公开(公告)号：US5933952A

公开(公告)日：1999-08-10

申请号：US914186

申请日：1997-08-19

申请人： Mathieu Philippe Albert Bichon ,  Bernard Armand Rene Costeplane ,  Alain Georges Henri Lorieux

发明人： Mathieu Philippe Albert Bichon ,  Bernard Armand Rene Costeplane ,  Alain Georges Henri Lorieux

IPC分类号： F01D5/18 ,  B21D11/14 ,  B21D53/78 ,  C22F1/00 ,  C22F1/18 ,  F01D5/28 ,  F02C7/00 ,  B23P15/00

CPC分类号： B21D53/78 ,  B21D11/14 ,  Y10T29/49336 ,  Y10T29/49339

摘要： A process for manufacturing a hollow turbomachine blade made from a titanium alloy of the TA6V type includes a hot twisting step in which an element of the blade is twisted progressively at a temperature above 700.degree. C. by a plurality of bars which are rotated about the twist axis and act on collars previously fixed to the element, the distribution and number of collars being determined according to the desired twist to be imparted and such as to obtain a linear twist development between each collar. Hot twisting apparatus for use in carrying out the operation is also described.

摘要翻译： 用于制造由TA6V型钛合金制成的中空涡轮机叶片的方法包括一个热扭转步骤，其中叶片的元件在高于700℃的温度下被多个杆旋转， 扭转轴线并且作用在先前固定到元件的套环上，根据要赋予的期望扭曲确定套环的分布和数量，并且获得每个套环之间的线性扭转发展。 还描述了用于执行操作的热扭转装置。

公开(公告)号：US5933951A

公开(公告)日：1999-08-10

申请号：US871637

申请日：1997-06-09

申请人： Jean-Pierre Serges Bergue ,  Mathieu Philippe Albert Bichon ,  Jean-Fran.cedilla.ois Georges Julien Lacuisse ,  Alain Georges Henri Lorieux

发明人： Jean-Pierre Serges Bergue ,  Mathieu Philippe Albert Bichon ,  Jean-Fran.cedilla.ois Georges Julien Lacuisse ,  Alain Georges Henri Lorieux

IPC分类号： B23P15/02 ,  B21D22/20 ,  B21D22/26 ,  B21J9/02 ,  B21K3/04 ,  B23P15/04 ,  B30B15/34 ,  C21D9/00 ,  C22F1/00 ,  C22F1/18 ,  F01D5/18 ,  F01D5/28 ,  F02C7/00 ,  B23P15/00

CPC分类号： B21J9/02 ,  B21D22/20 ,  B21D22/26 ,  B21K3/04 ,  B23P15/04 ,  Y10T29/49336 ,  Y10T29/49339

摘要： A process for manufacturing a hollow turbomachine blade made from a type TA6V titanium alloy includes a hot forming step in which an element of the blade is isothermally shaped in a press at a temperature between 700.degree. C. and 940.degree. C. under the action of at least two stamps and a holding-clamp which press the blade element on a shaping die, while ensuring a controlled deformation rate so as to obtain a lengthening of the fibres, that is to say the elongation of the different fibres of the element, with a controlled distribution on both sides of the central fibre. A multiple-action furnace-press designed for carrying out the process is also described.

摘要翻译： 用于制造由TA6V型钛合金制成的中空涡轮机叶片的方法包括热成形步骤，其中叶片的元件在压力下在700℃至940℃的温度下等温成形， 至少两个印章和夹持夹具，其将刀片元件压在成型模具上，同时确保受控的变形速率，以获得纤维的延长，也就是说元件的不同纤维的伸长率与 中央纤维两侧的受控分布。 还描述了设计用于执行该过程的多功能炉压机。

公开(公告)号：US06242715B1

公开(公告)日：2001-06-05

申请号：US09290996

申请日：1999-04-14

申请人： Mathieu Philippe Albert Bichon ,  Bernard Armand René Costeplane ,  Alain Georges Henri Lorieux

发明人： Mathieu Philippe Albert Bichon ,  Bernard Armand René Costeplane ,  Alain Georges Henri Lorieux

IPC分类号： A21B100

CPC分类号： B21D53/78 ,  B21D11/14 ,  Y10T29/49336 ,  Y10T29/49339

摘要： An apparatus for manufacturing a hollow turbomachine blade made from a titanium alloy of the TA6V type includes a hot twisting step in which an element of the blade is twisted progressively at a temperature above 700° C. by a plurality of bars which are rotated about the twist axis and act on collars previously fixed to the element, the distribution and number of collars being determined according to the desired twist to be imparted and such as to obtain a linear twist development between each collar.

