• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an aircraft turbomachine comprising: - a fan duct (116) delimited by a wall (30a, 30b), and through which circulates a flow of air (F) from upstream to downstream and an air passage (158) arranged in the wall (30a, 30b) and having an air inlet opening (159) flush with the wall (30a, 30b), the air passage ( 158) being adapted to take a portion of the flow of air from the fan duct (116) through said air inlet opening (159). The turbomachine is characterized in that it comprises a flap (302) rotatably mounted on the wall (30a, 30b) of the fan duct (116), about an axis of rotation (304) disposed downstream an air inlet opening (159) between an open position in which the flap (302) partly closes the air inlet opening (159) and leaves the blower duct (116) free of said air inlet opening (159), and a closed position in which the flap (302) leaves the air inlet opening (159) free and partially closes the blower duct (116). downstream of said air inlet opening (159). Such displacement of the flap (302) makes it possible to choose the quantity of air entering the air passage (158).
    公开号:FR3029171A1
    申请号:FR1461579
    申请日:2014-11-27
    公开日:2016-06-03
    发明作者:Guillaume Clairet；Stephane Warnet
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aircraft turbomachine, and an aircraft comprising at least one such turbomachine. A turbofan engine generally comprises an air intake system for supplying air to an air user system of the aircraft such as, for example, the system for renewing and regulating the air pressure in a vehicle. cabin or de-icing systems. The air intake system draws hot air at the hot parts of the turbomachine and the cold air at the blower duct of said turbomachine. In order for the air temperature supplied to the user systems to remain below a limit temperature, the air intake system comprises a heat exchanger (PCE) in which the hot air exchanges calories with the cold air. The cold air is supplied to the exchanger via an air passage that fluidly connects the exchanger to the fan duct. The passageway includes a scoop-type air inlet opening at its upstream end. This inlet opening is flush with the wall of the fan duct to reduce its aerodynamic impact, including its screen. However, with such a geometry, an inlet opening can not capture a cold air flow rate sufficient for all cases of use of the air intake system of a turbomachine, in particular a turbomachine with high dilution rate (greater than 13: 1) where the temperature of the hot air taken can exceed 550 ° C (against 450 to 500 ° C for other turbomachines). In particular, this occurs for cases of extreme operation of the air intake system, that is to say when the demand of the air user systems is strong and is combined with a low engine speed. A suitable solution for such turbomachines to cover all cases of use of the air intake system would be to arrange a large air inlet opening extending widely in the blower duct and combined with a heat exchanger with a large exchange surface. This solution can not be retained because of the space constraints available in the turbomachine. There is therefore a need for means for varying the amount of cold air directed to the exchanger according to the needs of the air intake system and which do not have the disadvantages of the prior art. The invention aims to remedy this need and concerns an aircraft turbomachine comprising: - a fan duct delimited by a wall, and through which circulates a flow of air from upstream to downstream, and an air passage arranged in the wall and comprising an air inlet opening flush with the wall, the air passage being designed to take a part of the flow of air from the blower duct to through said air inlet opening, characterized in that the turbomachine comprises a flap mounted rotatably on the wall of the fan duct, about an axis of rotation disposed downstream of the inlet opening of the engine. air, between an open position in which the shutter partially closes the air inlet opening and leaves free the blower duct downstream of said air inlet opening, and a closed position in which the shutter leaves free the air inlet opening and partly closes the duct of ufflante downstream of said air inlet opening. Such a turbomachine thus comprises means for choosing the quantity of air entering the air passage according to the needs of the various aircraft apparatus. Advantageously, the face of the flap which is oriented towards the fan duct is at the edge of the wall of said fan duct, when the flap is in the closed position. Advantageously, the turbomachine further comprises locking means provided to take alternately a first locking position in which they lock the shutter in the closed position, and a second locking position in which they lock the shutter in the open position. Advantageously, the turbomachine further comprises an elastic means designed to move the flap to its open position, when the locking means are unlocked.
    [0002] Advantageously, the turbomachine further comprises a return means provided to constrain the shutter in the closed position when the locking means are unlocked. According to a particular embodiment of the invention, the resilient means is a first torsion spring, the biasing means is a second torsion spring, and the second torsion spring is oversized relative to said first torsion spring. The invention also proposes an aircraft comprising at least one turbomachine according to one of the preceding variants.
