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公开(公告)号：EP1571445A3
公开(公告)日：2006-05-10
申请号：EP05250167.3
申请日：2005-01-14
IPC分类号： G01N27/90
CPC分类号： G01N27/90
摘要： A system (100) for fabricating and testing an article having a thermal-spray coating thereon. The system enables the use of a method which includes providing (102) a substrate article having a surface, thermally spraying (104) a coating material onto the surface of the substrate article, wherein a surface of contact between the coating material and the substrate article is a bondline, and nondestructively testing (106) the coated article. Nondestructively testing includes generating (108) an eddy current in the coated article, measuring (110) the eddy current in the coated article, and evaluating (112) a near-bondline region of the coated article located adjacent to the bondline using the measured eddy current.
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公开(公告)号：EP1527845A3
公开(公告)日：2005-12-21
申请号：EP04256644.8
申请日：2004-10-27
CPC分类号： B23P6/007 , B23K2201/001 , F01D5/005 , F04D29/023 , F04D29/321 , F05D2230/10 , F05D2230/232 , F05D2230/80 , F05D2300/174 , Y02T50/673 , Y10T29/49318 , Y10T29/49732 , Y10T29/49746
摘要： A method facilitates repairing a gas turbine engine compressor blade airfoil (20). The method comprises removing titanium alloy material (61) from along leading and trailing edges (34 and 36) of the airfoil, and along a radially outer tip (40) of the airfoil to form respective leading edge, trailing edge, and tip cut-backs (62, 64, and 66) which each define cut-back depths (D 1 , D 3 , D 2 ), and depositing titanium weld material onto the leading edge, trailing edge, and tip cut-backs. The method also comprises removing at least some of the titanium weld bead material to obtain pre-desired finished dimensions for the leading and trailing edges, and radially outer tip.
摘要翻译： 一种方法便于维修燃气涡轮发动机压缩机叶片翼型件（20）。 该方法包括从翼型的前缘和后缘（34和36）沿着翼型件的径向外顶端（40）去除钛合金材料（61）以形成相应的前缘，后缘和顶端切口， （62,64和66），其各自限定切回深度（D1，D3，D2），并且将钛焊接材料沉积到前缘，后缘和尖端切口上。 该方法还包括去除至少一些钛焊缝焊缝材料，以获得前缘和后缘以及径向外尖端的预期的成品尺寸。
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公开(公告)号：EP1571445A2
公开(公告)日：2005-09-07
申请号：EP05250167.3
申请日：2005-01-14
IPC分类号： G01N27/90
CPC分类号： G01N27/90
摘要： A system (100) for fabricating and testing an article having a thermal-spray coating thereon. The system enables the use of a method which includes providing (102) a substrate article having a surface, thermally spraying (104) a coating material onto the surface of the substrate article, wherein a surface of contact between the coating material and the substrate article is a bondline, and nondestructively testing (106) the coated article. Nondestructively testing includes generating (108) an eddy current in the coated article, measuring (110) the eddy current in the coated article, and evaluating (112) a near-bondline region of the coated article located adjacent to the bondline using the measured eddy current.
摘要翻译： 一种用于制造和其上具有热喷涂制品的测试系统（100）。 该系统允许使用，其包括提供一种方法（102），其具有基材制品的表面上，热喷涂（104）的涂层材料到基片制品的表面，worin涂层材料之间的接触表面和所述基片制品的 是键线，和非破坏性测试（106）的涂布制品。 非破坏性测试包括：产生（108）的经涂覆的制品在对涡流，测量（110）的经涂覆的制品中的涡流，并评估（112）邻近所述粘结线涂覆制品使用所测量的涡流的近联接区域 电流。
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5.发明公开Method for repairing gas turbine rotor blades 审中-公开Verfahren zur Reparatur von Turbinen-Rotorschaufeln
公开(公告)号：EP1533071A2
公开(公告)日：2005-05-25
申请号：EP04256954.1
申请日：2004-11-10
CPC分类号： B23P6/005 , B23K2201/001 , F01D5/005 , Y02T50/673 , Y10T29/49318 , Y10T29/49726 , Y10T29/49732
摘要： A method for replacing a portion of a gas turbine engine rotor blade, the rotor blade having a contour defined by a blade first sidewall (70) and a blade second sidewall (70) includes cutting through the rotor blade such that a cut line (110) extends from a leading edge (74) of the blade to a trailing edge (76) of the blade, and between the first sidewall and the second sidewall, removing the portion of the rotor blade that is radially outward of the cut line, and coupling a replacement blade portion (120) to remaining blade portion (98) such that the newly formed rotor blade (150) is formed with a predetermined aerodynamic contour.
摘要翻译： 一种用于替换燃气涡轮发动机转子叶片的一部分的方法，具有由叶片第一侧壁（70）和叶片第二侧壁（70）限定的轮廓的转子叶片包括切割通过转子叶片使得切割线（110 ）从叶片的前缘（74）延伸到叶片的后缘（76），并且在第一侧壁和第二侧壁之间，移除在切割线的径向外侧的转子叶片的部分，以及 将替换刀片部分（120）联接到剩余刀片部分（98），使得新形成的转子叶片（150）形成有预定的空气动力学轮廓。
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6.发明公开Method for repairing gas turbine compressor rotor blades 审中-公开Methode zur Reparatur von Verdichterschaufeln
公开(公告)号：EP1527845A2
公开(公告)日：2005-05-04
申请号：EP04256644.8
申请日：2004-10-27
IPC分类号： B23P6/00
CPC分类号： B23P6/007 , B23K2201/001 , F01D5/005 , F04D29/023 , F04D29/321 , F05D2230/10 , F05D2230/232 , F05D2230/80 , F05D2300/174 , Y02T50/673 , Y10T29/49318 , Y10T29/49732 , Y10T29/49746
摘要： A method facilitates repairing a gas turbine engine compressor blade airfoil (20). The method comprises removing titanium alloy material (61) from along leading and trailing edges (34 and 36) of the airfoil, and along a radially outer tip (40) of the airfoil to form respective leading edge, trailing edge, and tip cut-backs (62, 64, and 66) which each define cut-back depths (D 1 , D 3 , D 2 ), and depositing titanium weld material onto the leading edge, trailing edge, and tip cut-backs. The method also comprises removing at least some of the titanium weld bead material to obtain pre-desired finished dimensions for the leading and trailing edges, and radially outer tip.
