• 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:
    An aircraft turbomachine (10) comprising a nacelle and a motor (12) comprising at least one flow passage of an air flow, characterized in that a heat exchanger (20) of the pre-cooler type for the the air supply of the aircraft is mounted in the nacelle, this exchanger comprising a primary circuit whose input is connected to means for withdrawing compressed air from the engine and the outlet is connected to means for supplying air of the aircraft and a secondary circuit supplied with air taken from said air flow.
    公开号:FR3015573A1
    申请号:FR1362956
    申请日:2013-12-19
    公开日:2015-06-26
    发明作者:Jeremy Edmond Fert；Vulpillieres Eric De；Julien Pavillet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to an aircraft turbomachine, this turbomachine comprising a pre-cooler heat exchanger. STATE OF THE ART In an aircraft, it is necessary to have hot air available in order to perform certain functions, such as the air conditioning of the cockpit and the passenger cabin. or the deicing of certain organs of the aircraft. This hot air comes from the turbomachines of the aircraft and must undergo significant cooling before use. To do this, at least one heat exchanger, generally called pre-cooler (precooler), in which hot air taken from the engine of a turbomachine is cooled by cooler air, is provided. taken in the fan or secondary vein of this turbomachine. Each turbine engine is fixed by a pylon to a part of the aircraft, such as its fuselage. In the current technique, the aforementioned exchanger is mounted in the pylon. This exchanger comprises a first air circuit whose input is connected by a pipe to hot air sampling means and the outlet is connected to means for supplying hot air to the aircraft. The air sample is taken from the engine and sent to the first air circuit of the exchanger via a duct which passes through the secondary duct inside a structural arm and is then connected to the inlet of this exchanger. first air circuit. The exchanger comprises a second air circuit which is supplied with air taken from the fan duct of the turbomachine, this air then being discharged to the outside after heat exchange with the air of the first air circuit, in view of its cooling. The present invention provides an improvement to this technology. SUMMARY OF THE INVENTION The invention proposes an aircraft turbomachine, comprising a nacelle and a motor defining at least one flow line of an air flow, characterized in that a heat exchanger of the type described in FIG. cooler for the air supply of the aircraft is mounted in the nacelle, the exchanger comprising a primary circuit whose input is connected to means for withdrawing compressed air from the engine and the output is connected to means for air supply of the aircraft and a secondary circuit supplied with air taken from said air flow. The invention therefore proposes a new location for the heat exchanger or precooler, this exchanger being housed in the nacelle and no longer in the connecting pylon of the turbomachine to the aircraft. Some aircraft manufacturers could indeed require that this exchanger is housed in the nacelle. This allows in particular to facilitate access to this equipment because the disassembly of the outer covers of the nacelle can allow this access. In addition, it is conceivable that the exchanger is directly supplied by the flow of air taken from the fan duct without it being necessary to connect this exchanger by a specific duct to means for withdrawing air into this vein. . The invention thus makes it possible in particular to simplify and lighten the previous technology. In addition, it reduces the number of interfaces to the tower since it is no longer necessary to bring the two pipes cold flow and hot flow to the pylon. Only the mixed and cooled air duct is chimney up to this one. This simplifies accessibility to the tower and thus the assembly or disassembly of the propulsion system on the aircraft. In addition, since the pylon is a fire-resistant area (ie not protected in case of fire), the air and skin temperature of the pipe must not exceed a certain value. The fact that the interface pipe contains air cooled by the pre-cooler, makes it possible to limit or even eliminate the use of thermal blankets (for skin temperature) or double-skinned pipe (to contain possible leakage).
