• 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 a nacelle (11) for a propulsion unit comprising: - at least one scoop (2) opening towards the outside air, and - a channel (3) supplying outside air, from the scoop (2), two conduits (13, 14) which separate by forming a separation spout (8), characterized in that it comprises: - at least one exchanger (7) configured to cool a flow (12) of incoming air, said exchanger (7) being disposed at the separation nozzle (8), - the outside air flowing from the scoop (2) to the two ducts (13, 14) for cooling the flow (12) of air entering the exchanger (7). The invention also relates to a method of mounting an exchanger in the nacelle.
    公开号:FR3018503A1
    申请号:FR1452091
    申请日:2014-03-13
    公开日:2015-09-18
    发明作者:Sara Bustillo；Maria Natal
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] Field of the Invention The invention relates to a nacelle for a propulsion unit, said nacelle comprising an exchanger configured to cool an air flow.
    [0002] Presentation of the Prior Art It is known to install in a turbomachine an air / air exchanger type SACAC ("Surface Air Cooled Air Cooler") for cooling a flow of air, for example taken at the output of a compressor. As illustrated in FIG. 1, the exchanger 52 receives a hot air flow 51 (typically of a temperature greater than 200 ° C.) coming from the outlet of a high pressure compressor 50. At the outlet of the exchanger 52, the air flow 53 is cooled and has a temperature below 200 ° C. In the case of turbofans, the exchanger is disposed on the secondary vein, so as to cool the air flow to the exchanger with the air of the secondary vein. In the case of turboprops, the equivalent of the secondary vein is the air that passes around the nacelle and is accelerated by the propellers. The exchanger can therefore be disposed outside the nacelle. However, this solution causes interference with the flow around the nacelle, which increases the drag. This solution is therefore not satisfactory. In order to overcome these drawbacks, the invention proposes a nacelle for a propulsion unit comprising at least one scoop opening out to the outside air, a channel supplying outside air, from the scoop, two ducts which separate forming a separator nozzle, characterized in that it comprises at least one exchanger configured to cool an incoming air flow, said exchanger being arranged at the separation nozzle, the outside air flowing from the scoop to the two ducts for cooling the air flow entering the exchanger.
    [0003] The invention is advantageously completed by the following features, taken alone or in any of their technically possible combination: the exchanger comprises a frame, and a plurality of fins disposed on one or more faces of the frame; the exchanger is attached to at least one of the ducts by at least one plate; the ducts have a wall of composite material and the plate is metallic; the frame has a tapered profile at its leading edge; the flow of air entering the exchanger is taken at the outlet of a compressor of the turbomachine; The invention also relates to a turboprop engine comprising a nacelle as described and a turbomachine. In one embodiment, an air inlet of the exchanger is connected to the output of a compressor of the turbomachine, in order to cool the air flow taken at the outlet of the compressor. The invention also relates to a method of mounting an exchanger receiving a flow of air to be cooled, in a turbomachine comprising a nacelle in which is provided at least one scoop opening to the outside air, a channel supplying outside air, from the scoop, two ducts which separate to form a separation spout, characterized in that it comprises the steps of making an opening in the separation spout, introducing the exchanger through the opening, and arranging it at the separation spout so that the exchanger separates the two ducts. The method may further include the step of attaching the exchanger to one of the conduits via a plate. The invention has many advantages.
    [0004] The invention makes it possible to cool an air flow by an exchanger in a simple and effective manner.
    [0005] In particular, it makes it possible to reuse a flow of cold air circulating in the ducts of the propulsion unit in order to cool the flow of air entering the exchanger. In addition, the invention makes it possible at the same time to solve the problem of frost being able to be created in certain zones of the propulsion unit, in particular on the separation spouts of the ducts, and to cool a flow of hot air passing through a heat exchanger of the propulsion system. The invention therefore makes it possible to dispense with the laying of numerous ducts that would have been necessary to remove the frost and to cool the flow of air entering the exchanger. Other features and advantages of the invention will become apparent from the description which follows, which is purely illustrative and nonlimiting, and should be read with reference to the accompanying drawings in which: - Figure 1 is a representation of the operation an air / air exchanger in a turbomachine; - Figure 2 is a representation of a propulsion unit according to the invention, in side view; - Figure 3 is a representation of a propulsion unit according to the invention, seen from above; - Figure 4 is a representation of the positioning of the exchanger at the separation nozzle of the two ducts; - Figure 5 is a representation of the exchanger; - Figure 6 is a representation of Figure 4 in side view; - Figure 7 is a representation of Figure 4 in top view; - Figure 8 is a representation of the attachment of the exchanger to a conduit via a plate; - Figure 9 is a representation of an embodiment of a method of mounting an exchanger.
