• 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 turboprop (19) comprising a propeller shaft (21) and a gas generator (22) running along the propeller shaft (21), this gas generator (22) comprising a high pressure shaft ( 24) and a hollow low pressure shaft (28) extending one along the same longitudinal axis (AX '), the low pressure shaft (28) having a rear end coupled to a rear end of the propeller shaft (21) by a gearbox (37). It comprises an accessory box (39) contiguous to the gearbox (37) being located opposite a rear end of the low pressure shaft (28), and coupled to the rear end of the high pressure shaft ( 24) by a shaft passing through the low pressure shaft (28).
    公开号:FR3058470A1
    申请号:FR1660909
    申请日:2016-11-10
    公开日:2018-05-11
    发明作者:Nora EL GHANNAM；Marie Gerard Nicq Geoffroy；Laurent Louis Perrier Mathieu
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    DESCRIPTION
    TECHNICAL AREA
    The invention relates to the integration of an accessory box into a 5-spindle turboprop.
    PRIOR STATE OF THE ART
    A turboprop is an aircraft engine comprising a non-fairing propeller propelled by a gas turbine called a gas generator, and the thrust of which is generated only by this propeller.
    The invention relates to the integration of an accessory box, usually designated by the acronym AGB (Auxiliary Géra Box), into a turboprop with a remote shaft. Such an accessory box comprises at least one line of pinion gears for driving additional accessories or equipment at rotational speeds adapted to each equipment. This equipment typically includes one or more oil and fuel pumps, a starter, and an alternator.
    In a turboprop with offset shaft, such as the turboprop 1 of FIG. 1, the propeller shaft 2 extends along a longitudinal axis AX over the entire length of the propellant, and the gas generator 3 extends parallel to the propeller shaft 2. The gas generator 3 contains a high pressure rotary body 4 located in its front part and ending in a so-called high pressure shaft 6, as well as a low pressure turbine body 7 located in its part rear and which ends in a low pressure shaft 8.
    The low pressure turbine 7 is independent in rotation of the high pressure body 4, but they both rotate about the same axis AX 'parallel to the axis AX of the propeller shaft. This low pressure turbine 7 whose rotation speed is lower than the speed of the high pressure body, is supplied with pressurized gas and in the expansion phase from the high pressure body 4.
    The high pressure body 4 and the low pressure body 7 with their shafts rotate about the same axis AX 'while being independent of each other. The assembly is surrounded by an outer casing 10 formed of casings and extending over the majority of the length of the gas generator.
    A reduction gear 9 located at the rear of the turboprop is coupled on the one hand to the low pressure shaft 8 which passes through a corresponding nozzle 11, and on the other hand to the rear end of the propeller shaft 2. The reduction gear 9 are thus located at the rear of the turboprop, that is to say at its end opposite to the front end which comprises the propulsion propeller 12.
    As visible in FIG. 1, the front end of the gas generator 3 is equipped with an air inlet sleeve 14, in the form of a wall of revolution formed by a casing or the like surrounding the high pressure shaft . The accessory box, identified by 16, is attached to the lower part of the casing of the gas generator and driven by the high pressure shaft 6.
    This drive is provided by a radial shaft 17 perpendicular to the high pressure propeller shaft 6 which is coupled to a front part of this shaft by two bevel gears not visible in the figure. This radial shaft 17 passes through the wall of the air inlet sleeve 14 to be coupled by its other end to the accessory box 16 by means of another coupling.
    This other coupling is provided by another bevel gear comprising two other bevel gears for driving a main shaft 18 of the accessory box 16, which extends parallel to the high pressure shaft 6 and the shaft propeller 2.
    With the architecture of FIG. 1, the maintenance of the accessory box is complicated by the fact that it is located in the lower part of the turboprop engine, that is to say of awkward accessibility, and that it is driven in rotation by two bevel gear bevel gears making it large and heavy.
    The object of the invention is to provide a turboprop architecture in which the accessory box is integrated in a way that is both compact and accessible.
