• 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 drive unit for turbomachine equipment comprising a casing (30) and two gear lines (40a, 40b) arranged in a V, the casing (30) comprising two branches (30a, 30b) in each of which one of the two gear lines (40a, 40b) is disposed, a lubricant reservoir (35) being disposed between the two gear lines (40a, 40b).
    公开号:FR3016407A1
    申请号:FR1450342
    申请日:2014-01-16
    公开日:2015-07-17
    发明作者:Julien Viel；Jordane Peltier；Stephane Prunera-Usach
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to gearboxes for equipment (in English AGB or Accessory Gearbox) present in aircraft turbomachines. Such AGBs generally comprise a gear line for transmitting mechanical energy between drive members, for example a starter or a compressor, and slave devices such as an electric generator or a hydraulic pump or other equipment. The term gear line is to be understood here as a set of adjacent gears geared and located in the same plane or in parallel planes. More specifically, the invention relates to an AGB structure that can be integrated in a turbofan engine. STATE OF THE PRIOR ART A turbofan engine 100 extending along a longitudinal axis XX (FIG. 3) comprises a primary stream 111 in which circulates a primary flow F1 fed through a set of compressors 103, a combustion chamber 104 and then a turbine assembly 105. The turbojet engine 100 also comprises a secondary vein 112 disposed around the primary vein 111 and in which circulates a secondary flow F2. The most common AGB architecture is a banana or crescent-shaped AGB in the nacelle around the secondary vein. Such an AGB then extends axially in an area 107 called fan zone (in English "fan zone") located between the fan 101 (fan English) and a secondary rectifier 108 extending in this vein. The blower zone can also extend beyond the rectifiers, as has been schematized in zone 107 '. At least one of the radial arms of the secondary rectifier 108 is hollow and is traversed at its heart by a motion transfer shaft, called a radial shaft, and pipe systems that can bind the AGB equipment to other equipment arranged in another zone. 106 of the turbomachine called central zone (in English "zone core"). The core zone 106 is the space located between the outer wall 111E of the primary stream 111 and the inner wall 1121 of the secondary stream 112, for example around the high-pressure compressor 103 and the combustion chamber 104. AGB exist as V-shaped AGBs. These comprise two gear lines arranged at an angle relative to each other, that is to say, the orientation planes of the one or more respective pinion (s) are secant. Such architectures may be arranged in the core zone 106. SUMMARY OF THE INVENTION The object of the invention is an improved V-shaped AGB architecture.
    [0002] The invention thus relates to a drive unit for turbomachine equipment comprising an envelope and two gear lines arranged in a V, the envelope comprising two branches in each of which one of the two gear lines is arranged, a lubricant reservoir being disposed between the two gear lines.
    [0003] The invention thus makes it possible to move the reservoir from the blowing zone towards the core zone located between the primary vein and the secondary vein. Space is released in the blower area, which increases the blower diameter and engine performance. In addition, in the case of a so-called core AGB, that is to say arranged in the core zone, the reservoir is close to the lubricant user equipment. The lengths of lubrication lines are reduced and the overall architecture of the lubrication system is simplified. The invention also makes it possible to take advantage of the space available between the two branches of the AGB each comprising at least one piece of equipment, the two branches being arranged in a V with respect to one another. The invention thus makes it possible to improve the integration of the tank. Advantageously, the lubricant reservoir is integrated in the envelope.
    [0004] In an advantageous configuration, the casing is a first casing, and the lubricant reservoir is a second casing mounted in the first casing or against the first casing. In an alternative advantageous configuration, the envelope is a casting part.
