direction (Di) of the fixed sections (221).
3. Nacelle according to claim 1 or 2, wherein at least one return spring (240) is interposed between the first ring (210) and the second ring (230), said at least one spring being compressed during the rotation of the second ring.
4. Nacelle according to any one of claims 1 to 3, wherein at least one pivoting section (222) of a fin in the plurality of fins (222) is connected to a steering mechanism, said at least one pivoting section being connected to the pivoting sections of the other fins in the plurality of fins by a servo rod (223).
5. A turbomachine nacelle comprising at least one ventilation vent (300), characterized in that each ventilation opening comprises: - a first ring (310) defining a ventilation opening (311), - a plurality of first fins (320) extending into the ventilation opening of the first ring, each fin (320) being pivotally mounted on the first ring (310) between an open position of the ventilation opening (311) and a closed position of said ventilation opening, - a second, rotatable ring (330) extending around the first ring (310), the second ring comprising an air intake ring (331) having a lower ferrule (3310), an upper ferrule (3311), and a plurality of second fins (3312) extending between the lower and outer ferrules, - a motor for rotating the second outer ring (330), and in that,When the second ring is rotated, the first fins (320) are oriented to close the ventilation opening so as to channel air into the suction ring.
6. Nacelle according to claim 5, wherein the second ring (330) is rotationally engaged with the first ring (310) with an angular deflection (DA) between the first ring and said second ring, the at least partial filling of the angular deflection (DA) when the second ring (330) is rotated causing the first fins (320) to be oriented in the closed position of the ventilation opening (311).
7. Nacelle according to claim 5 or 6, wherein at least one return spring (340) is interposed between the first ring (310) and the second ring (330), said at least one spring being compressed during the rotation of the second ring.
8. Nacelle according to any one of claims 5 to 7, wherein at least one first fin of the plurality of first fins (320) is connected to a steering mechanism, said at least one first fin being connected to the other fins of the plurality of fins by a servo rod (323).
9. Aircraft comprising at least one nacelle according to any one of claims 1 to 8.