    [0006] DETAILED DESCRIPTION FIGS. 2 and 3 show a propulsion unit 1 of an aircraft. In these Figures, the propulsion unit 1 is a turboprop. The propulsion unit 1 comprises a turbomachine and a nacelle 11 in which is provided at least one scoop 2 opening to the outside air. During the displacement of the aircraft, the outside air enters the nacelle 11 through the scoop 2. In general, the scoop 2 is placed at 12 o'clock (azimuthal angle). A channel 3 is connected to the scoop 2 and is supplied with outside air.
    [0007] This channel 3 feeds two ducts 13, 14 in the nacelle 11, which separate forming a beak 8 separation. The two ducts 13, 14 each constitute a separate extension of the channel 3. The separation nozzle 8 is at the junction between the channel 3 and the inlet of the two ducts 13, 14. It defines the separation between the entrances of the two ducts 13 14. This separating spout 8 can be flat or protrude. After the separation nozzle 8, the conduits 13, 14 are separated by a slot 30 and are therefore distinct. The ducts 13, 14 are for example respectively a duct supplying cold air equipment 31 (which is for example the cooler "Air Cooled Oil Cooler", which cools the oil of the "Variable Frequency Generator" or current generator to variable frequency), and a conduit that supplies cold air equipment 32 (which is for example the "Precooler" or upstream cooler).
    [0008] The nacelle 11 further comprises at least one exchanger 7 configured to cool a stream 12 of air entering said exchanger 7. This is for example a stream 12 of air taken at the outlet of a compressor of the turbomachine of the propulsion system. In this case, an air inlet of the exchanger is connected to the output of a compressor of the turbomachine, in order to cool the air flow taken at the outlet of the compressor. Once cooled, the air flow can in particular be sent to equipment that controls pneumatic valves.
    [0009] The exchanger 7 is disposed at the separation nozzle 8. Therefore, the outside air entering the scoop 2, and passing through the channel 3 and the two ducts 13, 14 flows around the exchanger 7. The air flow 12 entering the exchanger 7 is cooled by the circulation of the outside air flowing around the exchanger 7. This judicious configuration makes it possible to reuse existing conduits 13, 14 in order to cool the flow of air entering the exchanger 7. It is therefore not possible to no need to recreate a new flow of cold air to cool the air flow 12 entering the exchanger 7.
    [0010] The structure of the exchanger 7 is cooled on both sides by the air flowing to the duct 13 and the air flowing to the duct 14. With this installation, the size of the exchanger 7 is reduced. In addition, the separation nozzle 8 is generally subjected to frost formation. Thanks to the judicious arrangement of the exchanger 7 at the separation nozzle 8, the frost is removed, and it is not necessary to set up additional devices to fight against the appearance of frost, such as ducts. defrosting. In one embodiment, the exchanger 7 comprises a frame 16 and a plurality of fins 18 disposed on one or more faces of the frame 16.
    [0011] One or more pipes 23 cause the stream 12 of air to be cooled in the frame 16. The air stream 12 leaves the frame 16, on the same side or on another side, via at least one other pipe 24, with a lower temperature. The fins 18 can channel and guide the outside air around the frame 16 of the exchanger 7, which improves the heat exchange, and thus the cooling efficiency. Advantageously, the fins 18 are disposed on both sides of the frame 16. They extend parallel to each other, and are parallel to the direction of flow of the outside air.
    [0012] In an exemplary embodiment, the frame 16 has a tapered profile at its leading edge 21. This configuration makes it possible to improve the flow of outside air around the frame 16.
    [0013] According to one embodiment, the turbomachine is a turboprop. The attachment of the exchanger 7 may for example be achieved by means of at least one plate 19. The plate 19 is, on the one hand, attached to one of the ducts 13, 14, and, secondly, to the exchanger 7. The fixing is for example carried out via screws 35. In general, the conduits 13, 14 have a wall of composite material. The frame 16 is metallic. In order to bond the frame 16 to at least one of the conduits, the plate 19 may be metallic.
    [0014] Referring to FIG. 9, a method of mounting the exchanger 7 in the nacelle 11 of the propulsion unit 1 is described. The method comprises the step 51 of making an opening in the separation nozzle 8 separating the two ducts 13, 14. The section and the dimensions of the opening are selected so as to correspond to the section and the dimensions of the exchanger 7. For example, the opening has a rectangular section, whose surface allows to leave passing the exchanger 7 with the fins 18. In step S2, the exchanger 7 is introduced through the opening and is disposed (step S3) at the separation nozzle 8 so that the exchanger 7 separates the two ducts 13, 14. The exchanger 7 then plays the role of separation nozzle between the two ducts 13, 14. Finally, the frame 16 of the exchanger 7 is attached to at least one of the ducts 13, 14 through at least one plate 19.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. Nacelle (11) for propulsion unit comprising: - at least one scoop (2) opening to the outside air, - a channel (3) supplying outside air, from the bailer (2), two ducts (13, 14) which separate in forming a separation spout (8), characterized in that it comprises: at least one exchanger (7) configured to cool a flow (12) of incoming air, said exchanger (7) being disposed at level of the spout (8) of separation, - the outside air flowing from the scoop (2) to the two ducts (13, 14) for cooling the flow (12) of air entering the exchanger (7) .