摘要翻译： 一种方法有助于修理燃气涡轮发动机压缩机叶片翼型件（20）。 该方法包括从翼型件的前缘和后缘（34和36）以及沿翼型的径向外端（40）移除钛合金材料（61），以形成相应的前缘，后缘和末端切口 背部（62,64和66），其各自限定切割深度（D1，D3，D2），并且将钛焊接材料沉积到前缘，后缘和尖端切口上。 该方法还包括移除至少一些钛焊缝材料以获得用于前缘和后缘以及径向外端的预期最终尺寸。
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7.发明公开Method for improving the wear resistance of a support region between a turbine outer case and a supported turbine vane 审中-公开用于改善涡轮机壳体和叶片之间的承载连接的耐磨性
公开(公告)号：EP1491720A1
公开(公告)日：2004-12-29
申请号：EP04253660.7
申请日：2004-06-18
CPC分类号： B23K10/02 , B23K10/027 , B23K2201/001 , C23C26/02 , C23C30/00 , F01D5/005 , F01D9/04 , F01D9/042 , F01D25/246 , F05D2230/232 , F05D2230/80 , F05D2230/90 , Y10T29/4932
摘要： A wear-resistant assembly of a turbine outer case (22) and a turbine vane (34) is fabricated by providing a turbine outer case (22), and a turbine vane (34) that, when assembled, is supported on the turbine outer case (22) in a support region such that a vane-support area (52) of the turbine vane (34) contacts a case-support area (54) of the turbine outer case (22). A wear-resistant material is welded to a weld area of at least one of the vane-support area (52) and the case-support area (54). In some circumstances, as where the turbine outer case (22) and the turbine vane (34) have previously been in service, material may be machined from the support region before the welding.
摘要翻译： 该方法包括提供一个涡轮外壳（22）和涡轮机叶片（34）。 当组装时所述叶片被支撑在在支撑区中的涡轮机外壳。 叶片触点的叶片支撑区域在所述支撑区域的情况下的情况下，支撑区域。 甲耐磨材料：诸如钴基合金焊接到区域中的一个的焊接区域。 从焊接区材料在焊接前被去除。
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公开(公告)号：EP1533071A3
公开(公告)日：2005-12-21
申请号：EP04256954.1
申请日：2004-11-10
CPC分类号： B23P6/005 , B23K2201/001 , F01D5/005 , Y02T50/673 , Y10T29/49318 , Y10T29/49726 , Y10T29/49732
摘要： A method for replacing a portion of a gas turbine engine rotor blade, the rotor blade having a contour defined by a blade first sidewall (70) and a blade second sidewall (70) includes cutting through the rotor blade such that a cut line (110) extends from a leading edge (74) of the blade to a trailing edge (76) of the blade, and between the first sidewall and the second sidewall, removing the portion of the rotor blade that is radially outward of the cut line, and coupling a replacement blade portion (120) to remaining blade portion (98) such that the newly formed rotor blade (150) is formed with a predetermined aerodynamic contour.
摘要翻译： 一种用于更换燃气涡轮发动机转子叶片的一部分的方法，所述转子叶片具有由叶片第一侧壁（70）和叶片第二侧壁（70）限定的轮廓，包括切穿转子叶片，使得切割线（110 ）从所述叶片的前缘（74）延伸到所述叶片的后缘（76），并且在所述第一侧壁和所述第二侧壁之间，从所述切割线的径向向外移除所述转子叶片的所述部分，以及 将替换叶片部分（120）联接到剩余叶片部分（98），使得新形成的转子叶片（150）形成有预定的空气动力学轮廓。
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9.发明公开Method for preparing and ultrasonically testing a thermal-spray coated article 审中-公开用于制备和通过热喷涂涂覆基板的超声波探伤方法
公开(公告)号：EP1471163A1
公开(公告)日：2004-10-27
申请号：EP04252349.8
申请日：2004-04-21
CPC分类号： G01N29/11 , C23C4/12 , G01N2291/0231 , G01N2291/044 , G01N2291/101 , G01N2291/2693
摘要： An article having a thermal-spray coating (46) thereon is prepared by thermally spraying a coating material (41) onto a surface (42) of a substrate article (44). The coated article (40) is nondestructively tested by directing a transmitted ultrasonic signal (68) into the coated article (40), receiving a received ultrasonic signal (72) from the coated article (40), and evaluating a near-bondline region (50) of the coated article (40) located adjacent to the surface (42) of the article using the received ultrasonic signal (72).
摘要翻译： 生产的涂覆制品（40）包括通过将反式mitted超声波信号进入涂层制品，接收到该信号热喷涂的涂层材料（41）喷射到基板制品（44）和非破坏性检测的表面（42） 从物品和评估邻近使用接收到的超声波信号的结合线（48）的物品的接近联接区域。
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