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公开(公告)号：US07360991B2
公开(公告)日：2008-04-22
申请号：US10864155
申请日：2004-06-09
IPC分类号： F03B11/00
CPC分类号： F03B11/00 , C22C19/07 , C23C26/02 , F01D11/005 , F01D11/12 , F01D25/243 , Y02T50/671 , Y10T428/12861 , Y10T428/24917
摘要： Methods and apparatus of fabricating a gas turbine engine component are provided. The method includes selecting a surface of a component to apply a wear-resistant material, applying a formed wear pad fabricated from a wear-resistant alloy and a braze material, and vacuum brazing the component and applied wear pad wherein the wear-resistant alloy is bonded to the component surface using the braze material.
摘要翻译： 提供了制造燃气涡轮发动机部件的方法和装置。 该方法包括选择组件的表面以施加耐磨材料，施加由耐磨合金和钎焊材料制成的成形耐磨垫，以及真空钎焊所述组件和应用的耐磨垫，其中所述耐磨合金为 使用钎焊材料粘合到部件表面。
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公开(公告)号：USRE39479E1
公开(公告)日：2007-01-23
申请号：US10358927
申请日：2003-02-05
IPC分类号： F01D9/04
CPC分类号： F01D5/189 , F01D9/042 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.
摘要翻译： 涡轮喷嘴包括在相对端部连接到外带和内带的多个叶片。 内带具有分段的前挂钩以减少热不匹配。 并且，在另外的实施例中，叶片包括具有优先冷却的冲击挡板。
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公开(公告)号：US06183192B2
公开(公告)日：2001-02-06
申请号：US09274144
申请日：1999-03-22
申请人： Judd D. Tressler , Glenn H. Nichols
发明人： Judd D. Tressler , Glenn H. Nichols
IPC分类号： F01D904
CPC分类号： F01D5/189 , F01D9/042 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.
摘要翻译： 涡轮喷嘴包括在相对端部连接到外带和内带的多个叶片。 内带具有分段的前挂钩以减少热不匹配。 并且，在另外的实施例中，叶片包括具有优先冷却的冲击挡板。
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公开(公告)号：US20090060724A1
公开(公告)日：2009-03-05
申请号：US12041361
申请日：2008-03-03
CPC分类号： F03B11/00 , C22C19/07 , C23C26/02 , F01D11/005 , F01D11/12 , F01D25/243 , Y02T50/671 , Y10T428/12861 , Y10T428/24917
摘要： Methods and apparatus of fabricating a gas turbine engine component are provided. The method includes selecting a surface of a component to apply a wear-resistant material, applying a formed wear pad fabricated from a wear-resistant alloy and a braze material, and vacuum brazing the component and applied wear pad wherein the wear-resistant alloy is bonded to the component surface using the braze material.
摘要翻译： 提供了制造燃气涡轮发动机部件的方法和装置。 该方法包括选择组件的表面以施加耐磨材料，施加由耐磨合金和钎焊材料制成的成形耐磨垫，以及真空钎焊所述组件和应用的耐磨垫，其中所述耐磨合金为 使用钎焊材料粘合到部件表面。
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公开(公告)号：US07222422B2
公开(公告)日：2007-05-29
申请号：US10708205
申请日：2004-02-16
申请人： Bhupendra Kumar Gupta , Edward John Emilianowicz , Thomas J. Kelly , Glenn H. Nichols , Marek M. Steplewski
发明人： Bhupendra Kumar Gupta , Edward John Emilianowicz , Thomas J. Kelly , Glenn H. Nichols , Marek M. Steplewski
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23K1/0008 , Y10T29/301 , Y10T29/302 , Y10T29/49318 , Y10T29/49721 , Y10T29/49723 , Y10T29/49726 , Y10T29/49728 , Y10T29/49732 , Y10T29/49734 , Y10T29/49737 , Y10T29/49742 , Y10T29/49746 , Y10T428/12861
摘要： A process for refurbishing a worn surface of a shroud support component of a turbomachine, as well as a shroud support component refurbished with the process. The process generally entails removing a surface region of the worn surface so as to define a repair surface on the component. A braze tape formed from a slurry to comprise a braze material and a wear-resistant alloy is then applied to the repair surface, followed by a heat treatment to cause the braze tape to diffusion bond to the repair surface so as to define a built-up surface. The built-up surface is then machined to define a wear-resistant coating on the component.
摘要翻译： 用于翻新涡轮机的护罩支撑部件的磨损表面的过程以及用该过程翻新的护罩支撑部件。 该方法通常需要去除磨损表面的表面区域，以便在部件上限定修复表面。 然后将由钎焊材料和耐磨合金制成的浆料形成的钎焊带施加到修复表面上，然后进行热处理，以使钎焊带扩散到修复表面上， 上表面。 然后，加工表面被加工以在部件上限定耐磨涂层。
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公开(公告)号：USRE39320E1
公开(公告)日：2006-10-03
申请号：US10262695
申请日：2002-10-02
CPC分类号： F01D5/288 , C23C28/3215 , C23C28/3455 , Y02T50/67 , Y02T50/671
摘要： An airfoil having extended life due to reduction in stresses. The stresses are reduced by extending the thermal barrier coating below the radius between the outer band perimeter and the inner flow path surfaces and tapering the coating thickness. This additional tapered thermal barrier coating reduces the temperature gradient across a region already having high mechanical stresses resulting from geometric considerations thereby lowering thermally-induced stresses so that low cycle fatigue life is improved.
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公开(公告)号：US6126400A
公开(公告)日：2000-10-03
申请号：US243355
申请日：1999-02-01
申请人： Glenn H. Nichols , Judd D. Tressler
发明人： Glenn H. Nichols , Judd D. Tressler
CPC分类号： F01D5/288 , C23C28/3215 , C23C28/3455 , Y02T50/67 , Y02T50/671
摘要： An airfoil having extended life due to reduction in stresses. The stresses are reduced by extending the thermal barrier coating below the radius between the outer band perimeter and the inner flow path surfaces and tapering the coating thickness. This additional tapered thermal barrier coating reduces the temperature gradient across a region already having high mechanical stresses resulting from geometric considerations thereby lowering thermally-induced stresses so that low cycle fatigue life is improved.
摘要翻译： 翼型由于应力减小而延长使用寿命。 通过将隔热涂层延伸到外带周边和内部流路表面之间的半径之下并使涂层厚度变细来减小应力。 这种附加的锥形热障涂层降低了由于几何考虑而导致的具有高机械应力的区域的温度梯度，从而降低了热应力，从而提高了低循环疲劳寿命。
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