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1. 发明授权

US06814818B2 Heat treatment of titanium-alloy articles to limit alpha case formation 失效
标题翻译：钛合金制品的热处理以限制α形成
公开(公告)号：US06814818B2
公开(公告)日：2004-11-09
申请号：US10286241
申请日：2002-10-30
申请人： Andrew Philip Woodfield , Thomas Froats Broderick , Reed Roeder Corderman
发明人： Andrew Philip Woodfield , Thomas Froats Broderick , Reed Roeder Corderman
IPC分类号： C22C1400
CPC分类号： C22F1/183
摘要： A method for heat treating titanium-alloy articles in a vacuum furnace includes a step of first determining, for a first set of titanium articles in a first vacuum furnace and for a first set of heat treatment conditions, a minimum surface area of the first set of titanium articles associated with an acceptable alpha case formation for the first set of titanium articles. There is a second determining, for a second set of titanium articles in a second vacuum furnace and for a second set of heat treatment conditions, of a minimum surface area of a second set of titanium articles associated with an acceptable alpha case formation for the second set of titanium articles, responsive to the value of the minimum surface area of the first set of titanium articles. There follows a heat treating of a third set of titanium articles in the second vacuum furnace and for the second set of heat treatment conditions, where the surface area of the third set of titanium articles is not less than the value of the minimum surface area of the second set of titanium articles.

2. 发明授权

US07449075B2 Method for producing a beta-processed alpha-beta titanium-alloy article 有权
标题翻译：用于生产β加工的α-β钛合金制品的方法
公开(公告)号：US07449075B2
公开(公告)日：2008-11-11
申请号：US10878105
申请日：2004-06-28
申请人： Andrew Philip Woodfield , Wesley Douglas Pridemore , Bernard Harold Lawless , Nancy Ann Sullivan , Peter Wayte , Michael James Weimer , Thomas Froats Broderick
发明人： Andrew Philip Woodfield , Wesley Douglas Pridemore , Bernard Harold Lawless , Nancy Ann Sullivan , Peter Wayte , Michael James Weimer , Thomas Froats Broderick
IPC分类号： C22F1/18
CPC分类号： C22F1/183 , C22C14/00
摘要： A titanium-alloy article is produced by providing a workpiece of an alpha-beta titanium alloy having a beta-transus temperature, and thereafter mechanically working the workpiece at a mechanical-working temperature above the beta-transus temperature. The mechanically worked workpiece is solution heat treated at a solution-heat-treatment temperature of from about 175° F. below the beta-transus temperature to about 25° F. below the beta-transus temperature, quenched, overage heat treated at an overage-heat-treatment temperature of from about 400° F. below the beta-transus temperature to about 275° F. below the beta-transus temperature, and cooled from the overage-heat-treatment temperature.
摘要翻译：通过提供具有β转子温度的α-β钛合金的工件，然后在高于β转子温度的机械加工温度下机械加工工件来制造钛合金制品。机械加工的工件在溶解热处理温度下，在β-转变温度以下约175°F至低于β-转变温度的约25°F，在过高温度下进行淬火，过热处理 - 在β-转变温度以下约低于低于β-转变温度约400°F的热处理温度，低于β-转变温度下约275°F，并从过热热处理温度冷却。

3. 发明授权

US07384244B2 Fatigue-resistant components and method therefor 无效
标题翻译：耐疲劳组件及其方法
公开(公告)号：US07384244B2
公开(公告)日：2008-06-10
申请号：US11014611
申请日：2004-12-16
申请人： Thomas Froats Broderick , Andrew P. Woodfield
发明人： Thomas Froats Broderick , Andrew P. Woodfield
IPC分类号： F01D5/14
CPC分类号： F01D5/005 , B23P9/02 , F01D5/286 , F05D2230/80 , F05D2230/90 , Y10T29/4932
摘要： A metallic component, which may be an airfoil, includes at least one treated patch, wherein the entire thickness of the component within the treated patch is in a state of residual compressive stress. A surface-treated area overlaps at least a boundary between the treated patch and the remainder of the component. The surface of the component within the surface-treated area is in a state of residual compressive stress, so as to resist crack initiation at the boundary between the treated patch and the remainder of the component. A method is also provided for making such a component.
摘要翻译：可以是翼型的金属部件包括至少一个经处理的贴片，其中处理的贴片内的部件的整个厚度处于残余压应力的状态。表面处理区域至少与经处理的贴片和部件的其余部分之间的边界重叠。表面处理区域内的部件的表面处于残余压应力的状态，以抵抗经处理的贴片与部件的其余部分之间的边界处的裂纹开始。还提供了制造这种组分的方法。

