• 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:

    公开号:FR3017658A1
    申请号:FR1451271
    申请日:2014-02-18
    公开日:2015-08-21
    发明作者:Julien Viel；Stephane Prunera-Usach；Bernard Brandt；Samuel Raymond Germain Becquerelle
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to an equipment training box for a turbomachine, also called a gear box for accessories or AGB for "accessory gear box". Such an accessory drive box is intended to transmit the original movement of the turbomachine by means of a radial shaft coming out of it, and to transmit it to various accessories or equipment ancillary to the turbomachine, such as pumps, electricity generators, etc., which are essential for the operation of the turbomachine or other aircraft of an aircraft propelled by this turbomachine. The equipment drive box also makes it possible to transmit the power of the equipment to the engine during the start-up phases. The transmission is carried out by a kinematic chain composed of successive gears. STATE OF THE PRIOR ART The document FR No. 12 58196 describes a gearbox to be fixed on a turbomachine to drive at least one equipment annexed to the turbomachine. This gearbox is shown more precisely in FIG. 1. It comprises: a power take-off member 1 intended to mesh with a radial shaft of the turbomachine, a casing 44; two kinematic chains 2, 3 internal to the casing. Each kinematic chain 2, 3 is composed of gears connected to each other. Each gear rotates a rotating shaft of equipment. The two kinematic chains 2, 3 are located in non-parallel planes. The power take-off member 1 is connected to each kinematic chain at one of the ends 4, 5 of said driveline.
    [0002] The document FR No. 13 59910 describes another type of gearbox to be fixed on a turbomachine to drive at least one equipment annexed to the turbomachine. This gearbox comprises: - a power take-off member for meshing with a radial shaft of the turbomachine, - a casing, - a kinematic chain internal to the casing. The kinematic chain comprises a central shaft which transmits the movement of the power take-off member to at least one pinion capable of driving in rotation at least one rotary shaft of an equipment. The power take-off member is connected to the central shaft at one end of the central shaft. However, in these two documents, the power take-off is constrained and it can not be performed on all the shafts of the turbomachine.
    [0003] SUMMARY OF THE INVENTION The invention aims to remedy the disadvantages of the state of the art by proposing a gearbox to be fixed on a turbomachine to drive at least one equipment annexed to the turbomachine which offers greater latitude to achieve the power take-off, in particular enabling the power take-off on the high-pressure shaft of a turbomachine, on its low-pressure shaft or on its intermediate shaft.
    [0004] To do this, is proposed according to a first aspect of the invention, a gearbox to be fixed on a turbomachine to drive at least one equipment annexed to the turbomachine, the gearbox comprising: - a housing; - A power take-off member adapted to mesh with a radial shaft of the turbomachine; At least one internal kinematic chain to the casing adapted to transmit the rotational movement of the power take-off member to at least one rotary shaft of a device, the kinematic chain comprising a first end and a second end; of power take-off being connected to the drive train by a gear with concurrent axes located inside the drive train.
    [0005] Thus, the invention proposes to connect the power take-off member to the kinematic chain no longer at one end of the kinematic chain but at a point strictly between the two ends of the kinematic chain. Relocating the power-take-off member inside the kinematic chain makes it possible to have a greater degree of latitude to perform the power take-off on a shaft of the turbomachine and therefore to have latitudes of installation of the gearbox. It will thus be possible to perform the aircraft power take-off no longer in the area of the compressor housing but on a location other engine shafts, such as on the intermediate shaft, or between the turbine and the combustion chamber, or between the compressor and turbine. The gearbox may also have one or more of the following features taken independently or in any technically possible combination.
    [0006] According to a first embodiment, called "column gearbox", the drive train comprises at least one central shaft capable of transmitting the movement of the power take-off member to at least one rotary shaft of a gearbox. via at least one intermediate gear, the central shaft having two ends, the power take-off member being connected to the central shaft by a counterbalance gearing located between the first end and the second end of the gearbox. central tree. Thus, in this embodiment, the movement of the power take-off member is transmitted to the rotary shaft of the equipment via a central shaft, thereby saving space and increasing latitude in the arrangement of the gearbox. Advantageously, the power take-off member extends in a secant direction to that of the central shaft.
    [0007] Advantageously, the central shaft comprises a first and a second part, the power take-off member being connected to the first part by a first gear with concurrent axes and to the second part by a second gear with concurrent axes. Indeed, the fact of relocating the power take-off member allows in this case to break down the central shaft into two parts which are connected independently of one another to the central shaft. In this case, the first gear with concurrent axes preferably has a reduction ratio different from that of the second gear with concurrent axes so that the two parts of the central shaft can thus rotate at different speeds. It is thus possible to connect the slow equipment to one of the two parts of the central shaft, while the fast equipment is connected to the other part of the central shaft, which makes it possible to optimize the drive train.