    [0002] The exchanger is preferably attached to an outer annular casing of the engine. This housing may include a housing recess of the exchanger. This facilitates the integration of the exchanger in the nacelle. The exchanger can be attached to a removable panel of the housing. This panel can be configured to define said recess. It is then possible, during a maintenance operation for example, to remove the exchanger by removing the housing panel. The exchanger may be partially embedded in the housing and include a protruding portion on the inner surface of the housing. This projecting portion may define an inlet or air supply mouth of the exchanger. Advantageously, the heat exchanger comprises a heat exchange block defining said primary and secondary circuits, an air bleed scoop in said air flow and supply of the secondary circuit, and a discharge nozzle of the air leaving the secondary circuit. The exchange block, scoop and nozzle can be attached directly to one another to form a one-piece assembly. This assembly may comprise inlet manifolds and air outlet respectively connected to the sampling and supply means of the primary circuit. The exchanger may further comprise a valve between the scoop and the exchange block or the nozzle, such as a valve valve (s). The inlet of the scoop may open radially inwards and / or axially upstream, and its outlet may open axially downstream and / or radially outwards. The inlet of the nozzle may open radially inwards and / or axially upstream, and its outlet may open axially downstream and / or radially outwards. The present invention also relates to a heat exchanger of the pre-cooler type for a turbomachine as described above, characterized in that it comprises a heat exchange block comprising primary and secondary circuits, collectors of air inlet and outlet of the primary circuit, a scoop configured to withdraw air in an air flow of the turbomachine and to supply the secondary circuit, a nozzle configured to evacuate the air from the secondary circuit, and the block, the scoop, the nozzle and the collectors are fixed together and form a one-piece assembly. The exchanger and its exchange block are for example of the brick type. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a schematic perspective view of an aircraft turbomachine according to the invention; FIG. 2 is a schematic perspective view of a heat exchanger of the pre-cooler type installed according to the invention, FIG. 1 is a diagrammatic view in axial section of the exchanger of FIG. 2; FIG. 4 is a diagrammatic front perspective view of a casing carrying an exchanger, which is partially embedded in this casing, FIG. FIG. 6 is a diagrammatic view in axial section of the exchanger of FIGS. 4 and 5; FIGS. 7 and 8 are schematic diagrammatic views of FIG. in perspective of a casing comprising two removable and interchangeable panels, one of which carries an exchanger according to the invention. DETAILED DESCRIPTION Reference is first made to FIG. 1 which represents a turbomachine 10 according to the invention for an aircraft, this turbomachine being here of the double-flow type. The turbomachine 10 comprises a motor 12 comprising an outer casing 14 defining an annular flow vein of a secondary flow. A primary flow flows inside the engine 12. The nacelle of the turbomachine is not shown here for clarity. The engine typically comprises from upstream to downstream, in the flow direction of the primary flow, at least one compression module, a combustion chamber, at least one turbine module, and a combustion gas ejection nozzle. The turbomachine 10 is fixed to a part of the aircraft, such as its fuselage, by means of a pylon 18, only structural elements of which are shown in FIG. 1. As explained above, hot air taken from the engine is cooled by means of a heat exchanger of the pre-cooler type (precooler) and feeds the aircraft to perform certain functions, such as the air conditioning of the cockpit and passenger cabin or the de-icing of certain organs of the aircraft. In the prior art as shown in FIG. 1, this exchanger is mounted in the pylon 18 and fixed to one of the structural elements of the pylon 18. On the contrary, according to the invention and as represented in particular in FIG. the exchanger 20 is mounted in the nacelle, that is to say in a space formed between the nacelle and the casing 14, and is preferably fixed on the casing 14, as shown in FIG. 1. A heat exchanger 20 according to FIG. The invention is better visible in FIGS. 2 and 3. This exchanger 20 comprises two circuits, primary and secondary, respectively. The primary circuit, also called hot circuit, has its input connected by at least one pipe 22 to hot air sampling means on the motor 12 (for example in the compression module), the output of this primary circuit being connected by at least one other pipe 24 to hot air supply means of the aircraft.
    [0003] The secondary circuit, also called cold circuit, has its input connected to means for withdrawing air from the secondary flow of the turbomachine, the output of this circuit being connected to means for evacuating the air outside the engine. the turbomachine. In the example shown in particular in Figure 2, the exchanger 20 essentially comprises six elements: a scoop 26 forming said means for withdrawing air from the secondary flow, a valve 28 for regulating the flow of air flowing in the secondary circuit, a heat exchange block 30 comprising for example bricks defining said primary and secondary circuits, a nozzle 32 forming the air evacuation means of the secondary circuit, and the respective inlet collectors air 34 and air outlet 36 of the primary circuit. The scoop 26 is fixed here by bolting directly on the outer casing 14. It comprises an inlet 38, shown in FIG. 3 or mouth which is surrounded by a peripheral flange 40 applied and fixed on the outer surface of the outer casing 14. the example shown, this inlet 38 of the scoop 26 communicates with an opening of the casing 14 and opens mainly radially inwards into the flow 42 of the secondary flow stream (Figure 3). The outlet 44 of the scoop 26 is oriented substantially axially downstream. The valve 28 is mounted directly downstream of the scoop 26. This is for example a valve 28 louvers 29, the valve comprising for example two louvers movable in rotation about axes transverse to the flow secondary flow in the scoop from a closed position of the passage section of the valve to a release position of this passage section.
