• 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 (30) comprising a wall, an air flow transiting, in use, via the fan duct; an air passage (120) arranged in the wall and having an air inlet aperture at the wall, the air passage being adapted to receive a portion of the air flow of the air duct; blower (30) through said opening; the turbomachine comprising an air intake box (300) arranged above the air inlet opening and fixed to the wall, said housing being arranged to intercept a portion of the air flow in the fan duct (30), said casing comprising successively, in the direction (F) of air flow, an upstream wall and then a downstream wall, the casing further comprising an upstream opening (301) and an opening downstream (302) respectively arranged on the upstream wall and the downstream wall, the inside of the housing being in fluid communication with the air inlet opening, the housing (300) further comprising a movable shutter means between A so-called open position, in which the closure means completely closes the downstream opening and completely releases the air inlet opening; and • a so-called closed position, in which the sealing means completely releases the downstream opening and completely closes the air inlet opening. The housing thus has a variable aerodynamic profile and adapted to the air requirements of a user system so as not to unnecessarily impact the aerodynamic performance of the turbomachine.
    公开号:FR3028289A1
    申请号:FR1460717
    申请日:2014-11-06
    公开日:2016-05-13
    发明作者:Stephane Warnet
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a turbofan engine aircraft with a double flow. More particularly, the invention relates to an air box covering an air inlet opening for supplying air to a heat exchanger of said turbomachine. A turbofan engine generally comprises an air intake system for supplying air to the aircraft's air user systems such as, for example, the system for renewing and regulating the air pressure. in the 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 aircraft air systems to remain below a limit temperature, the air intake system includes a heat exchanger (PCE) in which the cold and hot air streams are mixed. . 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 mileage. However, with such a geometry, an inlet opening can not capture a sufficient cold air flow for all cases of use of the air intake system of a turbomachine with a 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 the extreme operating cases of the air intake system, that is, when the demand for the air user systems is high 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 an air intake system adapted to all the engine speeds of such turbomachines. The invention aims to remedy this problem and relates to an aircraft turbomachine comprising a fan duct comprising a wall, a flow of air passing through, in use, via the fan duct; an air passage arranged in the wall and having an air inlet aperture at the wall, the air passage being adapted to receive a portion of the air flow of the fan duct through said opening; the turbomachine comprising an air intake box arranged above the air inlet opening and fixed to the wall, said housing being arranged to intercept a portion of the flow of air in the duct blower, said housing comprising successively, in the direction of air flow, an upstream wall and a downstream wall, the housing further comprising an upper wall, and two side walls parallel to each other, an upstream opening and an opening downstream being arranged respectively on the upstream wall and the downstream wall, the inside of the housing being hollow and provided with a fluid communication with the air inlet opening, the housing further comprising a movable shutter means between a so-called open position, in which the closure means completely closes the downstream opening and completely releases the air inlet opening; and a so-called closed position, in which the shut-off means completely releases the downstream opening and completely closes the air inlet opening. The air intake box according to the invention covering an air inlet opening thus functions as a scoop with a variable aerodynamic profile and adapted according to the needs of the air intake system so as not to impact unnecessarily. the aerodynamic performance of the turbomachine. In the open position, this scoop can cover the air requirements of the air intake system, especially in case of idling of the engine. The characteristics of the invention mentioned above, as well as others, will emerge more clearly on reading the following description of exemplary embodiments, said description being given in relation to the attached drawings, among which: FIG. 1 is a schematic view of a turbomachine seen in section along its longitudinal axis, the turbomachine comprising an air intake system provided with an air intake box according to one embodiment of the invention; FIG. 2 is a schematic view showing the arrangement of the various components of the air intake system of FIG. 1; - Figures 3a, 4a, 5a show, in a sectional view along its longitudinal axis, different configurations of the housing according to one embodiment of the invention; - Figures 3b, 4b, 5b respectively show, in a perspective view along its longitudinal axis, the configurations of the housing of Figures 3a, 4a, 5a; and - Figure 6 is a front view of the housing according to one embodiment of the invention.
    [0002] With reference to FIG. 1, a turbomachine 1 with a double flow comprises an annular nacelle 3, centered on a longitudinal axis X, and surrounding a motor 2. In the direction of flow of a flow of air passing through the turbomachine 1 and shown by the arrow F in FIG. 1, the engine 2 comprises, centered on its longitudinal axis X, a fan 5, a motor body 6 and a nozzle 7.
