CN102341588A - 通过周转齿轮传动链用于一对反向旋转螺旋桨的驱动机构 - Google Patents
通过周转齿轮传动链用于一对反向旋转螺旋桨的驱动机构 Download PDFInfo
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Abstract
本发明公开了一种驱动行星齿轮(16)和周转齿轮传动链(17)的涡轮机,也包括驱动两个螺旋桨转动的行星小齿轮架(14)和齿圈(10),该涡轮机通过围绕涡轮机支撑轴(19)的柔性套筒(22),而不是通支撑轴本身来连接行星齿轮,以获得柔性组件,该柔性组件在与轴(19)接触时带有限制停止位置,以限制施加于周转齿轮传动链(17)上的寄生内力,而不用耐受由于排除间隙(27)后限制停止的条件下,套筒的松散组件或破裂。
Description
技术领域
本发明涉及通过周转齿轮传动链,用于一对反向旋转螺旋桨的驱动机构。
背景技术
反向旋转螺旋桨是已知的,并且也设想其用在一些将来的飞行器上,以减少燃料消耗。螺旋桨的动力传动可以包括周转齿轮传动链。动力涡轮机(低压)使轴转动,该轴带动行星齿轮(中心齿轮)转动,该行星齿轮(中心齿轮)形成周转齿轮传动链的一部分。行星齿轮本身驱动卫星齿轮和行星小齿轮架,该行星小齿轮架连接其中一个螺旋桨的轴。周转齿轮也包括在其内表面上带齿的外齿圈,该带齿的外齿圈啮合卫星,并且连接另一个螺旋桨的轴。因此,齿轮齿比率的明智选择允许螺旋桨以所要求的速率在两个相反的方向旋转。在文献US-A-4 817 382中描述了这种设置,而文献EP-A-1 887 199公开了这样一种设置:其中周转齿轮传动链中的行星小齿轮架通过柔性接头被支撑在旋转轴的端部,该柔性接头吸收变形及减少齿轮传动链中应力。
周转齿轮传动链的优点在于它结构紧凑,但是大的力施加在其上可能损坏齿。本发明的主要目的是减少这些力,以便它基本上传动传动装置所必需的驱动扭矩,同时减少寄生阻力,像由于齿轮错位所引起的寄生阻力。但是机构必须抵抗在某些情况下所施加的大的力。
发明内容
本发明满足了这种双重要求,其中本发明通常地涉及一种机构,该机构包括:一对反向旋转的螺旋桨,驱动涡轮机,连接涡轮机的轴,包括周转齿轮传动链的传动装置,该周转齿轮传动链带有涡轮机所驱动的中心行星齿轮,驱动其中一个螺旋桨并且装配有卫星齿轮的行星小齿轮架,该卫星齿轮啮合行星齿轮和外齿圈,该外齿圈啮合行星齿轮和驱动另一个螺旋桨,其特征在于它包括连接涡轮机和行星齿轮以驱动它的套筒,该套筒被轴所环绕,并且在弯曲方面比轴更柔性。
该柔性套筒用于代替涡轮机轴来支撑行星齿轮,该涡轮机轴支撑壳体上涡轮转子,并且该套筒根据该行星齿轮所抵抗的径向力,耐受其轴位置中的振动。这减少了周转齿轮传动链中所产生的力。然而,因为固定的涡轮轴和柔性套之间间隙小,所以存在这么一个位置,当大的力施加于传动装置中时,在该位置套筒停止与轴接触。这就防止了过多的柔性,该过多的柔性可以阻止机构正确地运行,甚至引起它的毁坏,作为套筒破裂的第一个结果,并且偶尔可能出现的大的力被传送给刚性和硬的涡轮机轴。
如果涡轮机轴足够长,以至于它提供更稳固的支撑并且当产生推力接触时,就会阻止套筒的悬臂超过涡轮机轴,这是有利的。因此,涡轮机轴的两个支撑轴承之间的距离比其中一个轴承和行星齿轮之间的距离要长。
本发明的这种设置要好于文献EP-A-1 887 199中所示的设置,原因如下:首先,本发明的套筒比参考文献中柔性接头要长,这允许更大的移动,因此更好的柔性,以及内力更大的减少;其次,一旦已经排除间隙,涡轮机轴的支撑对移动提供了清晰的限制,同时保护套筒防止其过度变形;最后,涡轮机轴中套筒的设置可以实现在距离最近的轴支撑轴承的最短距离处设置周转齿轮链,这减少了尺寸和悬臂,同时参考文献中所描述的齿轮传动链更靠近轴承前面,以安装柔性接头。
当套筒在连接涡轮机一端形成半圆弯曲时,制造的套筒柔性更好,或者如果套筒包括带有长方形开口的部分,该开口以与套筒的轴向方向呈45°角度定向,这局部地弱化了套筒,因此该套筒在弯曲方面更有柔性,而同时保持其扭转强度,以便于它可以传送所需要的扭矩。当存在弯曲时,凹进部分可以位于弯曲和主要套筒接触面之一之间的连接处。
如果连接到齿圈的轴比连接到行星小齿轮架的轴更具有柔性,周转齿轮传动链中的力可以被进一步减小。连接到行星小齿轮架的组件比较硬,然后位于行星齿轮组件和比较柔性的齿圈组件之间,这就可以根据施加于每个的力独立地变形。
下面参考附图描述本发明。
附图说明
图1是本发明机构的总的视图。
图2表示周转齿轮传动链的布置。
图3表示周转齿轮传动链的主视图。
图4表示柔性套筒的特定部分。
具体实施方式
参考图1和2,本发明的发动机形成了包括两个螺旋桨1、2的部件,每个螺旋桨设置为绕相同的轴线X进行旋转。上游螺旋桨1安装在第一中空轴3上,下游螺旋桨2安装在第二中空轴4上。第一中空轴3通过一对轴承6和7被支撑在静态壳体5上,越过轴承6和7,该第一中空轴3延伸成带有波纹9的圆锥形套筒8,并且端部向上有齿圈10,该齿圈10带有在内表面上形成的齿。第二中空轴4由第一中空轴3通过两个轴承11和12支撑,并且第二中空轴4延伸成第二圆锥形套筒13,该第二圆锥形套简13包含在第一圆锥形套筒8内部,并且连接行星小齿轮架14。行星小齿轮架14具有围绕圆形分布的卫星齿轮15,该卫星齿轮啮合在齿圈10的外表面上和带有行星(或中心)齿轮16的内表面上。组装形成了传统类型的周转齿轮传动链17,如图3所示。