    [0005] In another advantageous configuration, the envelope is a piece produced by additive manufacturing. The reservoir may be a cavity formed in the envelope. The lubricant reservoir may form a main lubricant reservoir for the AGB or be only an auxiliary or secondary reservoir, for example as a subpart of a total volume of lubricant reservoirs, for example for use as a reservoir secondary used only in degraded mode. Degraded modes are, for example, post-incident wind-turbine-type situations when the fan is running at low speed, which does not allow the main lubrication unit to properly feed the oil system. . We talk about under-lubrication. The secondary tank can then be used for a limited time, coupled with a system for supplying low-speed transmission members. The invention also relates to a turbomachine comprising a drive unit for equipment as described above and disposed in the central zone (that is to say the "core zone"), located between a primary vein and a secondary vein of the turbomachine. Alternatively, the invention relates to a turbomachine comprising a drive unit for equipment as described above and disposed in the blower zone.
    [0006] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood on reading the detailed description which follows, non-limiting examples of implementation thereof, as well as the examination of the appended figures, diagrammatic and partial. , in which: - Figure 1 is a perspective view of a drive housing for equipment according to the invention; FIG. 2 is a cross section of the equipment drive box of FIG. 1; and, - Figure 3 is a general view of a turbojet engine in which the drive housing for equipment according to the invention can be implemented. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS FIGS. 1 and 2 illustrate an equipment package 10 according to the invention provided for example for a turbofan engine such as turbojet engine 100 (FIG. 3). The equipment drive box 10 is here disposed in the "core zone" 106 of the turbomachine as defined in the preamble, here under the longitudinal axis XX of the turbomachine (Figures 2 and 3). Alternatively, the drive housing 10 is disposed above or on the side of the axis XX (variant not shown). Alternatively again, the drive housing 10 is disposed in the fan zone (variant not shown). In the embodiment shown with reference to FIG. 1, the front part of the figure corresponds to the rear of the casing 10, oriented downstream of the turbomachine, while the rear part of the figure corresponds to the front of the housing 10, facing upstream. This orientation is however not limiting.
    [0007] The housing 10 comprises an envelope 30 provided with two branches (or arms) 30a and 30b. A gear line 40a or 40b is mounted in each of the branches 30a and 30b (see Figure 2). The gear lines 40a and 40b each comprise a respective pinion 45a or 45b extending along a plane Pa or Pb, or a general plane parallel to one of these two planes Pa and Pb. It is then said that the planes Pa and Pb are the general orientation planes of the gear lines 40a and 40b. Two equipment 20a and 20b equipment are here mounted on either side of the housing 10 on the respective upper face of each branch 30a and 30b.
    [0008] Each equipment 20a and 20b is supplied with rotary motion by a shaft one foot of which is disposed in the envelope 30. More specifically, each foot is provided with a pinion as one of the pinions 45a and 45b. In Figure 1, the shafts and the sprockets are not represented for a reason of readability. The shafts of the equipment 20a are oriented along an axis AA, the shaft of the equipment 20b is oriented along an axis BB. The equipment 20a and 20b form a V of orientation opposite to a V defined with respect to the gears, that is to say that the axes AA are oriented at an angle a different from a flat angle, that is to say -describe different from 0 ° or 180 °, relative to the BB axes. In a preferred but nonlimiting manner, this angle a is between 100 ° and 150 °. In other words, the planes Pa and Pb of general orientation of the gear lines 40a or 40b or of their pinion (s) 45a or 45b are intersecting in a V-shaped profile, that is, that is, they are neither confused nor parallel. An angle transmission box 25 (in English TGB or Transfer Gearbox) is arranged here without limitation to the front of the housing 10. An end of a rotary energy transfer shaft from the turbine is for example housed in the TGB 25.