    [0003] In the remainder of the description, the terms "upstream" and "downstream" are to be considered in relation to the direction of flow of the air flow (arrow F) passing through the turbomachine 1. The body of the engine 6 comprises elements making it possible to turn the blower 5 when the engine 2 is turned on. The turbomachine 1, further comprises, downstream of the fan 5, an annular intervein 8 concentric with the body of the engine 6 and which defines with the latter an annular stream of hot air flow 20. The pod 3 constitutes the outer shell of the turbomachine 1 and surrounds interveine 8 with which it is concentric. The nacelle 3 thus delimits, with the interveine 8, an annular stream of cold air flow, said fan duct 30. The fan duct 30 extends to the nozzle 7. The engine 6 is fixed to the nacelle 3 by means of two diametrically opposite bifurcations 16, 17 which make it possible to ensure mechanical cohesion of the turbomachine 1 and in particular connect the nacelle 3 and the intervein 8 together. Referring to FIGS. 1 and 2, the turbomachine 1 comprises , in known manner, an air intake system 100 for supplying air to one or more air user systems 60. The air intake system 100 comprises, arranged for example in the thickness of the air interveine 8: an exchanger 107 mixing a flow of hot air H and a cold air flow F received as inputs to the exchanger. An outlet of the exchanger 107 is fluidly connected to at least one air user system 60, for example arranged in the thickness of the intervein 8. - At least one air intake 101 intended to take air hot H in the body of the engine 6 to send it to the inlet of the exchanger 107. - an air passage 120 made in the intervein 8 and connecting the fan duct 30 to the exchanger 107 and through which a flow cold air F sent to the inlet of the exchanger 107 transits. a control valve 105, located at a downstream end of the air passage 120, between the passage and the exchanger 107. Said valve is fluidly connected to an inlet of the exchanger 107 and its opening angle controlled by the exchanger 107 according to the needs of the air user systems 60.
    [0004] Referring to FIGS. 3 to 6, the air passage 120 is delimited by an air inlet 121 at its upstream end, various passage structures 122, and the regulation valve 105. The air inlet 121 comprises an inlet opening 121a formed between an upstream inlet edge 121b, a downstream inlet edge 121c and side walls (not shown) connecting the upstream and downstream inlet edges and extending along the longitudinal axis X In known manner, the air passage 120 is oriented at an angle α, for example a between 200 and 70 °, relative to the longitudinal axis X, to facilitate the flow of cold air F from the blower duct 30. The air intake system 100 further comprises an air intake box 300, for example of substantially parallelepiped shape, housed in the blower duct 30 and arranged above the blower duct 30. 121a air inlet opening. The housing 300 is hollow and is defined by an upstream wall 311, a downstream wall 312, an upper wall 313 and two side walls 314,315 (see Figure 6) parallel to each other. The housing 300 is fixed, for example by gluing or screwing, to the wall 3a of the fan duct 30 at these side walls, downstream and upstream. The dimensions of the housing 300 being greater than the size of the inlet opening 121a of the air passage 120, the latter is entirely between the upstream walls 311, downstream 312 and side of the housing 300. The air passage 120 thus opens in the case 300.
    [0005] The casing 300 has, successively, in the direction of the air flow F, two openings, respectively an upstream opening 301 arranged on its upstream wall 311 and a downstream opening 302 arranged on its downstream wall 312. The casing 300 also comprises a means of shutter and an actuator (not shown), for example pneumatic or electric type and installed in a housing 320 of the housing, said housing 320 being adjacent and fixed to the upstream wall 311 of the housing. The upstream and downstream openings are, for example, slots as in the example illustrated in FIGS. 3 to 6. A slot then makes the whole width (dimension along an axis perpendicular to the longitudinal axis X) of the upstream wall or downstream on which it is arranged. The closure means 303 takes the form of a substantially flat flap pivotally mounted inside the housing 300 and hinged to each of the two side walls. The shutter 303 is operable via the actuator connected to the shutter 303 by a mechanical connection element of the connecting rod type (not shown in the figures). The flap 303 is movable between two extreme positions: a so-called open position P1, represented in FIGS. 3a-b, in which it completely and sealingly closes the downstream opening 302 and completely releases the air inlet opening 121a. In this case, all the cold air F entering the housing 300 enters the air passage 120 (arrow A in Figure 3a); and a so-called closed position P2, shown in FIGS. 5a-b, in which it completely releases the downstream opening 302 and closes the air inlet opening 121a completely and in a sealed manner. In this case all the air entering the housing 300 is discharged through the downstream opening 302 (arrow S in Figure 5a).
    [0006] The housing 300 thus forms an air channel through which a cold air flow F transiting from upstream to downstream in the fan duct 300 engages in the housing 300 via the upstream opening 301 and escapes from the housing 300 via the downstream opening (arrow S in Figure 5a) and / or the air inlet opening 121a (arrow A in Figure 3a).