    [0003] The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in connection with the attached drawings, among which: FIG. . 1 shows an aircraft comprising a turbomachine according to the invention, FIG. 2 is a schematic view of a section of a turbomachine according to the invention, FIG. 3 is a schematic view showing the arrangement of an air intake system, FIG. 4 shows a shutter of the turbomachine according to the invention in a closed position, FIG. 5 shows the shutter of the turbomachine in an open position, FIG. 6 shows an elastic means for assisting the opening of the shutter of the turbomachine according to the invention, and FIG. 7 shows a return means for returning the flap to its closed position. Fig. 1 shows an aircraft 10 which comprises at least one turbofan engine 100 which is here fixed under a wing 12 of the aircraft 10 via a mast 14.
    [0004] Fig. 2 shows a section of the turbomachine 100 with a double flow which comprises an annular nacelle 102, centered on a longitudinal axis X, and surrounding a motor 104. In the direction of flow of a flow of air passing through the turbomachine 100 and materialized by the arrow F, the motor 104 comprises, centered on its longitudinal axis X, a fan 106, a body 108 and a nozzle 110. In the remainder of the description, the terms "upstream" and "downstream" are to be considered relative to the flow direction of the flow of air passing through the turbomachine 100. The body 108 comprises elements for rotating the fan 106 when the motor 104 is turned on.
    [0005] The turbomachine 100 further comprises, downstream of the fan 106, an annular intervein 112 concentric with the body 108. The nacelle 102 constitutes the outer casing of the turbomachine 100 and surrounds the intervein 112. The intervein 112 defines with the body 108, a first annular vein 114, and the intervein 112 delimits with the nacelle 102, a second annular vein, said fan duct 116. The annular veins 114 and 116 extend to the nozzle 110. The first vein 114 follows the body 108 and channels a flow of hot air HA, and the fan duct 116 channels a cold air flow CA from the fan 106.
    [0006] The engine 104 is fixed to the nacelle 102 by means of two diametrically opposed bifurcations 118 which make it possible to ensure mechanical cohesion of the turbomachine 100 and in particular connect the nacelle 102 and the interveine 112. The turbine engine 100 also comprises a system 150 for supplying air to one or more air user systems of the aircraft 10 and which is shown schematically in FIG. 3. The air intake system 150 comprises, arranged for example in the thickness of the interveine 112: - an air intake 156 for taking hot air HA in the first annular vein 114, - an air passage 158 opening into the fan duct 116 through an air inlet opening 159 and adapted to withdraw a portion of the flow of cold air CA from the fan duct 116 through the opening air inlet 159, - an exchanger 152 receiving at the inlet the hot air stream HA of the air intake 156 and the cold air flow CA of the air passage 158 which passes through it here perpendicularly, and an outlet of which is fluidly connected to at least one air user system 154, - a regulating valve 160, disposed downstream of the air passage 158, between said air passage 158 and the exchanger 152 and fluidly connected to an inlet of the exchanger 152 and whose opening angle is controlled according to the cold flow requirements of the exchanger 152 to ensure the supply of the adequate air temperature to the air user systems 154. The cold air CA is removed from the exchanger 152 either in the interveine 112 or directly outside the mast 14. In the heat exchanger, the hot air HA exchanges calories with cold AC air. The hot air HA is cooled and discharged through the outlet of the exchanger 152. FIG. 4 and FIG. 5 show a detail of the peripheral zone of the air passage 158. Although in the example described, the air passage 158 and the air inlet opening 159 are arranged in the interveine 112, they can also and without departing from the scope of the present invention, be arranged in the wall of the nacelle 102, that is to say more generally in the wall of the fan duct 116. In the embodiment of the invention shown in FIGS. . 4 and 5, the wall of the fan duct 116 comprises the wall 30b of the nacelle 102 and the wall 30a of the intervein 112.
    [0007] The air inlet opening 159 is flush with the wall 30a, 30b of the fan duct 116. The turbomachine 100 also comprises a regulation system 300 comprising a flap 302 rotatably mounted on the wall 30a of the duct. 116, about an axis of displacement 304 disposed downstream of the air inlet opening 159, between an open position (FIG 4) in which the flap 302 partially closes the inlet opening air 159 and leaves the fan duct 116 free of said air inlet opening 159, and a closed position (Fig. 5) in which the flap 302 leaves the air inlet opening free. and partially closes the fan duct 116 downstream of said air inlet opening 159.