低压涡轮机18位于静态壳体5的另一侧。它包括是涡轮机轴19的第三中空轴,该涡轮机轴19通过两个轴承20和21支撑静态壳体5上的涡轮机。涡轮机轴19延伸不远离行星齿轮16,然而它们之间是分离的;行星齿轮16与最近的轴承21之间的间隙小于两个轴承20和21之间的距离。柔性套筒22通过将行星齿轮16连接到涡轮机18的转子而驱动它。柔性套筒22通过半圆形弯曲23连接到涡轮机18,该弯曲不会远离和涡轮机轴19的连接。柔性套筒22的主要部件是由涡轮机轴19所环绕的基本上圆柱形的接触面24,并且通过第三端部25延伸超过涡轮机轴19,作为行星齿轮16的支架。长方形开口26形成在套筒22中弯曲23和接触面24连接处,并且在图4中清楚地示出了大部分,它们的延伸方向相对于机构的X轴线方向呈45°,该X轴线方向对应于所有旋转部件(卫星齿轮15除外)的旋转轴。套筒22是柔性的,因为它足够薄,但是它在有凹槽的部分特别地弯曲。
该机构的运行可以描述如下:涡轮机18通过柔性套筒22驱动行星齿轮16,这引起行星小齿轮架14和齿圈10以确定的速度转动,接着是螺旋桨2和1以确定的速度转动。当沿着径向方向的不平衡力强加于行星齿轮16上时,柔性套筒22可以弯曲。相似地,当沿着径向的不平衡力施加于齿圈10时,第一圆锥形套筒8能够在波纹9的位置弯曲。然而,行星小齿轮架14通过第二中空轴4和第二圆锥形套筒13与螺旋桨2的连接是更硬的,这防止周转齿轮传动链17太柔性。并且圆锥形套筒22和涡轮机轴19之间的间隙27在靠近行星齿轮16的轴承21的位置是小的,这限制了可以施加于柔性套筒22的变形于合理的值,并且特别地防止它破裂以及周转齿轮传动链17变得太松。因为柔性套筒22和涡轮机轴19以相同的速度旋转,不会有这种推力状态的任何后果的担心,这种推力状态不会产生任何摩擦。
Claims (6)
1.一种机构,该机构包括:一对反向旋转的螺旋桨(1、2),驱动涡轮机(18),连接涡轮机及通过两个轴承(20、21)支撑涡轮机(18)在静态壳体(5)上的轴(19),包括周转齿轮传动链(17)的传动装置,该周转齿轮传动链(17)带有涡轮机所驱动的中心行星齿轮(16),驱动其中一个螺旋桨(2)并且装配有卫星齿轮(15)的行星小齿轮架(14),该卫星齿轮(15)啮合行星齿轮(16),啮合卫星齿轮(15)和驱动另一个螺旋桨(1)的外齿圈,其特征在于:它包括连接涡轮机(18)和行星齿轮(16)以驱动它的套筒(22),该套筒(22)被轴(19)所环绕,并且和轴(19)分离有间隙(27),在弯曲时比轴更有柔性,并且轴承(20、21)之一和行星齿轮之间的距离小于两个轴承(20、21)之间的距离。
2.根据权利要求1所述的机构,其特征在于:套筒(22)在与涡轮机连接的一端形成半圆形弯曲(23)。
3.根据权利要求1或2所述的机构,其特征在于:它包括带有长方形开口(26)的部分,该开口以与套筒(22)的轴向方向X呈45°角度被定向。
4.根据权利要求2和3所述的机构,其特征在于:所述部分位于距离涡轮机的连接一段距离与弯曲(23)的连接处,在套筒的主要基本上圆柱形的接触面(24)上。
5.根据权利要求1至4中任一权利要求所述的机构,其特征在于:连接齿圈和所述另一个螺旋桨(1)的轴(3、8、9)比连接行星小齿轮架(14)和所述其中一个螺旋桨(2)的轴(4、13)更具有柔性。
6.根据权利要求1至5中任一权利要求所述的机构,其特征在于柔性套筒(22)和涡轮机轴(19)之间的间隙(27)在轴承(21)处是小的,以限制施加于柔性套筒(22)上的变形。
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Application Number | Priority Date | Filing Date | Title |
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FR0951509 | 2009-03-11 | ||
FR0951509A FR2943035B1 (fr) | 2009-03-11 | 2009-03-11 | Dispositif d'entrainement d'une paire d'helices contrarotives par un train epycycloidal |
PCT/EP2010/052963 WO2010102995A1 (fr) | 2009-03-11 | 2010-03-09 | Dispositif d'entrainement d'une paire d'helices contrarotatives par un train epycycloïdal |