4. 发明授权

US07249412B2 Method for repairing a damaged blade of a Blisk 有权
标题翻译：修复Blisk损坏刀片的方法
公开(公告)号：US07249412B2
公开(公告)日：2007-07-31
申请号：US10853050
申请日：2004-05-25
申请人： Peter Wayte , Thomas Froats Broderick
发明人： Peter Wayte , Thomas Froats Broderick
IPC分类号： B23P6/00 , B23K9/04
CPC分类号： B23P6/007 , F01D5/34 , Y10T29/49318 , Y10T29/49732 , Y10T29/49737 , Y10T29/49742 , Y10T29/49746
摘要： A BLISK having a damaged blade, with a repair region that has a thickness less than a specified thickness as a result of damage during manufacture or prior service, is repaired by depositing repair metal onto the repair region to increase its thickness to greater than its specified thickness dimension. Only the repair region is stress relieved by heating the repair region to a stress-relieving temperature of from about 1150° F. to about 1250° F. for a time of at least about 1 hour. The intentional manipulation of microstructure in only the thinner airfoil sections allows multiple repairs, which are not possible in the thicker sections of the BLISK. An alpha-case thickness of repair metal, preferably of at least about 0.0002 inches of repair metal, is removed from a surface of the repair region.
摘要翻译：具有损坏的叶片的BLISK，其具有由于在制造或事先服务期间损坏而具有小于指定厚度的修复区域，通过将修复金属沉积到修复区域上来将其厚度增加到大于其指定值厚度尺寸。只有修复区域通过将修复区域加热至约1150°F至约1250°F的应力消除温度至少约1小时来减轻应力。只有更薄的翼型部分有意操纵微结构才允许多次维修，这在BLISK的较厚部分是不可能的。修复金属的α壳厚度，优选为至少约0.0002英寸的修复金属，从修复区域的表面去除。

5. 发明授权

US07097720B2 Lower fluence boundary laser shock peening 有权
标题翻译：低能量密度边界激光冲击硬化
公开(公告)号：US07097720B2
公开(公告)日：2006-08-29
申请号：US10426816
申请日：2003-04-30
申请人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
发明人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
IPC分类号： C21D1/04 , C21D1/09 , C21D1/10
CPC分类号： F01D5/286 , C21D10/005
摘要： A method for laser shock peening an article including laser shock peening a first area with at least one high fluence laser beam and laser shock peening a border area between the first area and a non-laser shock peened area of the article with at least one first low fluence laser beam. The border area may be laser shock peened with a second low fluence laser beam or more low fluence laser beams wherein the second low fluence laser beam and others have a lower fluence than the first low fluence laser beam. The border area may be laser shock peened with progressively lower fluence laser beams starting with the one first fluence laser beam wherein the progressively lower fluence laser beams are in order of greatest fluence to least fluence in a direction outwardly from the first area through the border area to the non-laser shock peened area.
摘要翻译：一种用于激光冲击硬化处理物品的方法，所述方法包括用至少一个高注量激光束激光冲击第一区域的激光冲击，以及用所述第一区域和所述第一区域和所述第一区域之间的至少一个第一区域激光冲击所述第一区域和所述制品的非激光冲击硬化区域之间的边界区域低能量激光束。边界区域可以是用第二低注量激光束或更低的能量密度激光束进行激光冲击喷丸，其中第二低注量激光束和其它激光束具有比第一低注量激光束更低的能量密度。边界区域可以是激光冲击喷丸，其中以一个第一注量激光束开始逐渐降低的注量激光束，其中逐渐更低的注量激光束按照最小注量的顺序，在从第一区域通过边界区域向外的方向上的最小注量到非激光冲击硬化区域。

