公开(公告)号：US09970301B2

公开(公告)日：2018-05-15

申请号：US14803798

申请日：2015-07-20

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14 ,  F01D9/04

CPC分类号： F01D5/146 ,  F01D9/041 ,  F04D29/544 ,  F05D2230/20 ,  F05D2230/30 ,  F05D2240/30

摘要： A blade of a compressor or of an axial-flow turbomachine. The blade comprises a joining airfoil, or main airfoil, extended by branches, or auxiliary branch airfoils. The branches are adjacent and extend the joining airfoil radially. The branches form a row over the circumference and comprise faces facing one another. The branches comprise joining edges connected to the joining airfoil and are coincident or joined so as to form a circumferential material continuation between the adjacent branches. The leading edges and the trailing edges of the branches are a continuation of the leading edges and the trailing edges of the joining airfoil. The branch airfoils offer more anchoring points for a blade. The overlap of the branch airfoils strengthens the edges of the joining airfoil, which can thus be formed thinner. The blade comprises a fixing platform connected to the branch airfoils.

公开(公告)号：US20160024932A1

公开(公告)日：2016-01-28

申请号：US14803818

申请日：2015-07-20

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14

CPC分类号： F01D5/146 ,  F04D29/544 ,  F05D2240/30

摘要： The invention relates to a blade of an axial turbomachine comprising an airfoil which extends radially and a first set of branches or divisions, which radially extend a radial end of the airfoil, and a second set of branches which radially extend the other of the radial ends of the airfoil and which are offset over the circumference of the turbomachine. The branches extend axially along the entire length of the airfoil. The sets have different numbers of branches. The branches further occupy the channel of the turbomachine and further counteract debris in the event of intake.

摘要翻译： 本发明涉及一种轴向涡轮机的叶片，其包括径向延伸的翼型件和径向延伸翼型件的径向端的第一组分支或分段，以及径向延伸径向端部中的另一个的第二组分支 并且其在涡轮机的圆周上偏移。 分支沿翼型的整个长度轴向延伸。 这些集合有不同的分支数量。 分支进一步占据涡轮机的通道，并进一步抵消进食时的碎屑。

公开(公告)号：US09863253B2

公开(公告)日：2018-01-09

申请号：US14803818

申请日：2015-07-20

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14

CPC分类号： F01D5/146 ,  F04D29/544 ,  F05D2240/30

摘要： The invention relates to a blade of an axial turbomachine comprising an airfoil which extends radially and a first set of branches or divisions, which radially extend a radial end of the airfoil, and a second set of branches which radially extend the other of the radial ends of the airfoil and which are offset over the circumference of the turbomachine. The branches extend axially along the entire length of the airfoil. The sets have different numbers of branches. The branches further occupy the channel of the turbomachine and further counteract debris in the event of intake.

公开(公告)号：US20160024931A1

公开(公告)日：2016-01-28

申请号：US14803798

申请日：2015-07-20

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14

CPC分类号： F01D5/146 ,  F01D9/041 ,  F04D29/544 ,  F05D2230/20 ,  F05D2230/30 ,  F05D2240/30

摘要： The invention relates to a blade of a compressor or of an axial-flow turbomachine. The blade comprises a joining airfoil, or main airfoil, extended by branches, or auxiliary branch airfoils. The branches are adjacent and extend the joining airfoil radially. The branches form a row over the circumference and comprise faces facing one another. The branches comprise joining edges connected to the joining airfoil and are coincident or joined so as to form a circumferential material continuation between the adjacent branches. The leading edges and the trailing edges of the branches are a continuation of the leading edges and the trailing edges of the joining airfoil. The branch airfoils offer more anchoring points for a blade. The overlap of the branch airfoils strengthens the edges of the joining airfoil, which can thus be formed thinner. The blade comprises a fixing platform connected to the branch airfoils.

摘要翻译： 本发明涉及压缩机或轴流式涡轮机的叶片。 叶片包括由分支或辅助分支翼型件延伸的连接翼型件或主翼型件。 分支相邻并且径向延伸接合翼型件。 分支在圆周上形成一排，并且包括彼此面对的面。 分支包括连接到接合翼型件的接合边缘并且重合或接合，以便形成相邻分支之间的圆周材料延续。 分支的前缘和后缘是连接翼型的前缘和后缘的延续。 分支翼型件为刀片提供了更多的固定点。 分支翼型件的重叠增强了连接翼型件的边缘，从而可以形成较薄的连接翼型件。 叶片包括连接到分支翼型件的固定平台。

公开(公告)号：US10125612B2

公开(公告)日：2018-11-13

申请号：US14804522

申请日：2015-07-21

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14 ,  F04D29/54 ,  F01D5/22 ,  F01D9/04 ,  F01D25/24 ,  F01D5/02

摘要： The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder.

公开(公告)号：US20160024933A1

公开(公告)日：2016-01-28

申请号：US14804522

申请日：2015-07-21

申请人： Techspace Aero S.A.

发明人： Stephane Hiernaux

IPC分类号： F01D5/14 ,  F01D25/24 ,  F01D9/04 ,  F01D5/02 ,  F01D5/22

CPC分类号： F01D5/146 ,  F01D5/02 ,  F01D5/225 ,  F01D9/041 ,  F01D25/24 ,  F04D29/544 ,  F05D2220/30 ,  F05D2240/12 ,  F05D2240/20 ,  Y02T50/673

摘要： The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder.

摘要翻译： 本发明涉及一种轴向涡轮机叶片，其包括径向延伸的半圆形叶片。 每个叶片包括翼型和侧向分支或侧向腿。 每个分支具有连接到翼型的端部和与翼型相对的端部。 叶片包括连接到两个相邻叶片和/或相同叶片的两个相邻分支的至少两个相对端部的第一护罩段，以便经由翼型件的侧向分支将翼型件连接到护罩段。 叶片还包括与第一护罩区段同心的第二护罩区段。 这些段通过翼型件和分支件相互连接。 叶片形成刚性壳体，并且通过用钛基粉末的添加剂制造提供。