CN1572406A - 修理涡轮机部件的方法 - Google Patents

修理涡轮机部件的方法 Download PDF

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CN1572406A
CN1572406A CNA2004100492623A CN200410049262A CN1572406A CN 1572406 A CN1572406 A CN 1572406A CN A2004100492623 A CNA2004100492623 A CN A2004100492623A CN 200410049262 A CN200410049262 A CN 200410049262A CN 1572406 A CN1572406 A CN 1572406A
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turbine components
prefabrication
brazing material
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repairing
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帕扎扬纳·R·萨布拉马尼安
詹姆斯·A·鲁德
劳伦特·克里特格尼
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General Electric Co
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B23K1/0018—Brazing of turbine parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/008—Soldering within a furnace
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K11/00—Resistance welding; Severing by resistance heating
    • B23K11/002—Resistance welding; Severing by resistance heating specially adapted for particular articles or work
    • B23K11/0033—Welding locally a thin plate to a large piece
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F01D19/02—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine-casing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
    • Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
    • Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
    • Y10T29/49737—Metallurgically attaching preform

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

一种修理涡轮机部件的方法，包含：将钎焊材料的预制品罩面到涡轮机部件的表面，其中该表面包含损坏的部分；将钎焊材料预制品固定到表面上；加热涡轮机部件至在钎焊材料和涡轮机部件间形成有效的钎焊连接的温度。还公开了使用该方法修理的涡轮机部件。