摘要翻译： 一种用于制造由TA6V型钛合金制成的中空涡轮机叶片的装置包括热扭转步骤，其中叶片的元件在高于700℃的温度下被多个杆旋转， 扭转轴线并且作用在先前固定到元件的套环上，根据要赋予的期望扭曲确定套环的分布和数量，并且获得每个套环之间的线性扭转发展。

公开(公告)号：US06210630B1

公开(公告)日：2001-04-03

申请号：US09204155

申请日：1998-12-03

申请人： Jean-Pierre SErges Bergue ,  Mathieu Philippe Albert Bichon ,  Jean-François Georges Julien Lacuisse ,  Alain Georges Henri Lorieux

发明人： Jean-Pierre SErges Bergue ,  Mathieu Philippe Albert Bichon ,  Jean-François Georges Julien Lacuisse ,  Alain Georges Henri Lorieux

IPC分类号： C21D1100

CPC分类号： B21J9/02 ,  B21D22/20 ,  B21D22/26 ,  B21K3/04 ,  B23P15/04 ,  Y10T29/49336 ,  Y10T29/49339

摘要： A process for manufacturing a hollow turbomachine blade made from a type TA6V titanium alloy includes a hot forming step in which an element of the blade is isothermally shaped in a press at a temperature between 700° C. and 940° C. under the action of at least two stamps and a holding-clamp which press the blade element on a shaping die, while ensuring a controlled deformation rate so as to obtain a lengthening of the fibers, that is to say the elongation of the different fibers of the element, with a controlled distribution on both sides of the central fiber. A multiple-action furnace-press designed for carrying out the process is also described.

摘要翻译： 用于制造由TA6V型钛合金制成的中空涡轮机叶片的方法包括热成型步骤，其中叶片的元件在压力机中在700℃和940℃之间的温度下等温成形， 至少两个印章和夹持夹具，其将刀片元件压在成型模具上，同时确保受控的变形速率，以获得纤维的延长，也就是说元件的不同纤维的伸长率与 中央纤维两侧的受控分布。 还描述了设计用于执行该过程的多功能炉压机。

公开(公告)号：US5826332A

公开(公告)日：1998-10-27

申请号：US721352

申请日：1996-09-26

申请人： Mathieu Philippe Albert Bichon ,  Xavier Gerard Andre Coudray ,  Alex Pierre Deblois ,  Christophe Nicolas Marie Joseph Huon De Kermadec ,  Jean-Fran.cedilla.ois Georges Julien Lacuisse ,  Bruno Andre Rolland

发明人： Mathieu Philippe Albert Bichon ,  Xavier Gerard Andre Coudray ,  Alex Pierre Deblois ,  Christophe Nicolas Marie Joseph Huon De Kermadec ,  Jean-Fran.cedilla.ois Georges Julien Lacuisse ,  Bruno Andre Rolland

IPC分类号： F01D5/18 ,  B21D26/055 ,  B21K3/00 ,  B23K20/02 ,  B23K20/18 ,  B23P15/04 ,  B23P15/00

CPC分类号： B21D26/055 ,  B23K20/023 ,  B23K20/18 ,  B23P15/04 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49895

摘要： A method of manufacturing a hollow machine blade consisting of two skins ining an internal cavity and interconnected by stiffeners comprises: forging and machining the primary components of the blade, including forming a reserve of material in localized regions of the inner faces of the skins, trunnion forming elements at the ends of the components, and locating holes in the components; deposition of diffusion barriers involving application of a mask, cutting the mask to a predetermined pattern using a special-purpose tool, peeling away portions of the mask, deposition of a coating product, peeling away the remainder of the mask, prefiring treatment, cleaning and checking; assembly of the primary components followed by isostatic-pressure diffusion welding; and subjecting the assembly to inflation under gas pressure and superplastic forming in a mould in order to shape the skins and form the interconnecting stiffeners, including the steps of cold-debonding the primary components, causing flow of the material reserved in the overthickness around the blade cavity, and extraction of the blade from the mould by way of mechanical means placing the blade under constraint after the forming of the blade.

摘要翻译： 一种制造中空机器叶片的方法，其由限定内部空腔并由加强件互连的两个外皮组成，包括：对所述叶片的主要部件进行锻造和加工，包括在所述表面的内表面的局部区域中形成材料储备，耳轴 在部件的端部处形成元件，并且在部件中定位孔; 扩散障碍物的沉积，包括施加掩模，使用专用工具将掩模切割成预定图案，剥离面罩的部分，涂覆产品的沉积，剥离面罩的其余部分，预处理，清洁和 检查; 主要组件的组装，然后进行等静压扩散焊接; 并使组件在气体压力下膨胀并在模具中进行超塑性成型，以便使外壳成形并形成互连加强件，包括冷脱粘主要部件的步骤，使保留在刀片周围的厚度的材料流动 空腔，并且通过机械方式从模具中提取叶片，在叶片成形之后将叶片置于约束之下。