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CN102341588A true CN102341588A (zh) | 2012-02-01 |
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EP (1) | EP2406484B1 (zh) |
JP (1) | JP5619786B2 (zh) |
CN (1) | CN102341588B (zh) |
BR (1) | BRPI1009788B1 (zh) |
CA (1) | CA2754175C (zh) |
FR (1) | FR2943035B1 (zh) |
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Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2977636B1 (fr) * | 2011-07-06 | 2013-08-09 | Snecma | Dispositif de lubrification d'un palier a roulement inter-arbres de turbopropulseur a double helice |
FR2979121B1 (fr) * | 2011-08-18 | 2013-09-06 | Snecma | Dispositif de transmission mecanique pour l'entrainement en rotation des helices contrarotatives d'un turbopropulseur a double helice. |
US9182011B2 (en) * | 2012-10-01 | 2015-11-10 | United Technologies Corporation | Fan drive gear system flexible support features |
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FR3001498B1 (fr) | 2013-01-30 | 2015-02-27 | Snecma | Partie fixe de recepteur de turbomachine comprenant un ensemble de maintien en position de servitudes a l'interieur d'un arbre creux fixe |
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FR3008155B1 (fr) * | 2013-07-03 | 2016-10-07 | Snecma | Transmission a reducteurs multiples entre un arbre d'entrainement et une paire d'helices coaxiales a cet arbre |
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US10072571B2 (en) * | 2015-01-15 | 2018-09-11 | United Technologies Corporation | Gas turbine engine split torque fan drive gear system |
FR3034465B1 (fr) | 2015-04-03 | 2017-05-05 | Snecma | Turbomoteur comportant deux flux de ventilation distincts |
GB201516570D0 (en) | 2015-09-18 | 2015-11-04 | Rolls Royce Plc | A Shafting Arrangement |
US10094335B2 (en) | 2015-12-07 | 2018-10-09 | General Electric Company | Compliant shaft with a recursive configuration for turbine engines |
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EP3587772A1 (en) | 2018-06-27 | 2020-01-01 | Rolls-Royce plc | Gas turbine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4817382A (en) * | 1985-12-31 | 1989-04-04 | The Boeing Company | Turboprop propulsion apparatus |