    [0008] The mobility of the flap 302 thus makes it possible to vary the section of the air inlet 159 between a position with minimum opening of the air inlet 159 and a position with maximum opening of the air inlet 159 and of choose the amount of cold air that enters the air passage 158 and arrives at the inlet of the exchanger 152. The displacement axis 304 is perpendicular to the air flow F.
    [0009] To avoid the appearance of aerodynamic drag in the fan duct 116, the face of the flap 302 which is directed towards the fan duct 116 is flush with the wall 30a, 30b of said fan duct 116, when the flap 302 is in closed position. To lock the flap 302 in the open or closed position, the regulating system 300 also comprises locking means 306 which can be activated remotely and which are provided for alternately taking a first locking position (FIG. which they lock the shutter 302 in the closed position, and a second locking position (Figure 5) in which they lock the shutter 302 in the open position.
    [0010] The locking means 306 are activated for example by an on-board computer of the aircraft 10 according to various criteria such as, for example, the speed of the aircraft 10, and the needs of the air user systems 154.
    [0011] In the embodiment of the invention, shown in Figs. 4 and 5, the locking means 306 comprise a linear actuator 308, a latch 310 and a notch 312. The notch 312 is formed on the flap 302.
    [0012] The latch 310 has two teeth and is rotatably mounted about an axis of rotation parallel to the axis of movement 304 under the wall 30a, 30b of the fan duct 116. The linear actuator 308 is also fixed under the wall 30a, 30b of the fan duct 116 and its movable end is fixed to the latch 310 by means of a pivot connection.
    [0013] The linear actuator 308 alternately takes a first position or a second position. The first position corresponds to the first locking position, and the latch 310 is arranged so that one of its teeth fits in the notch 312 thus blocking the flap 302 in the closed position. The second position corresponds to the second locking position, and the latch 310 is arranged so that the other of its teeth fits in the notch 312 thus blocking the shutter 302 in the open position. The linear actuator 308 may be a pneumatic, electropneumatic or electromechanical actuator. The locking means 306 may take other forms. They may take the form of a linear actuator and two notches made in the flap 302, and depending on the position of the flap 302 the movable end of the actuator is housed in one or the other of the notches. Fig. 6 shows a resilient means 320 provided to help the opening of the flap 302 after unlocking the locking means 306. This resilient means 320 is provided to move the flap 302 to its open position (arrow 322), when the locking means 306 are unlocked. The elastic means 320 need not move the flap 302 to its open position, it is sufficient to lift the flap 302 slightly so that the air flow F takes in said flap 302 and opens it completely from the makes aerodynamic forces implemented.
    [0014] The elastic means 320 is here a first pre-constrained torsion spring mounted coaxially with the axis of displacement 304, one of the branches bears against an abutment 324 of the wall 30a, 30b and whose other branch is in position. bearing against a stop 326 of the shutter 302.
    [0015] Fig. 7 shows a return means 330 provided to return the flap 302 from the open position to the closed position (arrow 332), when the locking means 306 are unlocked. The return means 330 thus forces the flap 302 in the closed position when the locking means 306 are unlocked.
    [0016] The return means 330 may be a motor that pivots the flap 302 to its closed position. The return to the closed position is effected when the engine 104 is at a standstill, so there is no more air to circulate in the fan duct 116, and the flap 302 is no longer subjected to a force aerodynamic the binding in the open position. The return means 330 may then be a second pre-stressed torsion spring which is also mounted coaxial with the displacement axis 304 and which forces the flap 302 in the closed position when the locking means 306 are unlocked. The second torsion spring 330 then has a branch which bears against an abutment 334 of the wall 30a, 30b and another branch which bears against an abutment 336 of the flap 302. To overcome the resistance of the first torsion spring 320 the second torsion spring 330 is oversized relative to said first torsion spring 320 in order to overcome its resistance when returning to the closed position and pre-constraining it. An opening sequence of the shutter 302 comprises the following sequence of steps from the closed position of the flap 302 and when the locking means 306 are in the first locking position and the motor 104 is running: - unlocking locking means 306, - initiation of the opening of the flap 302 by action of the elastic means 320 counteracting the aerodynamic moment, - inversion of the aerodynamic moment which takes over the elastic means 320 and ensures the complete opening of the flap 302, during of this displacement, the aerodynamic moment forces the return means 330, and - locking the locking means 306 in the second locking position.