    [0008] According to a second embodiment, known as a "V-gearbox", the gearbox comprises two kinematic chains, each kinematic chain being able to transmit the rotational movement of the power take-off member to at least one shaft rotary device of an equipment, each kinematic chain having a first end and a second end, the power take-off member being connected to each kinematic chain by a gear with concurrent axes located between the first and the second end of each kinematic chain.
    [0009] Advantageously, each kinematic chain comprises a gear line, the two gear lines extending in intersecting directions. According to different embodiments, the two concurrent-axis gears may have different or equal reduction ratios.
    [0010] A second aspect of the invention relates to a turbomachine comprising a gearbox according to one of the preceding claims.
    [0011] According to various embodiments: the turbomachine comprises a high pressure shaft, the power take-off member being connected to the high pressure shaft; - The turbomachine comprises a low pressure shaft, the power take-off member being connected to the low pressure shaft; the turbomachine comprises an intermediate shaft, the power take-off member being connected to the intermediate shaft. BRIEF DESCRIPTION OF THE FIGURES Other features and advantages of the invention will emerge on reading the detailed description which follows, with reference to the appended figures, which illustrate: FIG. 1, a schematic representation in perspective of a box of FIG. gear of the prior art; - Figure 2, a schematic perspective representation of a gear box according to a first embodiment of the invention; - Figure 3, a schematic perspective representation of a gear box according to a second embodiment of the invention; - Figure 4, a schematic perspective representation of a gearbox according to another embodiment of the invention.
    [0012] For the sake of clarity, identical or similar elements are identified by identical reference signs throughout the figures. DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT FIG. 2 represents a gearbox according to an embodiment of the invention known as a "V gearbox". This gearbox comprises: a housing 44; - A power take-off member 1; - A first and a second drive train 2, 3. Each drive train 2, 3 comprises a line of intermediate gears 22, 23. Each intermediate gear 22, 23 is preferably adapted to drive in rotation a rotary shaft of a gear . Each kinematic chain 2, 3 comprises a first end 4, 5 and a second end 6, 7. In contrast to the gearboxes of the prior art in which the power take-off member 1 is connected to each drive train at one of these ends, in this embodiment, the PTO 1 is connected to each kinematic chain 2, 3 at a zone 14 located within this kinematic chain. In other words, the zone 14 is strictly situated between the two ends 4, 6 and 5, 7 of each kinematic chain 2, 3. More specifically, the power take-off member 1 is preferably connected to each kinematic chain at one of these intermediate gears 22, 23 which is interposed between two intermediate gears of the drive train. The location of the power take-off member 1 can thus be chosen as a function of the radial shaft of the turbomachine to which it is connected.
    [0013] The power take-off member 1 is preferably connected to each drive train by a gear with intersecting axes 24. According to one embodiment, the gear with concurrent axes 24 connecting the power take-off member 1 to the first link kinematic 2 may have a reduction ratio different from that which links the power take-off member 1 to the second driveline 3. Thus, the slow equipment can be connected to one of the two drivelines, while the fast equipments are connected. to the other. Figure 3 shows a gearbox according to another embodiment of the invention called "gearbox column". In this embodiment, the gearbox comprises: a housing 25; - A power take-off member 1; - A kinematic chain 8. The drive train 8 comprises a central shaft 10 connected to intermediate gears 9, each intermediate gear 9 itself being connected to a rotary shaft 11 of equipment. The central shaft has two ends 12, 13. The central shaft 10 is connected to the power take-off member 1 by a gear with intersecting axes 26. Thus, the power take-off member 1 transmits its movement rotation to the central shaft 10 via the gear with intersecting axes 26. The central shaft 10 transmits its rotational movement to the rotary shafts 11 via the intermediate gears 9. According to one embodiment, can also use the same to achieve power take-off and transmission to gear gears. In this case, the concurrent axis gear 26 and the intermediate gear 9 are one and the same gear.