    STATEMENT OF THE INVENTION
    To this end, the subject of the invention is a turboprop engine comprising a propeller shaft and a gas generator which runs along this propeller shaft, this gas generator comprising a high pressure shaft and a hollow low pressure shaft extending l '' and one along the same longitudinal axis, the low pressure shaft having a rear end coupled to a rear end of the propeller shaft via a reduction gear characterized in that it comprises a box of accessories attached to the reducer, and coupled to the rear end of the high pressure shaft via a drive shaft passing through the low pressure shaft.
    The mounting of the accessory box attached to the rear of the gearbox facilitates maintenance access to the accessory box and also to the other components of the turboprop. This arrangement also makes it possible to reduce the overall section of the turboprop to optimize its aerodynamic line and its performance. In addition, the center of gravity of the engine is thus shifted backwards, which is beneficial as regards its attachment to the wing which carries it.
    The invention also relates to a turboprop thus defined, in which the accessory box is carried by the reduction gear.
    The invention also relates to a turboprop thus defined, in which the drive shaft passes through the reduction gear and a part of the accessory box to be extractable from the rear of the turboprop.
    The invention also relates to a turboprop thus defined, in which the reduction gear comprises a bearing carrying the drive shaft of the accessory box.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Figure 1 already described is a side view of a deported shaft turboprop of the prior art;
    Figure 2 is a side view of a turboprop according to the invention;
    Figure 3 is a detailed side view of the integration of the accessory box according to the invention.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
    The basic idea of the invention is to provide, in a turboprop architecture with a remote shaft, to mount the accessory box at the rear of the reducer by coupling it to a rear end of the high pressure shaft of the gas generator. In this configuration, the accessory box is easily accessible for maintenance, while being compactly integrated.
    The turboprop 19 with an offset shaft which is shown in FIG. 2 comprises a propeller shaft 21 extending along an axis AX, and a gas generator 22 skirting this propeller shaft 21. As can be seen in FIG. 2, the gas generator 22 has a shape extending longitudinally, and which runs along the propeller shaft 21 extending parallel thereto at a short distance therefrom. This gas generator 22 includes a high pressure rotary body 23 located in its front part and ending in a so-called high pressure shaft 24, as well as a low pressure body 27 located in its rear part which ends in a so called low pressure shaft. 28. The low pressure body Y1 which is independent in rotation from the high pressure body 23 is supplied with pressurized gas and in the expansion phase which comes from the high pressure body 23.
    The high pressure body 23 and the low pressure body 27 with their shafts rotate about the same axis AX 'while being independent of each other, and they are located respectively in the front part and in the rear part of the generator. gas. The assembly is surrounded by an outer casing 29 formed of casings and extending over the majority of the length of the gas generator.
    The casing 29 is extended at the front part of the gas generator 22 by a curved air inlet pipe 31, comprising an intake mouth 32 for collecting air in order to convey it at the inlet of the gas generator .
    The mouth 32 is located under the hub 33 of the propeller 34 carried by the front end of the propeller shaft 21, to receive a sufficient air flow. The rear of the pipe 31 is coupled to the inlet 26 of the casing 29, in order to supply the gas generator 22 with the air collected by the intake mouth 32.
    The rear end of the low pressure shaft 28 passes through the wall of an exhaust nozzle 36 which is connected to a downstream end of the casing 29, to be coupled to a reduction gear 37 to which the rear end is also coupled of the propeller shaft 21.
    The low pressure shaft 28 thus rotates the propeller 34 by means of the reduction gear 37, the propeller 34 rotating at a speed multiplied relative to the speed of the low pressure shaft 28.
    The low pressure shaft 28 is a hollow shaft which passes through an opening formed in a downstream portion 38 of the wall of this nozzle, this opening forming a movement passage orifice for transmitting the movement of the shaft 28 to the reduction gear 37 in order to '' drive the propeller.
    An accessory box 39 is coupled to the high pressure shaft 24 by an additional drive shaft 40, one end of which is coupled to a mechanism of the accessory box 39 to drive it in rotation. This drive shaft 40 passes through the reducer 37 as well as the hollow low pressure shaft 28 and the low pressure body 27, in order to be coupled to a rear end of the high pressure shaft 24. This box of accessories 39 is thus located opposite a rear end of the low pressure shaft 28.
    The reduction gear 37 advantageously comprises at its rear wall 47 which is crossed by this drive shaft, a bearing supporting the drive shaft not visible in the drawings.
