公开(公告)号：US20110296842A1

公开(公告)日：2011-12-08

申请号：US13154775

申请日：2011-06-07

申请人： Laurent Donatien BEHAGHEL ,  Frederic Dallaine ,  Delphine Leroux ,  Benjamin Philippe Pierre Pegouet

发明人： Laurent Donatien BEHAGHEL ,  Frederic Dallaine ,  Delphine Leroux ,  Benjamin Philippe Pierre Pegouet

IPC分类号： F23R3/42

CPC分类号： F01D3/04 ,  F01D5/046 ,  F01D5/081 ,  F01D25/12 ,  F01D25/162 ,  F02C7/06 ,  F02C7/18 ,  F04D27/0207 ,  F04D29/051 ,  F04D29/0513 ,  F04D29/0516 ,  F05D2240/12 ,  F05D2260/20

摘要： Inner combustion chamber casing of a turbomachine, which casing is intended to be placed downstream of a centrifugal compressor, the said casing having the shape of a disc, pierced by a central circle, and comprising on its disc at least one guide vane of the drawn-off air, the said guide vane extending longitudinally over the said disc between the periphery of the disc and the central circle and spreading out axially from the disc so as to form with the downstream face of the said centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor,characterized in that the said guide vane has a curved shape orienting in a radial direction at the level of its most central end.

摘要翻译： 涡轮机的内燃室壳体，该壳体旨在放置在离心压缩机的下游，所述壳体具有由中心圆刺穿的圆盘形状，并且在其盘上包括至少一个所绘制的导叶 所述导向叶片在盘的周边和中心圆之间在所述盘上纵向延伸并且从盘轴向扩散，以便与所述离心式压缩机的下游面形成用于空气的引导通道 其在从所述压缩机出来时被抽出，其特征在于，所述导向叶片具有在其最中心端的水平处沿径向定向的弯曲形状。

公开(公告)号：US08938975B2

公开(公告)日：2015-01-27

申请号：US13154775

申请日：2011-06-07

申请人： Laurent Donatien Behaghel ,  Frederic Dallaine ,  Delphine Leroux ,  Benjamin Philippe Pierre Pegouet

发明人： Laurent Donatien Behaghel ,  Frederic Dallaine ,  Delphine Leroux ,  Benjamin Philippe Pierre Pegouet

IPC分类号： F02C7/12 ,  F01D3/04 ,  F01D5/04 ,  F01D5/08 ,  F01D25/12 ,  F01D25/16 ,  F02C7/06 ,  F02C7/18 ,  F04D27/02 ,  F04D29/051

CPC分类号： F01D3/04 ,  F01D5/046 ,  F01D5/081 ,  F01D25/12 ,  F01D25/162 ,  F02C7/06 ,  F02C7/18 ,  F04D27/0207 ,  F04D29/051 ,  F04D29/0513 ,  F04D29/0516 ,  F05D2240/12 ,  F05D2260/20

摘要： An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.

摘要翻译： 提供了旨在放置在离心式压缩机下游的涡轮机的内燃机室壳体。 壳体具有由中心圆刺穿的盘的形状，并且在其盘上包括排出的空气的至少一个导向叶片。 导向叶片在盘的周边和中心圆之间在盘上纵向延伸并且从盘轴向扩展，以便与离心式压缩机的下游面形成空气的引导通道，该引导通道从出口 所述压缩机。 导向叶片具有在其最中心端的水平方向上沿径向定向的弯曲形状。

公开(公告)号：US20110076135A1

公开(公告)日：2011-03-31

申请号：US12994969

申请日：2009-05-25

申请人： Alain Dominique Gendraud ,  Delphine Leroux ,  Jean-Luc Le Strat ,  Pascal Tatiossian

发明人： Alain Dominique Gendraud ,  Delphine Leroux ,  Jean-Luc Le Strat ,  Pascal Tatiossian

IPC分类号： F04D29/66

CPC分类号： F01D11/24 ,  F05D2260/30 ,  F05D2260/96

摘要： A high pressure turbine of a turbomachine such as a turbojet, in which a control box of radial clearances of rotating blades are provided. An annular element including a determined flexibility has one end fixed to an annular support and the other end supported by a simple axial bearing with a given pressure on the upstream side of the control box. Thus, disturbing vibration loads are prevented at the attachment points of the control box with the external casing of turbines, thereby also eliminating the risk of cracks occurring.

摘要翻译： 诸如涡轮喷气发动机的涡轮机的高压涡轮机，其中设置有旋转叶片的径向间隙的控制箱。 包括确定的柔性的环形元件具有固定到环形支撑件的一端，另一端由在控制箱的上游侧具有给定压力的简单轴向轴承支撑。 因此，在与涡轮机的外壳的控制箱的附接点处防止了扰动的振动载荷，从而也消除了发生裂纹的风险。