    [0004] The heat exchange block 30 may be of the type used in the prior art for this application. The nozzle 32 is mounted directly at the output of the secondary circuit of the block 30, its inlet 46 opening predominantly axially upstream and its outlet 48 being oriented substantially radially outwardly. As can be seen in FIG. 2, the peripheral edge of the nozzle 32, defining the outlet 48, can be equipped with a seal 50 intended to bear radially on the inner surface of a removable external cover (not represented) of the nacelle. The six aforementioned elements of the exchanger 20 form here a one-piece assembly. In the example shown in FIG. 4, the block 30 has a parallelepipedal shape and comprises two opposite sides (downstream and upstream) respectively connected to the nozzle 32 and to the valve 28, and two other opposite sides connected respectively to the collectors 34, 36, shown in Figure 2. The size of the block 30, between the manifolds 34, 36, defines the hot run length of the primary circuit, and the size of the block 30, between the valve 28 and the nozzle 32, defines the length passes. cold of the secondary circuit. To allow integration of the exchanger 20, the housing 14 may comprise a recess 49 located to receive the exchanger. It can be seen in FIG. 3 that the passage cross section of the vein 42 is reduced at the level of the exchanger 20 because of this recess. Figures 4 to 6 show an alternative embodiment of the invention in which the exchanger 120 is partially embedded in the outer casing 114, the reference 117 in Figure 6 designating the outer wall of the outer casing 114 which generally comprises removable covers .
    [0005] The exchanger 120 comprises the same elements as the exchanger 20 described in the foregoing, namely a scoop 126, a valve 128, a heat exchange block 130, a nozzle 132 and two collectors 134, 136. In the example shown, parts of the scoop 126 and of the block 130 of the exchanger 120 are embedded in the casing 114 and project radially inside the casing 114. These protruding parts are therefore situated in the groove 142. flow of the secondary flow of the turbomachine. The inlet 138 of the scoop 126 opens predominantly axially upstream. The outlet of the nozzle 132 is here equipped with an exhaust grille 151.
    [0006] Figures 7 and 8 show another alternative embodiment of the invention, wherein the aforementioned recess of the outer casing 214 is defined by a removable panel 252 which is attached and fixed on the housing to close an opening thereof. The panel 252 has a substantially ovoidal shape, its peripheral edge being sealingly attached to the peripheral edge of the opening of the outer casing 214 except at its upstream end portion. Indeed, the peripheral edge 254 of the upstream end portion of the panel 252 is offset radially inwardly relative to the corresponding peripheral edge 256 of the opening, and defines therewith the inlet 238 of the scoop 220. This heat exchanger is fixed directly on the panel 252. The outer casing 214 comprises another opening, identical to the aforementioned opening, and closed by another panel 258 which is removable and interchangeable with the panel 252, c that is to say that each panel can be used to close one or the other of the openings of the housing 214. This allows to allow the integration of the exchanger in two different positions on the housing 214. The panel 258 does not define here a recess. In the example shown in FIG. 8, the openings closed by the panels 252, 258 are situated on either side of an orifice 260 of the housing 214 for mounting the arm 12h (for arm at 12 o'clock, by analogy with the dial of a watch) of the turbomachine. The exchanger 220 can thus be positioned on one side or the other of this arm, which allows the assembly of the exchanger on the fuselage side of the aircraft for each of the lateral turbomachines of an aircraft. The operation of the heat exchanger 20, 120, 220 according to the invention is identical to those of the prior art, for the air supply of an aircraft. The housing 14, 114, 214 may be metallic or composite.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. An aircraft turbomachine (10) comprising a nacelle and a motor (12) comprising at least one stream (42) for the flow of an air flow, characterized in that a heat exchanger (20) of the type pre-cooler for the air supply of the aircraft is mounted in the nacelle, this exchanger comprising a primary circuit whose input is connected to means for withdrawing compressed air from the engine and the outlet is connected to means supplying air to the aircraft and a secondary circuit supplied with air taken from said air stream.
    [0002]
    2. Turbomachine according to claim 1, characterized in that the exchanger (20) is fixed on an outer annular housing of the motor (14).
    [0003]
    3. The turbomachine according to claim 2, characterized in that the outer annular casing (14) comprises a housing recess of the exchanger (20).
