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1. 发明申请

US20050175463A1 Control of leak zone under blade platform 有权
标题翻译：控制叶片平台下的泄漏区
公开(公告)号：US20050175463A1
公开(公告)日：2005-08-11
申请号：US10514559
申请日：2003-05-28
申请人： Chantal Giot , Marc Marchi , Christian Gosselin , Eric Bil
发明人： Chantal Giot , Marc Marchi , Christian Gosselin , Eric Bil
IPC分类号： F01D1/00 , F01D5/22 , F01D11/00 , B63H1/26
CPC分类号： F01D5/3015 , F01D5/22 , F01D11/008 , F05D2240/55
摘要： A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.
摘要翻译：一种用于控制涡轮机叶片叶片平台下的泄漏区域的系统，其具有通过径向向内展开的边缘的边缘，并且由叶片的上游和下游径向壁设置在由平台限定的叶片间空腔内的叶片间空腔中，通过轮盘的周边。扩张边缘中的一个上游或下游具有相对于径向平面承载在相邻径向壁的倾斜表面上的弹性区域，使得在离心力的作用下，衬垫倾向于朝着径向壁轴向移动，以改善区域中的密封，并且使得当轮停止时，弹性区域径向向内移动，衬套围绕远离弹性区域的轴线枢转。

2. 发明申请

US20080063515A1 BLEED SYSTEM FOR A LOW-PRESSURE COMPRESSOR OF A TURBOMACHINE 有权
标题翻译：用于涡轮压缩机的低压压缩机的清洗系统
公开(公告)号：US20080063515A1
公开(公告)日：2008-03-13
申请号：US11755934
申请日：2007-05-31
申请人： Eric BIL , Gilles Charier , Philippe Fessou , Patrick Morel
发明人： Eric BIL , Gilles Charier , Philippe Fessou , Patrick Morel
IPC分类号： F04D27/00
CPC分类号： F02K3/075 , F01D17/105 , F04D27/0215 , F04D27/023 , F04D29/545 , F05D2240/55 , F05D2260/50
摘要： The bypass turbomachine comprises, between a primary flowpath (2) and a secondary flowpath (3), a structural intermediate casing (14). A bleed passage (29) allows the diversion of a portion of the gas stream toward the secondary flowpath (3), downstream of support arms (18) situated at the periphery of the intermediate casing. A bleed opening (28) emerges upstream of the support arms (18). A slide valve (22) slides between three positions, namely a closed position in which the slide valve (22) completely blocks off the bleed passage and opening, an intermediate position in which the bleed opening (28) emerging upstream of the support arms (18) is blocked off, while the bleed passage (29) for diverting a portion of the gas stream downstream of the support arms (18) is open, and an open position in which the bleed opening (28) emerging upstream of the support arms (18) and the bleed passage (29) emerging downstream of the support arms are both open.
摘要翻译：旁通涡轮机在主流路（2）和次流路（3）之间包括结构中间壳体（14）。排放通道（29）允许气流的一部分朝着位于中间壳体的周边的支撑臂（18）的下游侧向二级流路（3）转向。出血口（28）出现在支撑臂（18）的上游。滑阀（22）在三个位置之间滑动，即关闭位置，其中滑阀（22）完全阻止排放通道和打开;中间位置，其中出现在支撑臂上游的排气口（28） 18）被阻止，而用于将支撑臂（18）下游的气流的一部分转向的排放通道（29）是打开的，并且打开位置，其中出口开口（28）出现在支撑臂（18）和出现在支撑臂下游的排出通道（29）都是开放的。

3. 发明申请

US20070292271A1 Rotor blade for a compressor or a gas turbine 有权
标题翻译：用于压缩机或燃气轮机的转子叶片
公开(公告)号：US20070292271A1
公开(公告)日：2007-12-20
申请号：US11206156
申请日：2005-08-18
申请人： Eric Bil , Chantal Giot , Thomas Schlesinger
发明人： Eric Bil , Chantal Giot , Thomas Schlesinger
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , F05D2240/80 , F05D2260/94 , F05D2260/941 , Y02T50/671
摘要： Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, comprising a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.
摘要翻译：用于压缩机或燃气轮机的转子叶片，特别是用于涡轮喷气发动机的转子叶片，其包括吸入侧和压力侧，它们在其上游端由前缘并在其下游端由气体的后缘连接，将吸入侧和压力侧连接到叶片根部的平台以及形成在平台的下游部分下方并且包括与后缘成一直线的至少一个切口或切口的加强件，以便减小应力在机翼和平台之间的联合区域。

