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公开(公告)号：US06568079B2
公开(公告)日：2003-05-27
申请号：US09878848
申请日：2001-06-11
申请人： Gilbert Farmer , David Bruce Patterson , Steven Allen Stiverson , James Michael Caldwell , Edward John Emilianowicz , Jeffrey Michael Martini
发明人： Gilbert Farmer , David Bruce Patterson , Steven Allen Stiverson , James Michael Caldwell , Edward John Emilianowicz , Jeffrey Michael Martini
IPC分类号： B23P1500
CPC分类号： B23P6/005 , B23P2700/13 , F23R3/002 , F23R3/08 , F23R2900/00005 , F23R2900/00016 , Y02T50/67 , Y02T50/675 , Y10T29/49318 , Y10T29/49346 , Y10T29/49721 , Y10T29/4973 , Y10T29/49737
摘要： A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor.
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公开(公告)号：US06345441B1
公开(公告)日：2002-02-12
申请号：US09618379
申请日：2000-07-18
申请人： Gilbert Farmer , James Michael Caldwell , Steven Allen Stiverson , David Bruce Patterson , Edward John Emilianowicz
发明人： Gilbert Farmer , James Michael Caldwell , Steven Allen Stiverson , David Bruce Patterson , Edward John Emilianowicz
IPC分类号： B23P1500
CPC分类号： B23P6/005 , B23P2700/13 , F23R3/002 , F23R2900/00019 , Y10T29/49318 , Y10T29/4932 , Y10T29/49737
摘要： A method of repairing an annular transpiration cooled liner for a combustion chamber of a gas turbine engine. An annular portion of the liner including a damaged region is removed from between an upstream section and a downstream section of the liner. Sheet metal is formed into an annular replacement section having at least one axial seam extending between an upstream end and a downstream end of the replacement section. The replacement section is sized and shaped similarly to the removed annular portion of the liner. The upstream end of the formed annular section is joined to the upstream section of the liner and the downstream end of the formed annular section is joined to the downstream section of the liner.
摘要翻译： 一种修复用于燃气涡轮发动机的燃烧室的环形蒸发冷却衬套的方法。 包括受损区域的衬垫的环形部分从衬套的上游部分和下游部分之间移除。 钣金形成为具有在更换部分的上游端和下游端之间延伸的至少一个轴向接缝的环形更换部分。 替换部分的尺寸和形状类似于衬垫的移除的环形部分。 形成的环形部分的上游端连接到衬套的上游部分，并且所形成的环形部分的下游端连接到衬套的下游部分。
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公开(公告)号：US06530971B1
公开(公告)日：2003-03-11
申请号：US09771898
申请日：2001-01-29
申请人： Joel Heywood Cohen , David Edwin Budinger , James Michael Caldwell , Michael Glenn Gordon , Edward John Emilianowicz
发明人： Joel Heywood Cohen , David Edwin Budinger , James Michael Caldwell , Michael Glenn Gordon , Edward John Emilianowicz
IPC分类号： B22F100
CPC分类号： B23P6/007 , B23K35/0244 , B23K35/025 , B23K35/304 , F23R3/002 , F23R2900/00005
摘要： A braze material and method for repairing an article, such as a gas turbine engine combustor liner formed from a nickel-base or cobalt-base superalloy. The braze material is composed of a nickel-base braze alloy that is preferably in powder form and may be dispersed in a suitable vehicle to yield a slurry, putty or solid tape. The braze alloy is formulated to be capable of withstanding the high temperature operating environment of a combustor liner, and to have a melting temperature below the grain growth or incipient melting temperature of the superalloy to be repaired. A preferred braze alloy is formed by combining at least two nickel-base powders. A suitable composition for the braze alloy is, in weight percent, about 10 to about 19 chromium, about 3 to about 10.5 cobalt, about 1.75 to about 4.9 titanium, about 0.75 to about 3.4 aluminum, about 1.25 to about 4.1 tungsten, about 1.25 to about 4.1 molybdenum, about 0.025 to about 0.225 carbon, about 0.005 to about 0.15 zirconium, about 0.50 to about 2.6 boron, up to 1.5 iron, with the balance being nickel and incidental impurities.