    [0002]
    2. Nacelle (11) according to claim 1, wherein the exchanger (7) comprises: - a frame (16), and - a plurality of fins (18) disposed on one or more faces of the frame (16).
    [0003]
    3. nacelle (11) according to one of claims 1 or 2, wherein the exchanger (7) is attached to at least one of the conduits (13, 14) by at least one plate (19).
    [0004]
    4. Nacelle (11) according to claim 3, wherein the ducts (13, 14) have a wall of composite material and the plate (19) is metallic.
    [0005]
    5. Nacelle (11) according to claim 2, wherein the frame (16) has a tapered profile at its edge (21) of attack.
    [0006]
    6. Turboprop (1) comprising a turbomachine and a nacelle (11) according to one of claims 1 to 5.
    [0007]
    7. Turboprop (1) according to claim 6, wherein an air inlet of the exchanger (7) is connected to the output of a compressor of the turbomachine, to cool the air flow taken out of the compressor.
    [0008]
    8. A method of mounting an exchanger (7) receiving a flow of air to be cooled, in a nacelle (11) propulsion assembly comprising: - at least one scoop (2) opening to the outside air, and - a channel (3) supplying outside air, from the scoop (2), two ducts (13, 14) which separate to form a separation spout (8), characterized in that it comprises the steps of: practicing (S1) an opening in the separation spout (8), - introducing (S2) the exchanger (7) through the opening, and arranging it (S3) at the separation spout (8) so the exchanger (7) separates the two ducts (13, 14).
    [0009]
    9. The method of claim 8, comprising the step (S4) of fixing the exchanger (7) to one of the ducts (13, 14) via a plate (19).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20170021937A1|2017-01-26|
    FR3018503B1|2017-10-13|
    WO2015136210A1|2015-09-17|
    US10384793B2|2019-08-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2864996A1|2004-01-13|2005-07-15|Snecma Moteurs|SYSTEM FOR COOLING HOT PARTS OF AN AIRCRAFT ENGINE, AND AIRCRAFT ENGINE EQUIPPED WITH SUCH A COOLING SYSTEM|
    EP1882824A2|2006-07-19|2008-01-30|United Technologies Corporation|Lubricant cooling exchanger dual intake duct|
    EP2348211A1|2010-01-26|2011-07-27|Airbus Operations |Aircraft propulsion unit with a cooler installed at engine nacelle|
    FR2955616A1|2010-01-26|2011-07-29|Airbus Operations Sas|COOLING DEVICE FOR AN AIRCRAFT PROPELLER|
    US20130219854A1|2012-02-24|2013-08-29|Daniel T. Alecu|Air-cooled oil cooler for turbofan engine|
    FR2987602A1|2012-03-02|2013-09-06|Aircelle Sa|TURBOMOTEUR NACELLE EQUIPPED WITH A HEAT EXCHANGER|
    EP2701176B1|2012-08-24|2018-04-18|Siemens Aktiengesellschaft|Fuse element|
    EP2929162B1|2012-12-10|2019-06-05|United Technologies Corporation|Gas turbine engine with dual filtration particle separator|
    JP6157910B2|2013-04-16|2017-07-05|Nok株式会社|Manufacturing method of base material integrated gasket|US10858115B2|2018-02-19|2020-12-08|Pratt & Whitney Canada Corp.|Aircraft with wheel well between heat exchangers of engine assembly|
    US10745142B2|2018-02-19|2020-08-18|Pratt & Whitney Canada Corp.|Aircraft with wheel well between cooling duct outlets|
    US10870493B2|2018-02-19|2020-12-22|Pratt & Whitney Canada Corp.|Aircraft with engine assembly mounted to wheel well|
    CA3132276A1|2019-03-01|2020-09-10|Pratt & Whitney Canada Corp.|Cooling system configurations for an aircraft having hybrid-electric propulsion system|
    FR3094754B1|2019-04-03|2021-03-12|Safran Nacelles|Aircraft nacelle comprising at least one heat exchanger|
    法律状态:
    2016-02-25| PLFP| Fee payment|Year of fee payment: 3 |
    2017-03-06| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452091A|FR3018503B1|2014-03-13|2014-03-13|NACELLE COMPRISING AN EXCHANGER FOR COOLING A FLOW OF AIR|FR1452091A| FR3018503B1|2014-03-13|2014-03-13|NACELLE COMPRISING AN EXCHANGER FOR COOLING A FLOW OF AIR|
    PCT/FR2015/050586| WO2015136210A1|2014-03-13|2015-03-10|Nacelle comprising an exchanger for cooling a stream of fluid|
    US15/125,783| US10384793B2|2014-03-13|2015-03-10|Nacelle comprising an exchanger for cooling a stream of fluid|
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