    [0007] When the turbine engine 1 is started, the operation of the air intake device 100, as described above, is as follows: the air is admitted into the turbomachine via the fan 5. Downstream of the fan 5, the cold air flow F flows into the fan duct 30 and part of the air flow enters the housing through its upstream opening 301.
    [0008] According to an air flow required by a user system 60, the controller commands the actuator to bring the flap 203 into one of the following positions: - the open position P1: the open position is adopted for performing a maximum cold air sampling in the extreme operating cases of the air intake system 100 that occur when the demand for the air user systems 60 is high and is combined with a low engine speed. It should be noted that it is in this position that the screen induced by the box 300 is maximum. - The closed position P2 in which no fluid is taken through the inlet opening 121a and the screen induced by the housing 300 is minimal. an intermediate position PI (FIGS. 4a-b) in which the downstream opening 302 and the air inlet opening 121a are partially opened by the shutter 303 so as to allow a part of the fluid entering the housing 300 to out through the downstream opening 302 (arrow S) and another part to enter the air passage 120 (arrow A). Such an intermediate position PI is suitable for most engine speeds (for example at cruising speed) of the turbomachine 1 to perform a partial sampling of fluid with a greater or lesser release of the inlet opening 121a as a function of flow required. In this position, the screen induced by the housing 300 depends on the angle of incidence of the shutter relative to the direction of the air flow (arrow F) passing through the fan duct. The advantage of the invention is that the housing 300 covering the air opening 121a operates as a scoop having a variable aerodynamic profile and adapted to the needs of the user systems 60 so as not to unnecessarily impact the aerodynamic performance of the aircraft. turbomachine 1, especially in cruising engine speed. Thus, in the normal operating cases of the air intake system 100 where the flap 303 is in the intermediate position PI or the closed position P2, the screen induced by the case 300 is respectively limited or zero compared to the case where the flap is in the Pl position.
    [0009] In the open position P1, the housing 300 acts as an air scoop that makes it possible to cover the air requirements of the air intake system 100, especially in the case of idling engine speed. Advantageously, the best compromise in term of halftone induced in the position P2 / performances as a scoop of air in the position P1 is reached when the height of the case 300, measured in a radial direction of the fan duct 30 between the wall 3a of the fan duct 30 and the upper wall 313, represents between 5 and 30% of the height of the fan duct 30 in this same direction. Preferably and with reference to FIG. 6, the upstream opening 301 is located at a height D of the surface of the wall 3a. The distance D is calculated so that the upstream opening 301 is located outside the boundary flow layer of the air in the fan duct 30 when the turbomachine 1 is operating (this boundary layer, where the flow air is turbulent, being located at the wall 3a). Thus, the flow of the air entering the housing 300 is laminar, which makes it possible to minimize the screen when the shutter is in the configuration P2 or in an intermediate configuration P1.
    [0010] In secondary advantage of the invention, it will be noted that when the flap 303 is in the position P2 and to a lesser extent in the position P1, the air passage 120 receives no or little airflow from the duct Thus, in these positions and when the control valve 105 is closed or quasi-closed, the invention makes it possible to limit the cavity acoustic resonance phenomena. The invention is also advantageous in terms of weight gain. Indeed, unlike a flush air opening known from the prior art, the invention allows a better recovery of the dynamic pressure which reduces the dimensions of the exchanger and therefore its mass. In addition, the installation of the actuator in the housing 320 has the effect of facilitating the maintenance and installation of the housing 300 since a defective actuator can be replaced by disassembling the housing 320, without having to separate the housing 300 of the wall 3a of the fan duct 30. Without departing from the scope of the present invention, the actuator could also be positioned in the thickness of the wall 3a or at the downstream wall 312 of the housing. Preferably, the upper wall 313 and the side walls 314,315 of the housing 300 are aerodynamically profiled and each have successively in the direction of the air flow F, a leading edge and a trailing edge. This arrangement makes it possible to further limit the screen induced by the box. In addition and although in the example described above the air intake system 100 and in particular the air passage 120 are arranged in the thickness of the intervein 8, these elements can also and without departing from the scope of the present invention, be arranged in the thickness of the nacelle 3 or in the mast 200 for fixing the turbomachine 1 to a wing of the aircraft (not shown). Thus, the invention as described can be arranged for suspended turbomachines via different types of masts, among which the masts of configurations called "core" (heart) since there is no grip of the intake box Air 300 in engine compartment compartment. An air intake box 300 according to the invention may be added in "retrofit" on a turbomachine provided with a flush air opening according to the prior art in order to cover the latter, in order to cover the needs air intake systems, solve cavity resonance problems and reduce the mass of the exchanger. The invention although described with an application to the air passage of the exchanger of a turbomachine also finds application for the scooping of the ventilation air of the engine compartments or equipment installed in engine compartment zone.