4. 发明授权

US07214034B2 Control of leak zone under blade platform 有权
标题翻译：控制叶片平台下的泄漏区
公开(公告)号：US07214034B2
公开(公告)日：2007-05-08
申请号：US10514559
申请日：2003-05-28
申请人： Chantal Giot , Marc Marchi , Christian Gosselin , Eric Bil
发明人： Chantal Giot , Marc Marchi , Christian Gosselin , Eric Bil
IPC分类号： F01D11/00
CPC分类号： F01D5/3015 , F01D5/22 , F01D11/008 , F05D2240/55
摘要： A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.
摘要翻译：一种用于控制涡轮机叶片叶片平台下的泄漏区域的系统，其具有通过径向向内展开的边缘的边缘，并且由叶片的上游和下游径向壁设置在由平台限定的叶片间空腔内的叶片间空腔中，通过轮盘的周边。扩张边缘中的一个上游或下游具有相对于径向平面承载在相邻径向壁的倾斜表面上的弹性区域，使得在离心力的作用下，衬垫倾向于朝着径向壁轴向移动，以改善区域中的密封，并且使得当轮停止时，弹性区域径向向内移动，衬套围绕远离弹性区域的轴线枢转。

5. 发明申请

US20070243067A1 Gas turbine or compressor blade 有权
标题翻译：燃气轮机或压缩机叶片
公开(公告)号：US20070243067A1
公开(公告)日：2007-10-18
申请号：US11206155
申请日：2005-08-18
申请人： Eric Bil , Nicolas Hervy , Thomas Schlesinger
发明人： Eric Bil , Nicolas Hervy , Thomas Schlesinger
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , F05D2240/80 , F05D2260/94 , F05D2260/941 , Y02T50/673
摘要： Gas turbine or compressor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases and terminating on a platform, one part of which includes a downstream fairing that includes at least one through-notch that extends substantially between a transverse line passing through the trailing edge and the downstream end of the fairing.
摘要翻译：燃气轮机或压缩机叶片包括凸的外表面或吸入侧以及凹入的内表面或压力侧，这些侧面在其上游端由前缘连接，在其下游端由气体的后缘连接并终止于一个平台，其一部分包括下游整流罩，其包括至少一个通过贯穿后缘的横向线和整流罩的下游端之间延伸的通孔。

6. 发明申请

US20070039310A1 COMPRESSOR COMPRISING A PLURALITY OF CELLS RECONSTITUTING AN ANNULAR VOLUME OF SEPARATION OF FLOWS IN A TURBINE ENGINE 有权
标题翻译：包含多个细胞的压缩机重新构建涡轮发动机中流动分离的静态体积
公开(公告)号：US20070039310A1
公开(公告)日：2007-02-22
申请号：US11465998
申请日：2006-08-21
申请人： Eric Bil , Gilles Alain Charier
发明人： Eric Bil , Gilles Alain Charier
IPC分类号： F02K3/04
CPC分类号： F02K3/06 , F01D5/22 , F02K3/072 , F04D29/526 , F05D2220/36 , F05D2240/40 , F05D2300/603
摘要： This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.
摘要翻译：该涡轮发动机压缩机包括由内部和外部环形壁延伸的分离鼻，所述内部和外部环形壁协同地限定主流（F 1）和次级流（F 2）的分离的环形体积（V）。该体积（V）包括以第一风扇叶片成对分离的细胞形式的多个环形段，这些叶片通过主流（F 1）和二次流（F 2）。这些电池被固定到由上述叶片旋转地驱动的上游环形环和下游环形环。

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