    [0017] At the end of a flight of the aircraft 10, a closing sequence of the flap 302 comprises the following sequence of steps from the open position of the flap 302 and when the locking means 306 are in the second locking position. : - extinction of the motor 104, - unlocking the blocking means 306, - return of the flap 302 to its closed position by action of the return means 330, during this movement, the elastic means 320 is pre-constrained, - locking locking means 306 in the first locking position and the system is then re-initialized.
    权利要求:
    Claims (7)
    [0001]
    CLAIMS1) Turbine engine (100) aircraft (10) comprising: - a fan duct (116) delimited by a wall (30a, 30b), and through which circulates a flow of air (F) from upstream to the downstream, and - an air passage (158) arranged in the wall (30a, 30b) and comprising an air inlet opening (159) flush with the wall (30a, 30b), the passage of air (158) being adapted to withdraw a portion of the air flow of the blower duct (116) through said air inlet opening (159), characterized in that the turbomachine (100) comprises a flap (302) rotatably mounted on the wall (30a, 30b) of the fan duct (116), about an axis of rotation (304) disposed downstream of the air inlet opening ( 159), between an open position in which the flap (302) partially closes the air inlet opening (159) and leaves the blower duct (116) free downstream of said air inlet opening (159), and a closed position in wherein the flap (302) leaves the air inlet opening (159) free and partially closes the blower duct (116) downstream of said air inlet opening (159).
    [0002]
    2) turbomachine (100) according to claim 1, characterized in that the face of the flap (302) which is oriented towards the fan duct (116) is flush with the wall (30a, 30b) of said fan duct (116). ) when the flap (302) is in the closed position.
    [0003]
    3) turbomachine (100) according to one of claims 1 or 2, characterized in that it further comprises locking means (306) provided to take alternately a first locking position in which they lock the flap (302) in the closed position, and a second locking position in which they lock the flap (302) in the open position.
    [0004]
    4) turbomachine (100) according to one of claims 1 to 3, characterized in that it further comprises an elastic means (320) provided for moving the flap (302) to its open position, when the locking means ( 306) are unlocked.
    [0005]
    5) turbomachine (100) according to one of claims 1 to 4, characterized in that it further comprises a biasing means (330) provided to constrain the flap (302) in the closed position when the locking means (306 ) are unlocked.
    [0006]
    6) turbomachine (100) according to claim 4 and claim 5, characterized in that the elastic means (320) is a first torsion spring, in that the return means (330) is a second torsion spring, and in that the second torsion spring (330) is oversized with respect to said first torsion spring (320).
    [0007]
    7) Aircraft (10) comprising at least one turbomachine (100) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    FR3029171B1|2016-12-30|
    US20160153309A1|2016-06-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    SE541609C2|2013-06-25|2019-11-12|Foersvarets Materielverk|Propulsion system for aircraft|
    EP3108312B1|2014-02-21|2019-09-25|Taleris Global LLP|Methods for determining performance of an air-conditioning system of an aircraft|US11258333B2|2019-07-29|2022-02-22|Aurora Flight Sciences Corporation|Propulsor system with integrated passive cooling|
    RU2729558C1|2019-09-16|2020-08-07|Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" |Compressor intermediate housing of turbojet|
    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-03| PLSC| Publication of the preliminary search report|Effective date: 20160603 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461579A|FR3029171B1|2014-11-27|2014-11-27|AIRCRAFT TURBOMACHINE HAVING A VARIABLE SECTION AIR INTAKE|FR1461579A| FR3029171B1|2014-11-27|2014-11-27|AIRCRAFT TURBOMACHINE HAVING A VARIABLE SECTION AIR INTAKE|
    US14/950,942| US20160153309A1|2014-11-27|2015-11-24|Aircraft turbomachine having an air inlet of variable section|
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