US4936748A (en) * | 1988-11-28 | 1990-06-26 | General Electric Company | Auxiliary power source in an unducted fan gas turbine engine |
US5010729A (en) * | 1989-01-03 | 1991-04-30 | General Electric Company | Geared counterrotating turbine/fan propulsion system |
CN1084614A (zh) * | 1992-04-23 | 1994-03-30 | 普拉塞尔技术有限公司 | 应力得到减小的叶轮叶片 |
CN1854611A (zh) * | 2005-04-27 | 2006-11-01 | 联合工艺公司 | 用于燃气涡轮发动机中的陶瓷燃烧室衬里的弹性金属支撑 |
EP1887199A2 (en) * | 2006-07-31 | 2008-02-13 | General Electric Company | Gas turbine engine assembly |
CN101234668A (zh) * | 2007-01-26 | 2008-08-06 | 斯奈克玛 | 一种带有变距螺旋桨的涡轮螺旋桨发动机 |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS63183226A (ja) * | 1987-01-26 | 1988-07-28 | Mitsubishi Heavy Ind Ltd | 二重反転減速装置 |
US5862706A (en) * | 1996-07-16 | 1999-01-26 | Mcdonnell Douglas Helicopter Company | Shaft deflection controller |
DE19828562B4 (de) * | 1998-06-26 | 2005-09-08 | Mtu Aero Engines Gmbh | Triebwerk mit gegenläufig drehenden Rotoren |
RU2311554C2 (ru) * | 2005-12-23 | 2007-11-27 | Открытое акционерное общество "Авиадвигатель" | Двухконтурный газотурбинный двигатель |
US7591754B2 (en) * | 2006-03-22 | 2009-09-22 | United Technologies Corporation | Epicyclic gear train integral sun gear coupling design |
US7926260B2 (en) * | 2006-07-05 | 2011-04-19 | United Technologies Corporation | Flexible shaft for gas turbine engine |
US7857519B2 (en) * | 2007-12-07 | 2010-12-28 | Pratt & Whitney Canada Corp. | Compact bearing support |
FR2940247B1 (fr) | 2008-12-19 | 2011-01-21 | Snecma | Systeme d'helices contrarotatives entrainees par un train epicycloidal offrant une repartition de couple equilibree entre les deux helices |
-
2009
- 2009-03-11 FR FR0951509A patent/FR2943035B1/fr not_active Expired - Fee Related
-
2010
- 2010-03-09 RU RU2011141090/06A patent/RU2519531C2/ru active
- 2010-03-09 US US13/255,389 patent/US8967950B2/en active Active
- 2010-03-09 EP EP10708757.9A patent/EP2406484B1/fr active Active
- 2010-03-09 WO PCT/EP2010/052963 patent/WO2010102995A1/fr active Application Filing
- 2010-03-09 BR BRPI1009788-0A patent/BRPI1009788B1/pt active IP Right Grant