6. 发明授权

US07198684B2 Method for manufacturing articles using a semi-continuous flow of workpieces through metal working and annealing apparatus 失效
标题翻译：使用半连续流动的工件通过金属加工和退火设备制造制品的方法
公开(公告)号：US07198684B2
公开(公告)日：2007-04-03
申请号：US10388671
申请日：2003-03-14
申请人： Thomas Froats Broderick , Jeffrey Lynn Myers , Francois Laurent Giguere , Peter Brian Haley , Paul Raymond Phaneuf , William Francis Bergeron , Thomas Caudwell Straub
发明人： Thomas Froats Broderick , Jeffrey Lynn Myers , Francois Laurent Giguere , Peter Brian Haley , Paul Raymond Phaneuf , William Francis Bergeron , Thomas Caudwell Straub
IPC分类号： C21D8/00
CPC分类号： C21D9/0068 , B23P15/02 , C21D1/26 , C21D7/10 , F01D5/286
摘要： A plurality of gas turbine components or other articles are manufactured from a plurality of metallic-alloy workpieces using a manufacturing apparatus having a metalworking apparatus, and an annealing apparatus wherein the individual workpieces are annealed by single-workpiece annealing and not by large-batch annealing. A workpiece flow of the plurality of workpieces is established sequentially through the metalworking apparatus and the annealing apparatus.
摘要翻译：使用具有金属加工装置的制造装置的多个金属合金工件制造多个燃气轮机部件或其他制品，以及退火装置，其中各个工件通过单工件退火退火而不是通过大批量退火。通过金属加工装置和退火装置依次建立多个工件的工件流。

7. 发明授权

US06468367B1 Superalloy weld composition and repaired turbine engine component 有权
标题翻译：超合金焊接组成和修理的涡轮发动机部件
公开(公告)号：US06468367B1
公开(公告)日：2002-10-22
申请号：US09472917
申请日：1999-12-27
申请人： Charles Gitahi Mukira , Melvin Robert Jackson , Jon Conrad Schaeffer , William Scott Walston , Thomas Froats Broderick
发明人： Charles Gitahi Mukira , Melvin Robert Jackson , Jon Conrad Schaeffer , William Scott Walston , Thomas Froats Broderick
IPC分类号： C22C1905
CPC分类号： B23P6/007 , B23K35/304 , F01D5/005 , F01D5/28 , F05D2230/232 , Y02T50/67
摘要： A superalloy weld composition, includes: about 2 to about 5 wt % Co; about 5 to about 15 wt % Cr; about 7 to about 10 wt % Al; about 4 to about 6 wt % Ta; about 0.5 to about 1.5 wt % Si; about 0.1 to about 0.5 wt % Hf; up to about 0.05 wt % C; up to about 0.05 wt % B; about 1.0 to about 2.0 Re; about 3 to about 4.5 wt % W; and balance Ni.
摘要翻译：超合金焊接组合物包括：约2至约5重量％的Co;约5至约15重量％的Cr;约7至约10重量％的Al;约4至约6重量％的Ta;约0.5至约1.5重量％ Si;约0.1至约0.5重量％的Hf;至多约0.05重量％的C;至多约0.05重量％的B;约1.0至约2.0重量％;约3至约4.5重量％的W; 平衡Ni。

8. 发明授权

US07331755B2 Method for coating gas turbine engine components 有权
标题翻译：燃气轮机发动机部件的涂装方法
公开(公告)号：US07331755B2
公开(公告)日：2008-02-19
申请号：US10853609
申请日：2004-05-25
申请人： Thomas Froats Broderick , Ronald Lance Galley , Clifford Earl Shamblen , David Edwin Budinger , Reed Roy Oliver , Roger Owen Barbe
发明人： Thomas Froats Broderick , Ronald Lance Galley , Clifford Earl Shamblen , David Edwin Budinger , Reed Roy Oliver , Roger Owen Barbe
IPC分类号： F01D9/00 , B23P15/04
CPC分类号： F01D5/288 , F01D9/044 , Y10T29/49323
摘要： A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and executing a brazing operation such that the airfoil vane is permanently coupled to the platform portion and such that the wear coating material is bonded across a predefined area of the platform.
摘要翻译：一种用于组装用于燃气涡轮发动机的叶片扇区的方法，包括翼型叶片和平台的叶片扇区包括将耐磨涂层材料沉积到平台的选定区域上，将平台定位成邻近翼型叶片，并执行钎焊操作使得翼型叶片永久地联接到平台部分，并且使得磨损涂层材料跨越平台的预定区域结合。

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