    [0014] The gearbox according to this embodiment is particularly remarkable in that the power take-off member 1 is no longer connected to an end 12 of the central shaft 10, unlike the embodiments of the prior art, but it is connected to the central shaft 10 at an area between the two ends 12, 13 of the central shaft. More precisely, the power take-off member 1 is preferably connected to the central shaft 10 at a zone 14 situated between two intermediate gears 9. With reference to FIG. 4, the central shaft 10 can also be composed of two parts 15, 16 connected independently of each other to the power take-off member 1, the first portion 15 of the central shaft 10 being connected to the power take-off member 1 by a first a gear with intersecting axes 27, the second part 16 of the central shaft 10 being connected to the power take-off member 1 by a second gear with intersecting axes 28. The two parts 15, 16 are preferably aligned. The first concurrent-axis gear 27 may have a reduction ratio different from that of the second concurrent-axis gear 28 so that the first portion 15 of the central shaft 10 rotates at a different speed than the second portion 16. connect the slow equipment to one of the two parts 15, 16, while the fast equipment is connected to the other part.
    [0015] Naturally, the invention is not limited to the embodiments described with reference to the figures and variants could be envisaged without departing from the scope of the invention.
    权利要求:
    Claims (5)
    [0001]
    REVENDICATIONS1. Gearbox to be fixed on a turbomachine to drive at least one equipment annexed to the turbomachine, the gearbox comprising: - a housing; - A power take-off member (1) adapted to mesh with a radial shaft of the turbomachine; - At least one kinematic chain (2, 3, 8) internal to the housing adapted to transmit the rotational movement of the power take-off member (1) to at least one rotary shaft of an equipment, the kinematic chain (2 , 3, 8) having a first end (4, 5, 12) and a second end (6, 7, 13), characterized in that the power take-off member (1) is connected to the drive train (2 , 3, 8) by a gear with concurrent axes located inside the kinematic chain (2, 3, 8).
    [0002]
    Gearbox according to Claim 1, in which the kinematic chain (8) comprises at least one central shaft (10) capable of transmitting the movement of the power take-off member (1) to at least one rotary shaft ( 11) of equipment via at least one intermediate gear (9), the central shaft (10) having two ends (12, 13), the power take-off member (1) being connected to the central shaft (10) by a concurrent axis gear located between the first end (12) and the second end (13) of the central shaft (10).
    [0003]
    Gear box according to one of claims 2 or 3, wherein the central shaft (10) has a first (15) and a second part (16), the power take-off member (1) being connected to the first part (15) by a first gear with concurrent axes and the second part (16) by a second gear with concurrent axes.
    [0004]
    4. Gear box according to the preceding claim, wherein the first gear with concurrent axes has a reduction ratio different from that of the second gear with concurrent axes.
    [0005]
    5. gearboxes according to claim 1, comprising two kinematic chains (2, 3), each kinematic chain (2, 3) being able to transmit the rotational movement of the power take-off member (1) to at least a rotary shaft of an equipment, each kinematic chain (2, 3) having a first end (4, 5) and a second end (6, 7), the power take-off member (1) being connected to each chain kinematics (2, 3) by a counter-axis gear located between the first (4, 5) and the second end (6, 7) of each drive train (2, 3) .6. 7. Gearbox according to the preceding claim, wherein the two gears with concurrent axes have different reduction ratios. Turbomachine comprising a gearbox according to one of the preceding claims. Turbomachine according to claim 7, wherein the turbomachine comprises a high pressure shaft, the power take-off member being connected to the high pressure shaft. The turbomachine according to claim 7, further comprising a low pressure shaft, the power take-off member being connected to the low pressure shaft. A turbomachine according to claim 7, further comprising an intermediate shaft, the power take-off member being connected to the intermediate shaft. 10
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3108131B1|2019-09-11|Accessory gearbox of a turbomachine
    EP3055539A1|2016-08-17|Turbomachine auxiliary drive gearbox
    CA2536129C|2013-10-15|Two-spool turboshaft engine with means of power take-off on the low pressure and high pressure rotors, power take-off module for the turboshaft engine and process for mounting theturboshaft engine
    EP2521851B1|2013-11-13|Contra-rotating propeller system for an aircraft turbine engine
    FR2549006A1|1985-01-18|SHAFT MOUNTED BLADE ROTOR SYSTEM, PARTICULARLY FOR BOAT OR AIRPLANE PROPELLERS
    FR2943035A1|2010-09-17|DEVICE FOR DRIVING A PAIRE OF CONTRAROTIVE PROPELLERS BY AN EPYCYCLOIDAL TRAIN
    FR2950381A1|2011-03-25|TURBOMACHINE WITH NON-CARINE CONTRAROTATIVE PROPELLERS
    FR2979121A1|2013-02-22|MECHANICAL TRANSMISSION DEVICE FOR THE ROTATION DRIVE OF THE CONTRAROTATIVE PROPELLERS OF A DOUBLE PROPELLER TURBOPROPULSOR.