- 2010-03-09 CN CN201080010196.2A patent/CN102341588B/zh active Active
- 2010-03-09 JP JP2011553422A patent/JP5619786B2/ja active Active
- 2010-03-09 CA CA2754175A patent/CA2754175C/fr active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4817382A (en) * | 1985-12-31 | 1989-04-04 | The Boeing Company | Turboprop propulsion apparatus |
US4936748A (en) * | 1988-11-28 | 1990-06-26 | General Electric Company | Auxiliary power source in an unducted fan gas turbine engine |
US5010729A (en) * | 1989-01-03 | 1991-04-30 | General Electric Company | Geared counterrotating turbine/fan propulsion system |
CN1084614A (zh) * | 1992-04-23 | 1994-03-30 | 普拉塞尔技术有限公司 | 应力得到减小的叶轮叶片 |
CN1854611A (zh) * | 2005-04-27 | 2006-11-01 | 联合工艺公司 | 用于燃气涡轮发动机中的陶瓷燃烧室衬里的弹性金属支撑 |
EP1887199A2 (en) * | 2006-07-31 | 2008-02-13 | General Electric Company | Gas turbine engine assembly |
CN101234668A (zh) * | 2007-01-26 | 2008-08-06 | 斯奈克玛 | 一种带有变距螺旋桨的涡轮螺旋桨发动机 |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105899794A (zh) * | 2014-01-07 | 2016-08-24 | 斯奈克玛 | 用于减速涡轮机的叶片组的旋转驱动的行星减速装置 |
CN105899794B (zh) * | 2014-01-07 | 2018-03-13 | 斯奈克玛 | 用于减速涡轮机的叶片组的旋转驱动的行星减速装置 |
CN106212406A (zh) * | 2016-09-24 | 2016-12-14 | 翟凤平 | 逆驱动路亚 |
CN110268147A (zh) * | 2017-01-30 | 2019-09-20 | 通用电气阿维奥有限责任公司 | 将涡轮发动机齿轮箱连接到发动机核心的方法和系统 |
US11591969B2 (en) | 2017-01-30 | 2023-02-28 | Ge Avio S.R.L. | Method and system of connecting a turbine engine gearbox to engine core |
Also Published As
Publication number | Publication date |
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WO2010102995A1 (fr) | 2010-09-16 |
US20120099988A1 (en) | 2012-04-26 |
EP2406484B1 (fr) | 2013-07-24 |
CN102341588B (zh) | 2014-07-23 |
CA2754175A1 (fr) | 2010-09-16 |
BRPI1009788B1 (pt) | 2020-08-04 |
JP2012520410A (ja) | 2012-09-06 |
EP2406484A1 (fr) | 2012-01-18 |
CA2754175C (fr) | 2016-12-20 |
BRPI1009788A2 (pt) | 2016-03-08 |
JP5619786B2 (ja) | 2014-11-05 |
US8967950B2 (en) | 2015-03-03 |
FR2943035A1 (fr) | 2010-09-17 |
FR2943035B1 (fr) | 2012-09-28 |
RU2011141090A (ru) | 2013-04-20 |
RU2519531C2 (ru) | 2014-06-10 |
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