    The drive shaft of the accessory box 39 passes through the entire thickness of the reducer 37 to extend inside the low pressure shaft 28 so as to be coupled to a rear end of the high shaft pressure 24. Advantageously, this drive shaft can be extracted from the rear of the turbo propellant, through the reduction gear and the accessories box.
    Thus, and as visible in FIG. 2, the rear portion of the turboprop comprises successively in the longitudinal direction of the axes AX and AX ', the exhaust nozzle 36, the reduction gear 37, and the accessories box 39.
    The accessories box 39 is thus directly coupled in line on the axis AX 'of the high pressure and low pressure shafts at the rear of the turboprop, that is to say that it is located at the rear end of the turboprop.
    This accessory box 39 which is coupled to the high pressure shaft 24 comprises a casing 41 forming a chassis, which encloses a line of pinions, and which carries a set of elements 42, 43, 44 also called equipment or accessories. These accessories include for example one or more oil and fuel pumps, an alternator and possibly a starter to drive the high pressure shaft 24 when the engine is to be started. These different elements 42, 43, 44 are rotated at different speeds by the gear.
    As can be seen more clearly in FIG. 3, the accessory box 39 is carried by the reducer 37, being here attached to a rear face 47 of this reducer, this rear face extending substantially perpendicular to the axis AX of the propeller. Furthermore, the drive shaft 40 advantageously passes through the reduction gear 37 and possibly a part of the accessory box 39 to be extractable from the rear of the turboprop.
    权利要求:
    Claims (4)
    [1" id="c-fr-0001]
    1. Turbopropeller (19) comprising a propeller shaft (21) and a gas generator (22) which runs along this propeller shaft (21), this gas generator (22) comprising a high pressure shaft (24) and a hollow low pressure shaft (28) extending
    5 both on the same longitudinal axis (AX '), the low pressure shaft (28) having a rear end coupled to a rear end of the propeller shaft (21) via 'a reducer (37) characterized in that it comprises an accessory box (39) attached to the reducer (37), and coupled to the rear end of the high pressure shaft (24) by means of a drive shaft (40) passing through the shaft
    10 low pressure (28).
    [2" id="c-fr-0002]
    2. Turboprop according to claim 1, in which the accessories box (39) is carried by the reduction gear (37).
    15
    [3" id="c-fr-0003]
    3. Turboprop according to claim 1 or 2, wherein the drive shaft (40) passes through the reducer (37) and part of the accessory box (39) to be extractable from the rear of the turboprop.
    [4" id="c-fr-0004]
    4. Turbopropellers according to claim 3, wherein the reducer
    20 (37) has a bearing carrying the drive shaft of the accessory box (39).
    S60494
    1/2
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3538751B1|2021-09-15|Turboprop engine comprising a gas generator and an accessory box coupled to a rear end of a high pressure shaft of the gas generator
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    EP1691056B1|2008-09-10|Bypass turbofan engine with means to drive the gearbox
    EP3155234A1|2017-04-19|A turbine engine comprising a drive system for a device such as an accessories case
    FR2866070A1|2005-08-12|TURBOREACTOR WITH HIGH DILUTION RATE
    EP0395497B1|1993-02-24|Counter rotating prop-fan engine
    EP3283747B1|2020-09-09|Turbomachine with counter rotating propellers upstream of the gas generator
    FR2921423A1|2009-03-27|Double-body turbo machine e.g. jet engine, for airplane, has selective coupling units intercalated between shaft and two transmission shafts to connect shaft respectively to transmission shafts during starting and operating phases
    WO2015107300A1|2015-07-23|Accessory gearbox
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    FR2971816A1|2012-08-24|GEARBOX DRIVE SHAFT OF AUXILIARY MACHINES OF A TURBOJET ENGINE