摘要翻译： 一种用于修复物品的钎焊材料和方法，例如由镍基或钴基超级合金形成的燃气涡轮发动机燃烧器衬套。 钎焊材料由镍基钎焊合金组成，其优选为粉末形式，并且可以分散在合适的载体中以产生浆料，油灰或固体胶带。 钎焊合金被配制成能够承受燃烧器衬套的高温操作环境，并且具有低于要修复的超级合金的晶粒生长或初始熔化温度的熔融温度。 通过组合至少两种镍基粉末形成优选的钎焊合金。 用于钎焊合金的合适组合物的重量百分比为约10至约19铬，约3至约10.5钴，约1.75至约4.9钛，约0.75至约3.4铝，约1.25至约4.1钨，约1.25 至约4.1钼，约0.025至约0.225个碳，约0.005至约0.15个锆，约0.50至约2.6个硼，至多1.5个铁，余量为镍和附带杂质。
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公开(公告)号：US06449952B1
公开(公告)日：2002-09-17
申请号：US09836037
申请日：2001-04-17
IPC分类号： F02C720
CPC分类号： F23R3/60 , F01D25/243 , F23R3/04 , F23R3/50 , F23R2900/00017 , Y02T50/675
摘要： A cowl for directing flow of air entering an annular combustor assembly of a gas turbine engine and which is removable from the combustor without disassembling the combustor. The cowl is annular in shape and has a plurality of circumferentially spaced fastener holes for receiving fasteners which commonly connect and align the cowl, an annular dome, and a liner. At least one notch is in the cowl, each notch being sized sufficiently larger than a corresponding fastener to permit the cowl to be moved to or removed from an operative position while the corresponding fastener remains in position for connecting the dome and liner to one another.
摘要翻译： 用于引导空气流进入燃气涡轮发动机的环形燃烧器组件的整流罩，并且其可以从燃烧器移除而不拆卸燃烧器。 整流罩是环形的，并且具有多个周向间隔开的紧固件孔，用于接收共同连接和对准整流罩，环形圆顶和衬套的紧固件。 在整流罩中至少有一个凹口，每个凹口的尺寸足够大于相应的紧固件，以允许整流罩从操作位置移动或移除，同时相应的紧固件保持在适当位置，以将圆顶和衬套彼此连接。
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公开(公告)号：US20100031664A1
公开(公告)日：2010-02-11
申请号：US11644612
申请日：2006-12-22
CPC分类号： F23R3/002 , B23P6/005 , B23P2700/13 , F23R3/06 , F23R2900/00019 , F23R2900/03041 , Y02T50/67 , Y02T50/675 , Y10T29/49348
摘要： A replacement panel for repairing a liner for a gas turbine engine combustor, the combustor having a combustion zone formed by inner and outer liners, the replacement panel comprising a sheet of material suitable for use in a combustor liner, at least one opening in the sheet of material, a thermal barrier material applied to the sheet of material adjacent the at least one opening; and a peripheral edge free of thermal barrier material.
摘要翻译： 一种用于修理用于燃气涡轮发动机燃烧器的衬套的更换面板，所述燃烧器具有由内衬和外衬层形成的燃烧区，所述替换面板包括适于用于燃烧器衬套的材料片，所述片中的至少一个开口 材料，施加到邻近所述至少一个开口的材料片材上的热障材料; 和没有隔热材料的周边边缘。
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公开(公告)号：US08312627B2
公开(公告)日：2012-11-20
申请号：US11644614
申请日：2006-12-22
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23P2700/13 , F23R2900/00019 , Y10T29/49318 , Y10T29/49718 , Y10T29/49721 , Y10T29/4973 , Y10T29/49885
摘要： A method for repairing a combustor liner for a gas turbine engine combustor, the combustor having a combustion zone formed by inner and outer liners, the method comprising the steps of removing a portion of a combustor liner to form a deficit in the liner; providing a replacement panel having at least one opening and a thermal barrier material applied to the replacement panel adjacent to the opening, and installing the replacement panel in the deficit.