    [0009] A lubricant reservoir 35 is here disposed between the gear lines 40a and 40b. In the embodiment shown, the reservoir 35 is integrated in the envelope 30 in a central interval 30c located between the branches 30a and 30b. The reservoir 35 is located more precisely between the two branches 30a, 30b, at the junction between their two ends closest together. In other words, the reservoir 35 is located generally close to the tip of the V defined by the equipment 20a and 20b, the hollow of this V being open towards the longitudinal axis XX of the turbomachine (see in particular in FIG. ). The envelope 30 may be manufactured by casting or by a similar process (for example of the additive manufacturing type, such as by laser powder melting or by powder blasting or other processes), or by machining in the mass or by machining. of distinct walls and subsequent assembly thereof. The lubricant reservoir 35 may be without limitation a cavity provided in a larger room or a separate housing, located in the housing 30 or externally and against it. When the casing 30 is manufactured by casting, the reservoir 35 is preferably a cavity formed in the casting. When the casing 30 is a casing formed for example of machined walls, the reservoir 35 is preferably a second separate casing disposed in the casing 30. In general, a lubricant reservoir such as the reservoir 35 thus placed between the Equipment 20a and 20b makes it possible to limit the lengths of the lubricant supply pipe as much as possible and to simplify the architecture thereof. Alternatively, equipment is mounted in a turbine zone disposed between the walls 111E and 1121, for example in the zone 109 vis-à-vis a turbine 105 (Figure 3) and / or the drive housing 10 s It extends itself into this turbine zone 109. The reservoir 35 can form the main lubricant reservoir of the AGB. The reservoir 35 may still form only a portion of the total volume of lubricant reservoirs provided to supply the AGB, or even be an oil reserve for the degraded operating phases. Other variants are still possible without departing from the scope of the invention.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A drive unit for turbomachine equipment comprising an envelope (30) and two gear lines (40a, 40b) arranged in a V, characterized in that: the envelope (30) comprises two branches (30a, 30b) in each wherein one of the two gear lines (40a, 40b) is disposed, a lubricant reservoir (35) being disposed between the two gear lines (40a, 40b).
    [0002]
    2. A drive housing for turbomachine equipment, according to claim 1, the lubricant reservoir (35) being integrated in the casing (30).
    [0003]
    3. Gearbox for turbomachine equipment, according to one of claims 1 to 2, the casing (30) being a first casing, and the lubricant reservoir (35) being a second casing mounted in the first casing.
    [0004]
    4. A drive housing for turbomachine equipment according to one of claims 1 or 2, the casing (30) being a casting.
    [0005]
    5. Drive unit for turbomachine equipment, according to one of claims 1 or 2, the casing (30) being a part produced by additive manufacturing.
    [0006]
    6. Gearbox for turbomachine equipment, according to one of claims 4 or 5, the lubricant reservoir (35) being a cavity formed in the casing (30).
    [0007]
    7. A drive unit for turbomachine equipment, according to claim 1, the casing (30) being a first casing, and the lubricant reservoir (35) being a second casing mounted against the first casing.
    [0008]
    8. Drive unit for turbomachine equipment according to one of claims 1 to 7, the lubricant reservoir (35) being a main reservoir.
    [0009]
    9. A drive housing for turbomachine equipment according to one of claims 1 to 7, the lubricant reservoir (35) being an auxiliary reservoir.
    [0010]
    10. Turbomachine comprising a drive unit for equipment according to one of claims 1 to 9, the drive housing for equipment being disposed in the central zone, located between a primary stream and a secondary vein of the turbomachine.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3094829B1|2019-11-13|Accessory gearbox
    EP1777393B1|2008-09-10|Device for mechanical power extraction from HP- and LP-shaft of atwo-spool engine
    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
    FR2987416A1|2013-08-30|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.