    CA2917431A1|2015-02-12|Epicyclic reduction gear with fluid transfer pipes, and propeller turbomachine for an aircraft with such a reduction gear
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    FR2569232A1|1986-02-21|ADJUSTABLE EXHAUST NOZZLE FOR A GAS TURBOMACHINE
    FR3060661A1|2018-06-22|PROPELLER SHAFT TURBOPROSER COMPRISING A BOX OF ACCESSORIES
    FR2921341A1|2009-03-27|Multi-flow turbojet-engine i.e. turbofan engine, suspension for airplane, has rear fixation unit with connection unit that fixes case and strut, where rear and front fixation units respectively transmit vertical/lateral and torque efforts
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    FR2919344A1|2009-01-30|Turbofan for aircraft, has fan conduit with external and internal rotation walls connected by single tubular radial arm permitting passage of electrical cables and fluid conduits e.g. air conduit, oil conduit and fuel conduit
    FR3021296A1|2015-11-27|DUAL PROPELLER PROPELLER ASSEMBLY FOR AIRCRAFT
    FR3061147A1|2018-06-29|AIRBORNE TYPE AIRBORNE TURBOPROPOWER WITH DEPTH TREE COMPRISING MEANS OF SUSPENSION TO AN AIRCRAFT PYLON
    FR3035156A1|2016-10-21|DOUBLET TURBOMOTOR WITH CONTRAROTATIVE PROPELLERS HAS BEFORE THE GAS GENERATOR
    同族专利:
    公开号 | 公开日
    FR3058470B1|2019-05-10|
    EP3538751A1|2019-09-18|
    US20190331028A1|2019-10-31|
    US10927766B2|2021-02-23|
    WO2018087478A1|2018-05-17|
    EP3538751B1|2021-09-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3025025A|1959-05-02|1962-03-13|Daimler Benz Ag|Propulsion system for airplanes|
    WO2012004516A1|2010-07-06|2012-01-12|Turbomeca|Method and architecture for recombining the power of a turbomachine|
    US20120128487A1|2010-11-24|2012-05-24|David John Howard Eames|Remote shaft driven open rotor propulsion system with electrical power generation|
    EP2774852A2|2013-03-05|2014-09-10|Rolls-Royce plc|Gas turbine engine installation|
    WO2004074655A1|2003-02-24|2004-09-02|Pratt & Whitney Canada Corp.|Low volumetric compression ratio integrated turbo-compound rotary engine|
    FR3017159B1|2014-01-31|2016-03-04|Snecma|AIR SUPPLYING AN AIR CONDITIONING CIRCUIT OF A CABIN OF AN AIRCRAFT FROM ITS TURBOPROPULSOR|
    US10738709B2|2017-02-09|2020-08-11|Pratt & Whitney Canada Corp.|Multi-spool gas turbine engine|US10465611B2|2016-09-15|2019-11-05|Pratt & Whitney Canada Corp.|Reverse flow multi-spool gas turbine engine with aft-end accessory gearbox drivingly connected to both high pressure spool and low pressure spool|
    US11174916B2|2019-03-21|2021-11-16|Pratt & Whitney Canada Corp.|Aircraft engine reduction gearbox|
    US11268453B1|2021-03-17|2022-03-08|Pratt & Whitney Canada Corp.|Lubrication system for aircraft engine reduction gearbox|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-11| PLSC| Publication of the preliminary search report|Effective date: 20180511 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660909|2016-11-10|
    FR1660909A|FR3058470B1|2016-11-10|2016-11-10|TURBOPROPULSEUR COMPRISING A GAS GENERATOR AND AN ACCESSORY BOX ACCOUPLED TO A REVERSE END OF A HIGH PRESSURE TREE OF THE GAS GENERATOR|FR1660909A| FR3058470B1|2016-11-10|2016-11-10|TURBOPROPULSEUR COMPRISING A GAS GENERATOR AND AN ACCESSORY BOX ACCOUPLED TO A REVERSE END OF A HIGH PRESSURE TREE OF THE GAS GENERATOR|
    EP17800919.7A| EP3538751B1|2016-11-10|2017-11-09|Turboprop engine comprising a gas generator and an accessory box coupled to a rear end of a high pressure shaft of the gas generator|
    US16/347,300| US10927766B2|2016-11-10|2017-11-09|Turboprop comprising a gas generator and an accessory box coupled to a rear end of a high pressure shaft of the gas generator|
    PCT/FR2017/053057| WO2018087478A1|2016-11-10|2017-11-09|Turboprop engine comprising a gas generator and an accessory box coupled to a rear end of a high pressure shaft of the gas generator|
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