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1. 发明授权

US07399159B2 Detachable leading edge for airfoils 失效
标题翻译：可拆卸的翼型前缘
公开(公告)号：US07399159B2
公开(公告)日：2008-07-15
申请号：US10876081
申请日：2004-06-24
申请人： Paul Matheny , Brad Carter , Brian Potter
发明人： Paul Matheny , Brad Carter , Brian Potter
IPC分类号： F01D5/28
CPC分类号： F01D5/147 , F01D5/16 , F04D29/324 , F05D2240/303 , Y02T50/672 , Y02T50/673
摘要： The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.
摘要翻译：风扇/压缩机和涡轮转子的翼型被构造成包括可拆卸的前缘。前缘包括翼型部分和适于装配到形成在转子盘中的互补槽的附件。可拆卸的前缘在集成叶片转子（IBR或BLISK）设计中是有效的，因为前缘的损坏可以通过去除前缘并进行修复或更换，而不必干扰IBR的剩余部分来固定。

2. 发明申请

US20080199320A1 Detachable leading edge for airfoils 审中-公开
标题翻译：可拆卸的翼型前缘
公开(公告)号：US20080199320A1
公开(公告)日：2008-08-21
申请号：US12111683
申请日：2008-04-29
申请人： Paul Matheny , Brad Carter , Brian Potter
发明人： Paul Matheny , Brad Carter , Brian Potter
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/16 , F01D5/3007 , F04D29/324 , F05D2240/303 , Y02T50/672 , Y02T50/673
摘要： A replaceable leading edge insert for an: integrally bladed rotor disk in which the insert includes an enlarged base portion that can be inserted into a dovetail shaped slot formed in the rotor disk to secure the insert to the rotor disk against centrifugal loads during the operation of the blade. The blade on the rotor disk is formed without a leading edge and the leading edge insert includes an aft edge of similar shape to the fore edge n the blade such that the insert can be bonded or fastened to the blade along the entire length of the insert from the blade root to the tip. The rotor disk and the insert include a an annular groove formed on the front side in which a retaining ring is inserted to lock the inserts to the rotor disk. The inserts can be made of a different material from the rotor disk and can be formed with a sweep to form a more :aerodynamic and efficient blade.
摘要翻译：一种可替换的前缘插入件，用于：整体叶片的转子盘，其中插入件包括扩大的基部，其可以插入到形成在转子盘中的燕尾形槽中，以将插入件固定到转子盘，以防止在操作期间的离心负载刀片。转子盘上的刀片形成为没有前缘，并且前缘刀片包括与刀片前缘相似形状的后缘，使得刀片可以沿着刀片的整个长度被接合或紧固到刀片从叶根到尖端。转子盘和插入件包括形成在前侧上的环形槽，其中插入有保持环以将插入件锁定到转子盘。插入件可以由与转子盘不同的材料制成，并且可以用扫掠形成以形成更多：空气动力学和有效的叶片。

3. 发明申请

US20050118028A1 Detachable leading edge for airfoils 失效
标题翻译：可拆卸的翼型前缘
公开(公告)号：US20050118028A1
公开(公告)日：2005-06-02
申请号：US10876081
申请日：2004-06-24
申请人： Paul Matheny , Brad Carter , Brian Potter
发明人： Paul Matheny , Brad Carter , Brian Potter
IPC分类号： B63H1/20 , F01D5/14 , F01D5/16 , F04D29/32
CPC分类号： F01D5/147 , F01D5/16 , F04D29/324 , F05D2240/303 , Y02T50/672 , Y02T50/673
摘要： The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.
摘要翻译：风扇/压缩机和涡轮转子的翼型被构造成包括可拆卸的前缘。前缘包括翼型部分和适于装配到形成在转子盘中的互补槽的附件。可拆卸的前缘在集成叶片转子（IBR或BLISK）设计中是有效的，因为前缘的损坏可以通过去除前缘并进行修复或更换，而不必干扰IBR的剩余部分来固定。

4. 发明授权

US07300255B2 Laminated turbomachine airfoil with jacket and method of making the airfoil 有权
标题翻译：具有夹套的层压涡轮机翼型和制造翼型的方法
公开(公告)号：US07300255B2
公开(公告)日：2007-11-27
申请号：US11061313
申请日：2005-02-18
申请人： Brian Potter , Brad Carter , John Ryznic
发明人： Brian Potter , Brad Carter , John Ryznic
IPC分类号： F01D5/30 , F01D5/12
CPC分类号： F01D5/282 , F01D5/3007 , F01D5/3092
摘要： An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.
摘要翻译：具有翼型部分，颈部和根部的涡轮机叶片的改进，颈部从根部延伸，并且从颈部延伸的翼型部分和泪滴形状的根部包括护套，其附接到根部并且沿着颈部的一部分延伸。此外，形成涡轮机械刀片的方法包括提供材料层压体的步骤; 提供刀片插入件; 缠绕层压体以插入以形成具有根部部分的叶片，从根部延伸的颈部部分和从颈部部分延伸的翼型部分; 并且提供固定在根部周围的护套和从根部延伸的颈部的一部分，护套具有这样的形状，以防止由于作用在刀片上的离心力在临界点处层压体的分层。

