专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08622699B2 Device adapted to be fitted with propeller blades 有权
标题翻译：适用于安装螺旋桨叶片的装置
公开(公告)号：US08622699B2
公开(公告)日：2014-01-07
申请号：US12904852
申请日：2010-10-14
申请人： François Gallet , Patrick Morel , Wouter Balk
发明人： François Gallet , Patrick Morel , Wouter Balk
IPC分类号： F01D7/00
CPC分类号： F01D7/00 , B64C11/04 , F05D2260/79 , Y02T50/672 , Y02T50/673
摘要： A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.
摘要翻译：适于安装有螺旋桨叶片的装置包括第一保持环，其在其周边上包括多个径向孔; 以及第二保持环，其包括在其周边上的多个径向孔，所述第一和第二保持环在径向方向上一个地安装在另一个的顶部上，所述第一保持环中的每个孔与所述第二保持环中的孔相对地定位保持环，第一保持环中的孔与第二保持环中的孔相对布置，形成适于接收叶片脚的孔对。

2. 发明申请

US20110176924A1 DEVICE ADAPTED TO BE FITTED WITH PROPELLER BLADES 有权
标题翻译：适用于螺旋叶片的装置
公开(公告)号：US20110176924A1
公开(公告)日：2011-07-21
申请号：US12904852
申请日：2010-10-14
申请人： François Gallet , Patrick Morel , Wouter Balk
发明人： François Gallet , Patrick Morel , Wouter Balk
IPC分类号： B64C11/04
CPC分类号： F01D7/00 , B64C11/04 , F05D2260/79 , Y02T50/672 , Y02T50/673
摘要： A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.
摘要翻译：适于安装有螺旋桨叶片的装置包括第一保持环，其在其周边上包括多个径向孔; 以及第二保持环，其包括在其周边上的多个径向孔，所述第一和第二保持环在径向方向上一个地安装在另一个的顶部上，所述第一保持环中的每个孔与所述第二保持环中的孔相对地定位保持环，第一保持环中的孔与第二保持环中的孔相对布置，形成适于接收叶片脚的孔对。

3. 发明授权

US09309808B2 Turboprop provided with a blade-positioning device 有权
标题翻译：涡轮螺旋桨飞机配备有刀片定位装置
公开(公告)号：US09309808B2
公开(公告)日：2016-04-12
申请号：US13578926
申请日：2011-02-11
申请人： Wouter Balk , Gilles Alain Charier , François Gallet
发明人： Wouter Balk , Gilles Alain Charier , François Gallet
IPC分类号： B64C11/32 , F02C6/20 , F01D7/00
CPC分类号： F02C6/206 , B64C11/32 , F01D7/00 , F05D2220/325
摘要： A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis.
摘要翻译：一种涡轮螺旋桨飞机，其设置有包括固定机舱的叶片定位装置，包括多个叶片根部的旋转机舱，涡轮机，固定和旋转机舱和涡轮机沿着纵向轴线同轴;叶片定位装置，其包括用于每个叶片被配置为将适于将平移运动转换成旋转运动的运动的装置，用于将运动变换的装置中的每一个固定到旋转机舱并且适于枢转叶片。定位装置设置在固定机舱的内表面和涡轮的外表面之间，该定位装置包括一个构件，该构件包括固定到固定机舱的主体和用于沿着基本上平行于纵向轴线的轴线滑动的杆。

4. 发明申请

US20120308385A1 TURBOPROP PROVIDED WITH A BLADE-POSITIONING DEVICE 有权
标题翻译： TURBOPROP用刀片定位装置提供
公开(公告)号：US20120308385A1
公开(公告)日：2012-12-06
申请号：US13578926
申请日：2011-02-11
申请人： Wouter Balk , Gilles Alain Charier , François Gallet
发明人： Wouter Balk , Gilles Alain Charier , François Gallet
IPC分类号： F01D7/00 , B64C11/32
CPC分类号： F02C6/206 , B64C11/32 , F01D7/00 , F05D2220/325
摘要： A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis.
摘要翻译：一种涡轮螺旋桨飞机，其设置有包括固定机舱的叶片定位装置，包括多个叶片根部的旋转机舱，涡轮机，固定和旋转机舱和涡轮机沿着纵向轴线同轴;叶片定位装置，其包括用于每个叶片被配置为将适于将平移运动转换成旋转运动的运动的装置，用于将运动变换的装置中的每一个固定到旋转机舱并且适于枢转叶片。定位装置设置在固定机舱的内表面和涡轮的外表面之间，该定位装置包括一个构件，该构件包括固定到固定机舱的主体和用于沿着基本上平行于纵向轴线的轴线滑动的杆。

5. 发明申请

US20100205934A1 BYPASS ENGINE WITH CONTRAROTATING TURBINE WHEELS 有权
标题翻译： BYPASS发动机与配套涡轮轮
公开(公告)号：US20100205934A1
公开(公告)日：2010-08-19
申请号：US12707145
申请日：2010-02-17
申请人： François Gallet
发明人： François Gallet
IPC分类号： F02K3/00
CPC分类号： F02C3/107 , F01D1/24 , F02C3/067 , F02K3/072 , F05D2260/4031 , Y02T50/671
摘要： Bypass aeronautical engine comprising a fan (1), an LP compressor (3) and an HP compressor (4), a combustion chamber (5), an HP turbine and at least one LP turbine stage, said LP stage comprising a first movable bladed wheel (9a, 10a) carried by a first turbine shaft and a second movable bladed wheel (9b, 10b, 11b) turning in the opposite direction to said first wheel, said fan being driven by said second wheel via a second turbine shaft (2b) and by said first shaft (2a) via a module for reversing its direction of rotation, wherein the reversing module is produced with the aid of two bevel pinions (19, 21) of the same size, carried respectively by the first and second LP turbine shafts, and with the aid of a reversing pinion (20), the two turbine shafts (2a, 2b) turning in absolute value at the same speed of rotation.
摘要翻译：旁通航空发动机，包括风扇（1），LP压缩机（3）和HP压缩机（4），燃烧室（5），HP涡轮机和至少一个LP涡轮机级，所述LP级包括第一可移动叶片由第一涡轮轴承载的轮（9a，10a）和与所述第一轮相反的方向转动的第二可移动叶轮（9b，10b，11b），所述风扇由所述第二轮经由第二涡轮轴（2b ）和所述第一轴（2a）经由用于反转其旋转方向的模块的所述第一轴（2a），其中所述反转模块借助于相同尺寸的两个斜切小齿轮（19,21）而被分别由所述第一和第二LP 涡轮轴，并且借助于换向小齿轮（20），两个涡轮轴（2a，2b）以相同的旋转速度转动绝对值。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式