    EP2045447B1|2015-07-08|Intermediate casing of a turbofan engine and corresponding turbofan engine
    EP3377732B1|2021-05-19|Front part of a turbomachine
    EP3137741B1|2020-09-09|Aircraft turbine engine with improved drawing of mechanical power
    CA3012406A1|2017-08-03|Axially-partitioned oil-distribution wheel, and planetary reduction gear comprising such a wheel
    CA2951196A1|2015-12-17|A turbine engine comprising a drive system for a device such as an accessories case
    EP2867551B1|2016-05-25|Bearing with lubrication means and system for changing the pitch of fan blades of an aircraft turbofan engine equipped with said bearing
    FR3013325A1|2015-05-22|PRESSURE OIL SUPPLY DEVICE OF A TURBOMACHINE LINEAR ACTUATOR
    EP3049327B1|2017-08-09|Device for supplying hydraulic fluid to a ram and mechanism for controlling the pitch of the blades of a turbine engine propeller comprising the ram
    EP2028352B1|2011-03-02|Gas turbine engine with means of driving the turbine accessory drive gearbox assembly and method of assembling said engine
    FR2987402A1|2013-08-30|Fan module for double-flow turbojet, has reducer carried by support casing that is able to be fixed on support of turbojet such that reducer is able to be mounted on fan module beforehand or during simultaneous assembly of fan module
    CA2952506A1|2015-12-30|Device and method for lubricating a turbomachine rolling bearing
    EP3137740B1|2018-07-25|Assembly for aircraft turbine engine and method for mounting same
    FR3009028A1|2015-01-30|PROPULSIVE AIRCRAFT SYSTEM WITH AUXILIARY BLOWER DRAINED IN ROTATION BY GEAR AND METHOD FOR PROPULSION THEREOF
    WO2016146931A1|2016-09-22|One-piece turbine nozzle for a gas turbine engine
    FR3023585A1|2016-01-15|INTERMEDIATE CASTER FOR A TURBOREACTOR
    FR3005486A1|2014-11-14|LUBRICATION IN A TURBOMACHINE
    FR3001496A1|2014-08-01|Device for lubrication of bearing of rotating shaft of direct drive turboshaft engine for aircraft, has nozzle radially projecting lubricant, and support ring arranged to convey lubricant from supply conduit to nozzle during lubrication
    FR3106155A1|2021-07-16|GEAR LUBRICATION SYSTEM FOR AN AIRCRAFT TURBOMACHINE
    FR3042820A1|2017-04-28|DEVICE FOR VENTILATION OF A TURBOMACHINE COMPARTMENT
    FR3045105A1|2017-06-16|CIRCUIT FOR COOLING AND / OR HEATING A FLUID COMPRISING A HEAT EXCHANGER AIR DEHILE / FLUID
    同族专利:
    公开号 | 公开日
    US20160333792A1|2016-11-17|
    CA2936476A1|2015-07-23|
    RU2666265C2|2018-09-06|
    JP2017503964A|2017-02-02|
    WO2015107300A1|2015-07-23|
    RU2016129017A|2018-02-28|
    EP3094829B1|2019-11-13|
    EP3094829A1|2016-11-23|
    RU2016129017A3|2018-07-02|
    US10077715B2|2018-09-18|
    FR3016407B1|2016-02-19|
    JP6515108B2|2019-05-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2978869A|1956-11-01|1961-04-11|Bristol Siddeley Engines Ltd|Engine accessory mounting arrangements|
    WO1987004222A1|1985-12-27|1987-07-16|Sundstrand Corporation|Integral gear box and electrical generating system|
    FR2941744A1|2009-01-30|2010-08-06|Hispano Suiza Sa|ASSEMBLY OF AN ACCESSORY RELAY HOUSING AND AN OIL TANK|EP3153255A1|2015-10-10|2017-04-12|Diehl Defence GmbH & Co. KG|Housing for a transmission and use of an additives production process|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|
    FR2607185B1|1986-11-20|1990-05-04|Snecma|LUBRICATION SYSTEM FOR A TURBOMACHINE STARTER|
    DE10359109A1|2003-12-17|2005-07-21|Deere & Company, Moline|Gear arrangement for a vehicle|