    FR2980513A1|2013-03-29|SHIFTING CHANGE MECHANISM FOR OPEN ROTOR ENGINE
    EP2576995B1|2014-08-06|Gearbox in a turbomachine
    CA2941804A1|2015-09-24|Accessory gearbox for gas turbine engine
    EP2893171A1|2015-07-15|Drive gearbox on a turbomachine, consisting of a drive train with gear lines extending into non-parallel planes
    EP2582922B1|2014-03-19|Guiding and sealing device for a turbine engine, having a carbon seal and built-in journal bearing
    FR3084623A1|2020-02-07|PROPULSION SYSTEM FOR ELECTRIC VEHICLE
    FR3029584A1|2016-06-10|SPEED TRANSMISSION DEVICE FOR THE DISPLACEMENT OF A MOTOR VEHICLE, IN PARTICULAR A MOTORIZED VEHICLE WITH AT LEAST TWO WHEELS, AND MOTOR POWER PACKAGE USING SUCH A DEVICE, IN PARTICULAR FOR A HYBRID VEHICLE.
    FR3021594A1|2015-12-04|SPEED TRANSMISSION DEVICE FOR THE DISPLACEMENT OF A MOTOR VEHICLE, IN PARTICULAR A MOTORIZED VEHICLE WITH TWO WHEELS.
    WO2015107308A1|2015-07-23|Accessory gearbox assembly for an aircraft turbine engine
    FR3062423B1|2019-03-15|DRIVE SYSTEM FOR A FUEL PUMP OF A TURBOMACHINE
    EP3721118B1|2021-12-29|Planetary gear train
    FR3026389A1|2016-04-01|PROPELLER DRIVE BOX FOR PROPELLER ENGINE
    EP3204626A1|2017-08-16|Compact spinal transmission
    FR3002980A1|2014-09-12|LUBRICATION GROUP FOR A TURBOMACHINE
    FR3044730A1|2017-06-09|TWO LINE TRANSMITTER SPEED REDUCER FOR TURBOPROPULSEUR, TURBOPROPULSEUR COMPRISING SUCH REDUCER
    FR3098847A1|2021-01-22|EPICYCLOIDAL GEAR REDUCER FOR A TURBOMACHINE
    同族专利:
    公开号 | 公开日
    CA2939840A1|2015-08-27|
    WO2015124857A1|2015-08-27|
    US10190505B2|2019-01-29|
    EP3108131B1|2019-09-11|
    FR3017658B1|2019-04-12|
    RU2016136969A|2018-03-22|
    RU2016136969A3|2018-09-06|
    US20170009660A1|2017-01-12|
    RU2686967C2|2019-05-06|
    EP3108131A1|2016-12-28|
    JP6696905B2|2020-05-20|
    CA2939840C|2021-08-10|
    JP2017508915A|2017-03-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR970075A|1947-08-08|1950-12-29|Bristol Aeroplane Co Ltd|Improvements to gas turbo-engines|
    US2803943A|1953-12-30|1957-08-27|Armstrong Siddeley Motors Ltd|Means for supporting and driving accessories which are exterior to a ductedfan turbo-jet engine|
    FR2290576A1|1974-11-08|1976-06-04|Gen Electric|DEVICE FOR DRIVING THE ADDITIONAL EQUIPMENT OF A GAS TURBINE|
    US20060248900A1|2005-05-05|2006-11-09|Gabriel Suciu|Accessory gearbox|
    FR2941744A1|2009-01-30|2010-08-06|Hispano Suiza Sa|ASSEMBLY OF AN ACCESSORY RELAY HOUSING AND AN OIL TANK|
    EP2535544A2|2011-06-14|2012-12-19|Honeywell International, Inc.|Transverse mounted accessory gearbox|
    US20140020506A1|2012-07-20|2014-01-23|Hung Duong|Gearbox for gas turbine engine|EP3135882A1|2015-08-26|2017-03-01|Honeywell International Inc.|Transverse mounted accessory gearbox|
    EP3511549A1|2018-01-16|2019-07-17|Rolls-Royce plc|An accesssory gearbox assembly and a gas turbine engine comprising an accessory gearbox assembly|FR1258196A|1960-05-31|1961-04-07|Improvements to drum blowers for cleaning seeds in agricultural threshers|
    FR1359910A|1963-03-22|1964-04-30|Charbonnages De France|Cyclanic hydrocarbons and their production process|
    GB1103417A|1965-12-07|1968-02-14|Dowty Rotol Ltd|Engine installations and starting means therefor|
    RU2162158C1|1999-12-24|2001-01-20|ГОСУДАРСТВЕННОЕ УНИТАРНОЕ ПРЕДПРИЯТИЕ ТУШИНСКОЕ МАШИНОСТРОИТЕЛЬНОЕ КОНСТРУКТОРСКОЕ БЮРО "СОЮЗ" Военно-промышленный комплекс "МАПО"|Aircraft gas turbine engine accessory drive box|