    [0004]
    4. A turbomachine according to claim 3, characterized in that the exchanger (220) is fixed on a removable panel (252) of the housing (214), this panel being configured to define said recess.
    [0005]
    5. Turbomachine according to one of claims 2 to 4, characterized in that the exchanger (120) is partially embedded in the housing (114) and comprises a projecting portion on the inner surface of the housing.
    [0006]
    6. Turbomachine according to one of the preceding claims, characterized in that the exchanger (20) comprises a block (30) for heat exchange defining said primary and secondary circuits, a scoop (26) for sampling air in said flow of air and supply of the secondary circuit, and a nozzle (32) discharging the air leaving the secondary circuit.
    [0007]
    7. The turbomachine according to claim 6, characterized in that the exchange block (30) comprises collectors (34, 36) of inlet and air outlet respectively connected to the sampling and supply means of the primary circuit. .
    [0008]
    8. The turbomachine according to claim 6 or 7, characterized in that the exchanger (20) comprises a valve (28) between the scoop (26) and the exchange block (30).
    [0009]
    9. Turbomachine according to one of claims 6 to 8, characterized in that the block (30), the scoop (26) and the nozzle (32) are fixed together and form a one-piece assembly.
    [0010]
    10. heat exchanger (20) pre-cooler type for a turbomachine (10) according to one of the preceding claims, characterized in that it comprises a block (30) of heat exchange defining primary and secondary circuits , inlet manifolds (34) and air outlet (36) of the primary circuit, a scoop (26) configured to draw air in an air flow of the turbomachine and to supply the secondary circuit, a nozzle (32) configured to exhaust air from the secondary circuit, and in that the block, scoop, nozzle and collectors are secured together and form a one-piece assembly.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3015573A1|2015-06-26|AIRCRAFT TURBOMACHINE COMPRISING A HEAT EXCHANGER OF THE PRE-COOLING TYPE
    EP1496207B1|2006-12-20|Device to passively control the thermal dilatation of a turbomachine housing
    CA2875044A1|2015-06-19|Casing for a propulsion assembly
    CA2621195C|2013-06-11|Turbofan provided with a pre-cooler
    EP1265030A1|2002-12-11|Mounting of a metallic matrix composite combustion chamber with flexible linking shrouds
    CA2955739C|2017-07-04|System for supplying pressurised air installed in an aircraft turbine engine including sealing means
    FR3001199A1|2014-07-25|MOTOR COVER INCORPORATING AN EQUIPMENT VENTILATION CIRCUIT
    FR2834533A1|2003-07-11|DEVICE FOR COOLING THE COMMON NOZZLE ON A NACELLE
    EP1956226B1|2009-08-19|Discharge device for a jet engine, and jet engine comprising same
    FR3046200B1|2019-06-07|TURBOMACHINE COMPRISING AN OIL TANK AND AN AIR-OIL EXCHANGER
    FR3036442A1|2016-11-25|TURBOMACHINE COMPRISING A VENTILATION SYSTEM
    FR3028289A1|2016-05-13|AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE HOUSING WITH A VARIABLE AERODYNAMIC PROFILE
    WO2015082799A1|2015-06-11|Propulsion assembly comprising a box for retaining drained fluids
    CA2933353C|2022-03-01|Aircraft turbomachine comprising a heat exchanger of the precooler type
    FR2933128A1|2010-01-01|DEVICE FOR COLLECTING AIR IN A TURBOMACHINE
    FR3030627A1|2016-06-24|SERVITUDE PASSAGE SYSTEM FOR TURBOMACHINE
    FR3065490A1|2018-10-26|PROPELLANT AIRCRAFT ASSEMBLY COMPRISING AIR-LIQUID HEAT EXCHANGERS
    FR3072127B1|2019-11-01|INTERMEDIATE CASTER HUB DISCHARGE DUCT FOR AN AIRCRAFT AIRCRAFT COMPRISING COOLING CHANNELS
    FR3094030A1|2020-09-25|AIRCRAFT POWERTRAIN PACKAGE
    FR3070418A1|2019-03-01|AIRCRAFT TURBOMACHINE