5. 发明申请

US20050260078A1 Laminated turbomachine airfoil with jacket and method of making the airfoil 有权
标题翻译：具有夹套的层压涡轮机翼型和制造翼型的方法
公开(公告)号：US20050260078A1
公开(公告)日：2005-11-24
申请号：US11061313
申请日：2005-02-18
申请人： Brian Potter , Brad Carter , John Ryznic
发明人： Brian Potter , Brad Carter , John Ryznic
IPC分类号： F01D5/28 , F01D5/30 , B63H1/20
CPC分类号： F01D5/282 , F01D5/3007 , F01D5/3092
摘要： An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.
摘要翻译：具有翼型部分，颈部和根部的涡轮机叶片的改进，颈部从根部延伸，并且从颈部延伸的翼型部分和泪滴形状的根部包括护套，其附接到根部并且沿着颈部的一部分延伸。此外，形成涡轮机械刀片的方法包括提供材料层压体的步骤; 提供刀片插入件; 缠绕层压体以插入以形成具有根部部分的叶片，从根部延伸的颈部部分和从颈部部分延伸的翼型部分; 并且提供固定在根部周围的护套和从根部延伸的颈部的一部分，护套具有这样的形状，以防止由于作用在刀片上的离心力在临界点处层压体的分层。

6. 发明授权

US06857856B2 Tailored attachment mechanism for composite airfoils 有权
标题翻译：复合翼型的定制附件机构
公开(公告)号：US06857856B2
公开(公告)日：2005-02-22
申请号：US10646257
申请日：2003-08-22
申请人： Brian Potter , Brad Carter
发明人： Brian Potter , Brad Carter
IPC分类号： F01D5/28 , F01D5/30
CPC分类号： F01D5/3007 , F01D5/282 , F01D5/3092 , Y02T50/672 , Y02T50/673
摘要： A turbine engine composite blade attachment mechanism is provided, including a blade having an airfoil section, a neck section, and a root section. The root section includes a continuous loop integral with the blade and branching out from the neck section to completely surround a root insert. The blade includes a plurality of fibers which extend from the airfoil section through the neck and around the core. The root section and neck are enveloped by a jacket having a thickness which increases from the distal side surface of the loop to the neck portion, and has an inner contour substantially aligned with the proximal side surface contour of the loop and the core. The jacket and root are disposed inside a rotary disk cavity such that when tensile loading is applied, the neck width is maintained and compressive transverse loads may be applied to the fibers to prevent lamination thereof.
摘要翻译：提供了一种涡轮发动机复合叶片附接机构，包括具有翼型部分，颈部和根部的叶片。根部分包括与叶片一体的连续环，并从颈部分出，以完全包围根部插入物。叶片包括多个纤维，其从翼型部分延伸穿过颈部并围绕芯部延伸。根部和颈部由具有从环的远端侧表面增加到颈部的厚度的护套包围，并且具有基本上与环和芯的近侧表面轮廓对齐的内轮廓。护套和根部设置在旋转盘腔内，使得当施加拉伸载荷时，保持颈部宽度并且可以将压缩的横向载荷施加到纤维上以防止其层压。

7. 发明授权

US5499449A Method of manufacturing battery terminals 失效
标题翻译：制造电池端子的方法
公开(公告)号：US5499449A
公开(公告)日：1996-03-19
申请号：US203561
申请日：1994-03-01
申请人： Warren Carter , Brad Carter
发明人： Warren Carter , Brad Carter
IPC分类号： H01M2/30 , H01R11/28 , H01R43/16 , H01R43/24 , H01R43/04
CPC分类号： H01M2/305 , H01R43/16 , H01R43/24 , H01R11/281 , Y10T29/49208 , Y10T29/49218 , Y10T29/49934 , Y10T29/53996
摘要： A method of forming a battery terminal of the type having an electrically conductive screw encased within a conductive material casting such as lead. The preferred method uses a pair of die halves axially aligned with one another. A casting of a battery terminal having upper and lower terminal portions is provided, along with an electrically conductive post or screw. The casting and screw are placed between the die halves. The die halves are compressively forced against one another. A forging cone causes the casting to be forced into the thread spaces of the screw or against the surface of the post and changes the exterior angle of the casting.
摘要翻译：一种形成具有封装在诸如铅的导电材料铸造中的导电螺钉的类型的电池端子的方法。优选的方法使用一对彼此轴向对齐的半模。提供具有上端子部和下端子部的电池端子的铸造以及导电柱或螺钉。铸造和螺钉被放置在半模之间。模具一半被压迫地相互压制。锻造锥体使得铸件被迫进入螺钉的螺纹空间或者压在柱的表面上并改变铸件的外部角度。

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