    JP4490553B2|2000-04-28|2010-06-30|本田技研工業株式会社|Auxiliary drive unit for gas turbine engine|
    US6895835B2|2000-09-19|2005-05-24|Alan M. Cordeiro|Method of improving performance in a motor-driven system|
    US6735954B2|2001-12-21|2004-05-18|Pratt & Whitney Canada Corp.|Offset drive for gas turbine engine|
    US20050183540A1|2004-02-25|2005-08-25|Miller Guy W.|Apparatus for driving an accessory gearbox in a gas turbine engine|
    US20080148881A1|2006-12-21|2008-06-26|Thomas Ory Moniz|Power take-off system and gas turbine engine assembly including same|
    US8192143B2|2008-05-21|2012-06-05|United Technologies Corporation|Gearbox assembly|
    US8347637B2|2010-05-25|2013-01-08|United Technologies Corporation|Accessory gearbox with internal layshaft|
    US8490411B2|2010-11-17|2013-07-23|United Technologies Corporation|Axial accessory gearbox|
    JP5703370B2|2011-04-07|2015-04-15|川崎重工業株式会社|Aircraft power generator|
    US9926849B2|2011-06-14|2018-03-27|Honeywell International Inc.|Transverse mounted accessory gearbox|
    DE102012018603A1|2012-09-20|2014-03-20|Rolls-Royce Deutschland Ltd & Co Kg|Accessory gearbox device|
    US10145260B2|2013-06-06|2018-12-04|Safran Aircraft Engines|Accessory drive case for a turboprop|
    FR3011882B1|2013-10-11|2018-01-26|Hispano Suiza Sa|ACCESSORY DRIVE HOUSING FOR TURBOMACHINE|
    US10662878B2|2016-02-03|2020-05-26|Honeywell Internatioanl Inc.|Compact accessory systems for a gas turbine engine|
    FR3050761B1|2016-04-27|2019-07-05|Safran Aircraft Engines|CONTROL OF OIL FLOW IN A COOLING CIRCUIT OF A TURBOMACHINE|
    GB201615969D0|2016-09-20|2016-11-02|Rolls Royce Plc|Control system for a cabin blower system|US9926849B2|2011-06-14|2018-03-27|Honeywell International Inc.|Transverse mounted accessory gearbox|
    FR3016407B1|2014-01-16|2016-02-19|Hispano Suiza Sa|TRAINING BOX FOR EQUIPMENT|
    US10502142B2|2017-04-11|2019-12-10|United Technologies Corporation|Turbine engine gearbox assembly with sets of inline gears|
    CN107795639A|2017-10-25|2018-03-13|南通大学|A kind of special four axles three-dimensional commutator of transmitting device|
    CN107524759A|2017-10-25|2017-12-29|南通大学|A kind of three axle three-dimensional commutators applied to transmitting device|
    US10519870B2|2018-06-04|2019-12-31|United Technologies Corporation|Multiple mounting surface gearbox|
    法律状态:
    2016-02-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-01| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-25| CD| Change of name or company name|Owner name: HISPANO SUIZA, FR Effective date: 20170725 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 5 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 8 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1451271A|FR3017658B1|2014-02-18|2014-02-18|EQUIPMENT DRIVE HOUSING FOR TURBOMACHINE|
    FR1451271|2014-02-18|FR1451271A| FR3017658B1|2014-02-18|2014-02-18|EQUIPMENT DRIVE HOUSING FOR TURBOMACHINE|
    RU2016136969A| RU2686967C2|2014-02-18|2015-02-16|Accessory gearboxand gas turbine engine|
    JP2016553338A| JP6696905B2|2014-02-18|2015-02-16|Gearbox and turbine engine including the gearbox|
    US15/119,181| US10190505B2|2014-02-18|2015-02-16|Housing for driving an apparatus for a turbine engine|
    CA2939840A| CA2939840C|2014-02-18|2015-02-16|Housing for driving an apparatus for a turbine engine|
    EP15709258.6A| EP3108131B1|2014-02-18|2015-02-16|Accessory gearbox of a turbomachine|
    PCT/FR2015/050372| WO2015124857A1|2014-02-18|2015-02-16|Housing for driving an apparatus for a turbine engine|
    [返回顶部]