    FR3000985A1|2014-07-18|Cooling device for casing of turbine for turboshaft engine, has supply unit for directly providing part of air of power supply enclosure of low pressure module of turbine, in housing without allowing air to pass by cooling pipe
    FR3095229A1|2020-10-23|Assembly for the primary flow of an aeronautical turbomachine, turbomachine provided with it
    WO2018083403A1|2018-05-11|Cooling device for a turbine of a turbomachine
    FR3063345A1|2018-08-31|DEVICE FOR TESTING A GAS TURBOMACHINE FOR AN AIRCRAFT
    同族专利:
    公开号 | 公开日
    WO2015092251A1|2015-06-25|
    CA2933353A1|2015-06-25|
    US11060462B2|2021-07-13|
    FR3015573B1|2015-12-11|
    US20170002747A1|2017-01-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20030218096A1|2002-05-22|2003-11-27|Herve Marche|Exchanger for aircraft air conditioning circuit and integrated propulsion assembly for such an exchanger|
    US20080230651A1|2005-09-26|2008-09-25|Airbus France|Turbofan Provided With a Pre-Cooler|
    EP2492199A2|2011-02-28|2012-08-29|General Electric Company|Environmental control system supply precooler bypass|FR3087840A1|2018-10-29|2020-05-01|Safran Aircraft Engines|NACELLE HOOD FOR POWERED AIRCRAFT ASSEMBLY|
    FR3108944A1|2020-04-02|2021-10-08|Safran Aircraft Engines|COMPOSITE WALL ELEMENT FOR AN AIRCRAFT TURBOMACHINE|US5123242A|1990-07-30|1992-06-23|General Electric Company|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine|
    US7607308B2|2005-12-08|2009-10-27|General Electric Company|Shrouded turbofan bleed duct|
    GB0607771D0|2006-04-20|2006-05-31|Rolls Royce Plc|A heat exchanger arrangement|
    US7861512B2|2006-08-29|2011-01-04|Pratt & Whitney Canada Corp.|Turbofan bypass duct air cooled fluid cooler installation|
    FR2905975B1|2006-09-20|2008-12-05|Snecma Sa|BLOWER DRIVE FOR A TURBOMACHINE.|
    US9206912B2|2013-01-23|2015-12-08|The Boeing Company|Dual door fan air modulating valve|
    EP3084183B1|2013-12-18|2019-07-10|United Technologies Corporation|Heat exchanger flow control assembly and corresponding method|USD791300S1|2014-11-27|2017-07-04|Ubbink B.V.|Wall duct|
    USD791301S1|2014-11-27|2017-07-04|Ubbink B.V.|Wall duct|
    US9879591B2|2015-02-20|2018-01-30|Pratt & Whitney Canada Corp.|Engine intake assembly with selector valve|
    US20170074167A1|2015-09-10|2017-03-16|Honeywell International Inc.|Turbofan engine mounted precooler system|
    US10563585B2|2016-03-02|2020-02-18|United Technologies Corporation|Heat exchanger for gas turbine engine|
    US11203437B2|2016-06-30|2021-12-21|Bombardier Inc.|Assembly and method for conditioning engine-heated air onboard an aircraft|
    US20180162537A1|2016-12-09|2018-06-14|United Technologies Corporation|Environmental control system air circuit|
    EP3413001B1|2017-06-06|2020-01-08|Ge Avio S.r.l.|Additively manufactured heat exchanger|
    US10807722B2|2017-07-11|2020-10-20|Hamilton Sunstrand Corporation|Cabin air compressor motor cooling flow enhancement cowl|
    FR3078947B1|2018-03-13|2020-03-13|Airbus Operations|AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM|
    法律状态:
    2015-12-01| PLFP| Fee payment|Year of fee payment: 3 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 6 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362956A|FR3015573B1|2013-12-19|2013-12-19|AIRCRAFT TURBOMACHINE COMPRISING A HEAT EXCHANGER OF THE PRE-COOLING TYPE|FR1362956A| FR3015573B1|2013-12-19|2013-12-19|AIRCRAFT TURBOMACHINE COMPRISING A HEAT EXCHANGER OF THE PRE-COOLING TYPE|
    PCT/FR2014/053349| WO2015092251A1|2013-12-19|2014-12-15|Aircraft turbomachine comprising a heat exchanger of the precooler type|
    US15/104,445| US11060462B2|2013-12-19|2014-12-15|Aircraft turbomachine comprising a heat exchanger of the precooler type|
    CA2933353A| CA2933353A1|2013-12-19|2014-12-15|Aircraft turbomachine comprising a heat exchanger of the precooler type|
    [返回顶部]