    权利要求:
    Claims (6)
    [0001]
    CLAIMS1) An aircraft turbomachine (1) comprising a fan duct (30) comprising a wall (3a), an air flow transiting, in use, via the fan duct; an air passage (120) arranged in the wall (3a) and having an air inlet opening (121a) at the wall (3a), the air passage being adapted to receive a portion of the air flowing air from the blower duct (30) through said opening; characterized in that the turbomachine comprises an air intake box (300) arranged above the air inlet opening (121a) and fixed to the wall (3a), said housing being arranged to intercept a portion of the flow of air in the blower duct (30), said box comprising successively, in the direction (F) of air flow, an upstream wall (311) and a downstream wall (312) ), the housing further comprising an upper wall (313), and two mutually parallel lateral walls, an upstream opening (301) and a downstream opening (302) being respectively arranged on the upstream wall and the downstream wall, the inside the housing being hollow and provided with fluid communication with the air inlet opening (121a), the housing (300) further comprising a closing means (303) movable between: - a position (P1) said open, in which the closure means completely closes the downstream opening (302) and completely releases the opening e air inlet (121a); and a so-called closed position (P2), in which the closure means completely releases the downstream opening (302) and completely closes the air inlet opening (121a).
    [0002]
    2) turbomachine according to claim 1, characterized in that the dimensions of the housing (300) are greater than the size of the inlet opening (121a) of the air passage (120), the inlet opening ( 121a) is entirely between the upstream (311), downstream (312) and lateral walls of the housing (300).
    [0003]
    3) turbomachine according to claim 1 or claim 2, characterized in that the closure means (303) is a flap hinged to each of the side walls of the housing (300).
    [0004]
    4) Turbine engine according to claim 3, characterized in that the housing comprises an actuator mechanically connected to the flap (303) and configured to move said flap (303) between said two extreme positions (P1, P2).
    [0005]
    5) turbomachine according to claim 4, characterized in that the housing comprises a housing (320) adjacent to its upstream wall (311) and wherein is housed the actuator.
    [0006]
    6) turbomachine according to any one of the preceding claims, characterized in that, in a radial dimension, the height of the housing is between 5 and 30% of the height of the fan duct (30).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20160131038A1|2016-05-12|
    US10001062B2|2018-06-19|
    FR3028289B1|2019-12-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4250703A|1979-03-15|1981-02-17|Avco Corporation|Swinging door particle separator and deicing system|
    WO1982002181A1|1980-12-29|1982-07-08|Co Boeing|Auxiliary power unit scoop and inlet|
    GB2308866A|1996-01-04|1997-07-09|Rolls Royce Plc|Ducted fan gas turbine engine with secondary duct|
    DE102011011879A1|2011-02-21|2012-08-23|Airbus Operations Gmbh|Cooling air inlet, engine bleed air system and method for operating a cooling air inlet|
    US4782658A|1987-05-07|1988-11-08|Rolls-Royce Plc|Deicing of a geared gas turbine engine|
    US7014144B2|2003-07-22|2006-03-21|Honeywell International, Inc.|Dual action inlet door and method for use thereof|
    DE102009011635A1|2009-03-04|2010-09-09|Rolls-Royce Deutschland Ltd & Co Kg|Air guide element of a running gap adjustment system of an aircraft gas turbine|US10040560B2|2015-09-30|2018-08-07|The Boeing Company|Trailing edge core compartment vent for an aircraft engine|
    US10189572B2|2016-05-02|2019-01-29|The Boeing Company|Systems and methods for preventing ice formation on portions of an aircraft|
    GB201705802D0|2017-04-11|2017-05-24|Rolls Royce Plc|Inlet duct|
    FR3080889B1|2018-05-03|2020-08-07|Airbus Operations |AIRCRAFT PROPULSION KIT INCLUDING A COLD AIR INTAKE DEVICE WITH VARIABLE AERODYNAMIC PROFILE|
    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-13| PLSC| Publication of the preliminary search report|Effective date: 20160513 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-11-23| PLFP| Fee payment|Year of fee payment: 5 |
    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
    FR1460717A|FR3028289B1|2014-11-06|2014-11-06|AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE BOX WITH VARIABLE AERODYNAMIC PROFILE|
    FR1460717|2014-11-06|FR1460717A| FR3028289B1|2014-11-06|2014-11-06|AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE BOX WITH VARIABLE AERODYNAMIC PROFILE|
    US14/928,302| US10001062B2|2014-11-06|2015-10-30|Aircraft turbine engine comprising an air intake housing with a variable aerodynamic profile|
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