摘要翻译： 一种用于修理用于燃气涡轮发动机燃烧器的燃烧器衬套的方法，所述燃烧器具有由内衬和外衬层形成的燃烧区，所述方法包括以下步骤：去除燃烧器衬套的一部分以在衬套中形成缺陷; 提供具有至少一个开口和隔热材料的替换面板，所述隔热材料施加到邻近开口的替换面板，并且将更换面板安装在缺口中。
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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：US07546684B2
公开(公告)日：2009-06-16
申请号：US10901262
申请日：2004-07-27
CPC分类号： F23R3/00 , B23P6/005 , B23P2700/13 , F23R3/60 , F23R2900/00019 , Y10T29/49318 , Y10T29/4932 , Y10T29/49346 , Y10T29/49721 , Y10T29/49728 , Y10T29/4973 , Y10T29/49746
摘要： A method for repairing a damaged portion of a combustor inner liner assembly. The method includes removing the combustor from a gas turbine engine. After inspecting the combustor to determine whether cracks exists in portions of the inner liner assembly, the method includes removing a cracked inner liner assembly from the combustor. Then the portion of the inner liner assembly, comprising a multi-hole panel region, an aft lip region, an aft seal flange region and an aft panel support leg are separated from the inner liner assembly. The multi-hole panel region and aft lip, where fatigue damage typically exists, along with the aft seal flange region, are discarded and a new aft lip region/aft seal flange region and multi-hole panel region are provided. The new parts are joined to the aft panel support leg and the inner liner assembly aft of forward bolt flange region after these parts are refurbished. The inner liner assembly is then reattached to the combustor and reassembled into the engine.
摘要翻译： 一种用于修理燃烧器内衬组件的损坏部分的方法。 该方法包括从燃气涡轮发动机移除燃烧器。 在检查燃烧器以确定在内衬组件的部分中是否存在裂纹的情况下，该方法包括从燃烧器去除裂纹的内衬组件。 然后，内衬组件的包括多孔面板区域，后唇区域，后密封凸缘区域和后面板支撑腿部的部分与内衬组件分离。 通常存在通常存在疲劳损伤的多孔面板区域和后缘以及后部密封凸缘区域，并且提供新的后缘区域/后部密封凸缘区域和多孔面板区域。 这些部件经过翻新后，新的部件连接到后板支撑腿和内衬组件后方的前螺栓法兰区域。 内衬组件然后重新连接到燃烧器并重新组装到发动机中。
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公开(公告)号：US20080172876A1
公开(公告)日：2008-07-24
申请号：US11644614
申请日：2006-12-22
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23P2700/13 , F23R2900/00019 , Y10T29/49318 , Y10T29/49718 , Y10T29/49721 , Y10T29/4973 , Y10T29/49885
摘要： A method for repairing a combustor liner for a gas turbine engine combustor, the combustor having a combustion zone formed by inner and outer liners, the method comprising the steps of removing a portion of a combustor liner to form a deficit in the liner; providing a replacement panel having at least one opening and a thermal barrier material applied to the replacement panel adjacent to the opening, and installing the replacement panel in the deficit.
摘要翻译： 一种用于修理用于燃气涡轮发动机燃烧器的燃烧器衬套的方法，所述燃烧器具有由内衬和外衬层形成的燃烧区，所述方法包括以下步骤：去除燃烧器衬套的一部分以在衬套中形成缺陷; 提供具有至少一个开口和隔热材料的替换面板，所述隔热材料施加到邻近开口的替换面板，并且将更换面板安装在缺口中。
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公开(公告)号：US06904676B2
公开(公告)日：2005-06-14
申请号：US10310571
申请日：2002-12-04
CPC分类号： B23P6/005 , B23P2700/13 , F23R3/002 , F23R3/60 , F23R2900/00019 , Y02T50/67 , Y10T29/49346
摘要： A method facilitates replacing a portion of a gas turbine engine combustor liner. The combustor includes a combustion zone formed by inner and outer liners. The inner and outer liners each include a series of panels, and at least one of the inner and the outer liner includes an aft support coupled to an aft end of liner. The method comprises cutting through at least one of the combustor inner and the outer liner upstream from the liner aft support, removing the combustor liner aft support from the combustor, and installing a replacement aft support within the combustor such that the liner aft support extends aft ward from the portion of the combustor liner that is upstream from the cut.
摘要翻译： 一种方法有助于更换燃气涡轮发动机燃烧器衬套的一部分。 燃烧器包括由内衬和外衬层形成的燃烧区。 内层和外衬层各自包括一系列面板，并且内衬套和外衬套中的至少一个包括联接到衬套的后端的后支撑件。 该方法包括切割穿过衬套后部支撑件上游的燃烧器内部和外部衬套中的至少一个，从燃烧器移除燃烧器衬套后部支撑件，以及在燃烧器内安装替换后部支撑件，使得衬里后部支撑件向后延伸 从切口上游的燃烧器衬套的部分出来。
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