    US8192143B2|2008-05-21|2012-06-05|United Technologies Corporation|Gearbox assembly|
    US9816441B2|2009-03-30|2017-11-14|United Technologies Corporation|Gas turbine engine with stacked accessory components|
    SE534755C2|2010-04-08|2011-12-06|Scania Cv Ab|Lubrication system for a vehicle gearbox|
    US8347637B2|2010-05-25|2013-01-08|United Technologies Corporation|Accessory gearbox with internal layshaft|
    US20130180262A1|2012-01-18|2013-07-18|Hung Duong|Gas turbine engine accessory gearbox|
    US9194294B2|2012-05-07|2015-11-24|United Technologies Corporation|Gas turbine engine oil tank|
    US8973465B2|2012-07-20|2015-03-10|United Technologies Corporation|Gearbox for gas turbine engine|
    FR2995053B1|2012-09-03|2016-03-04|Snecma|TURBOMACHINE MOVEMENT GEAR BOX COMPRISING A GEAR-LINKED CINEMA CHAIN EXTENDING IN NON-PARALLEL PLANS|
    US10145260B2|2013-06-06|2018-12-04|Safran Aircraft Engines|Accessory drive case for a turboprop|
    FR3008463B1|2013-07-10|2015-08-07|Hispano Suiza Sa|COMPACT DRIVE HOUSING STRUCTURE FOR AIRCRAFT TURBOMACHINE|
    FR3008462B1|2013-07-10|2016-12-23|Hispano Suiza Sa|INTEGRATION OF A GEAR TRAIN IN A DRIVE GEAR FOR DRIVE HOUSING FOR TURBOMACHINE|
    FR3011882B1|2013-10-11|2018-01-26|Hispano Suiza Sa|ACCESSORY DRIVE HOUSING FOR TURBOMACHINE|
    FR3017658B1|2014-02-18|2019-04-12|Safran Transmission Systems|EQUIPMENT DRIVE HOUSING FOR TURBOMACHINE|
    FR3027367B1|2014-10-17|2018-02-09|Safran Transmission Systems|EQUIPMENT SUPPORT FOR A TURBOMACHINE COMPRISING A MAGNETIC REDUCER|
    US9845735B2|2015-01-14|2017-12-19|United Technologies Corporation|System and apparatus for diversified gearbox|
    US10662878B2|2016-02-03|2020-05-26|Honeywell Internatioanl Inc.|Compact accessory systems for a gas turbine engine|FR3033009B1|2015-02-24|2017-08-25|Hispano Suiza Sa|ASSEMBLY COMPRISING A HYDRODYNAMIC BEARING PROVIDED WITH A LUBRICANT STORAGE RESERVE|
    DE102016008641B4|2015-07-21|2020-08-06|Mazda Motor Corporation|Automatic transmission and manufacturing process therefor|
    US10107135B2|2015-10-26|2018-10-23|United Technologies Corporation|Gas turbine engine with gearbox health features|
    US10247296B2|2016-12-12|2019-04-02|General Electric Company|Additively manufactured gearbox with integral heat exchanger|
    US10502142B2|2017-04-11|2019-12-10|United Technologies Corporation|Turbine engine gearbox assembly with sets of inline gears|
    US10823080B2|2017-05-31|2020-11-03|General Electric Company|Dual accessory gearbox|
    US10731566B2|2017-10-18|2020-08-04|Honeywell International Inc.|Compact accessory systems for a gas turbine engine|
    GB201806028D0|2018-04-12|2018-05-30|Rolls Royce Plc|Accessory gearbox|
    法律状态:
    2015-01-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-22| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-05| 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 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450342A|FR3016407B1|2014-01-16|2014-01-16|TRAINING BOX FOR EQUIPMENT|FR1450342A| FR3016407B1|2014-01-16|2014-01-16|TRAINING BOX FOR EQUIPMENT|
    PCT/FR2015/050092| WO2015107300A1|2014-01-16|2015-01-15|Accessory gearbox|
    RU2016129017A| RU2666265C2|2014-01-16|2015-01-15|Gearbox|
    JP2016546018A| JP6515108B2|2014-01-16|2015-01-15|Accessory gearbox|
    CA2936476A| CA2936476A1|2014-01-16|2015-01-15|Accessory gearbox|
    US15/111,618| US10077715B2|2014-01-16|2015-01-15|Accessory gearbox|
    EP15705631.8A| EP3094829B1|2014-01-16|2015-01-15|Accessory gearbox|
    [返回顶部]