Description

修理涡轮机部件的方法
技术领域
本发明涉及修理金属部件损坏部分的方法，并涉及修理过的金属部件。更具体而言，本发明涉及修理涡轮机部件的方法，并涉及修理过的涡轮机部件。
背景技术
功率产生装置的某些部件，例如涡轮机发动机，在装置的热气体通道中操作。在气体涡轮机发动机的涡轮机部分中，部件经常经受极端的温度和燃烧气体中存在的污染物，该污染物产生于来自热膨胀的周期荷载以及热气体流的磨损。作为在此种环境下操作的结果，涡轮机部件的暴露部分易发生退化。不同形式的退化可以包括但不限于例如在涡轮机部件的翼面和侧壁表面的氧化效应、裂缝产生和/或腐蚀和磨损。这些类型的退化可能导致涡轮机操作效率的丧失，以及由于与其分离和接触，有可能损坏位于退化部分的下游的部件。
在航空和发电工业中，修理昂贵的发动机部件比替换它们变得更经济。修理和恢复损坏的部分防止了灾难性的故障，提高了整个气体涡轮机的效率，并降低了操作成本。为提供充分的修理和恢复，该工艺应该能够将表面恢复到其原始的尺寸，同时提供结构上牢固的结构。而且，修理的周期应该最短。为了进行修理和恢复，典型地例如通过研磨、切割、机械加工、刨削、激光烧蚀等除去全部损坏的部分，使得相容的填料材料能够被堆焊或涂覆。然后堆焊填料材料以代替除去的部分。对于修理，填料材料与母材或基底金属的充分粘结是重要的考虑因素。理想的是，填料材料应该提供与母材金属相似的物理和机械性能。另外，由于填充材料和涡轮机部件将要面对苛刻的操作条件，希望填料材料表现出充分的耐腐蚀性和耐环境性能。也希望修理涡轮机部件的工艺不损坏超出修理的部分的周围和延伸区域。
目前的修理工艺典型地包括单个裂缝(如果可见)的焊接修理或将新材料样片焊接到除去损坏部分形成的凹陷处而代替损坏部分。通常，焊接修理裂缝或通过把它们熔化和熔合在一起而将新材料的样片连接到母材部件上。为了熔合金属，集中的热源直接施加到连接区域。该热源为高温，以便熔化母材金属和填料金属(金属被连接)。因为焊接热是强烈的，将其均匀地施加到很宽的区域是不切实际的。
不幸的是，由于不均匀集中加热和使用的高温，焊接工艺可以引起要修理的涡轮机部件显著的变形，这是因为由非均匀集中加热引起的穿过涡轮机部件的严重的热梯度；焊接工艺可以有害地锁定内应力(lock in internalstress)；焊接工艺可以导致次级开裂(secondary crack)；焊接工艺难以修理临近涡轮机部件冷却孔(cooling hole)(例如喷嘴)的损坏部分而不影响孔本身；而且焊接工艺可能需要相当多的时间和人工来实施修理。
除了这些可能由焊接引起的问题以外，作为良好的焊接实践的一部分，在特定的条件下可能需要预热步骤。预热步骤的目的是防止氢引起(hydrogen-induced)的开裂；该类型的开裂在焊接已经冷却后出现，并通常从焊接的焊边或其它焊接缺陷发展。这样的裂缝难以发现，并且特别当焊接位于高应力区域时，可能对涡轮机部件的使用寿命有害。来自预热的升高的温度增加了氢的扩散，并将氢烘焙到焊接外。预热也允许焊接的冷却速度更低，防止过度失去在焊接和基底金属热影响区域中的延展性。当然，预热也显著增加了涡轮机部件的修理开销和时间。
而且，在焊接工艺引起变形的这些情况下，涡轮机部件可能需要进行机械力和/或热处理，以消除变形引起的应力。涡轮机部件是严格规范的，而且在修理和恢复完成后，保持原始的形状和原始的规格是重要的。
由此，存在改进对损坏的涡轮机部件的修理和恢复工艺的需要。
发明内容
这里公开的是修理涡轮机部件的方法，包括：将钎焊材料(brazingmaterial)的预制品铺(overlay)到涡轮机部件的表面，其中该表面包括损坏的部分；将钎焊材料预制品固定到表面上；加热涡轮机部件至钎焊材料和涡轮机部件间形成有效的钎焊连接的温度。
在另一实施方式中，修理涡轮机部件的方法包括：从涡轮机部件的表面除去损坏的部分，以在表面形成凹陷的部分：将至少一种钎焊材料预制品固定到凹陷部分，其中，该预制品的侧向尺寸(lateral dimension)与凹陷部分的侧向尺寸大致相等；加热涡轮机部件至温度从而足以在钎焊材料和涡轮机部件间形成钎焊连接。
通过下面详细的描述和附图，对上述内容和其它特征加以说明。
附图说明
图1为修理涡轮机部件的工艺流程图；
图2图解了钎焊之后、研磨之后的基材和对比基材(witness)；
图3图解了喷嘴部件的钎焊修理；和
图4为测试不同钎焊连接抗拉强度的测试结构的平面图。
具体实施方式
本发明涉及修理涡轮机部件损坏部分的钎焊方法。该方法通常包括：将钎焊材料预制品铺到涡轮机部件的表面上，其中所述表面含有损坏的部分；将钎焊材料预制品点焊到所述表面上；以及加热涡轮机部件至在钎焊材料和涡轮机部件间形成有效钎焊连接的温度。该修理方法优选还包含机械加工经点焊的钎焊材料，使涡轮机部件恢复其原始的尺寸。
根据另一实施方式，钎焊方法包含从涡轮机部件移除损坏的部分，以在表面形成凹陷部分；将钎焊材料的至少一种预制品插入凹陷部分，其中该至少一种预制品的侧向尺寸与凹陷部分的侧向尺寸相等；点焊该至少一种预制品到该凹陷部分；以及加热涡轮机部件到在钎焊材料和涡轮机部件间足够形成钎焊连接的温度。可以加入同时机械加工的或单独制造的其它预制品，以提供完全填充凹陷的足够的厚度。优选稍微过量填充的预制品焊着在凹陷部分，然后对其进行机械加工，以便涡轮机部件恢复至其原始的尺寸。
现在参考图1，解释了实例性的工艺流程。该工艺流程包括涡轮机部件的冶金学分析，以便确定损坏部分。一旦确定了损坏部分，分割出(section)相容的钎焊材料预制品，以便具有足够的区域来完全覆盖损坏部分。取决于涡轮机的功能和操作条件，涡轮机部件可以由多种材料制成。可以制造气体涡轮机的典型材料是镍基超级合金。选择钎焊材料以与形成涡轮机部件的金属相容。
预制品是精确量的钎焊合金，确保每次使用所需要的精确的体积。因为恰当量的合金填充了损坏区域，这通常导致不合格部分的减少。预制品优选通过使钎焊粉末烧结成最符合每种应用的理想的形状而制造。本方法并不是要限于具体合金的预制品。合适的预制品可从Aerospace InternationalMaterials公司购买。
合适的制造预制品的钎焊材料是两种或多种纯金属制成的合金。钎焊材料的物理性质取决于冶金学组成。该组成决定钎焊材料是否与要修理的金属相容-能够润湿它们并完全流经连接区域和/或裂缝而不形成有害的冶金学化合物。熔体行为也基于冶金学组成。因为大部分钎焊材料是合金，它们通常不象纯金属那样熔化，即在一个温度下从固体转变为液体，例外的是那些在熔化时形成低共熔物(eutectics)的金属合金组成。在冶金学术语中，低共熔钎焊材料具有同样的熔点(固相线)和流动点(液相线)。
然后将钎焊材料预制品点焊到表面上，以允许进一步处理涡轮机部件以进行损坏部分的修理。电阻焊接等可以用于将钎焊材料预制品点焊到表面上。点焊量优选保持最小，以便防止涡轮机部件的变形损坏。
包含经点焊预制品的涡轮机部件然后进行钎焊工艺，以在损坏部分形成钎焊连接。在优选的实施方式中，钎焊过程在熔炉中进行。优选熔炉配备真空和气体容积(gas capabilities)。真空钎焊优选在大约10-3～10-6毫巴的压力和高于600°F的温度下进行，其进一步有助于防止金属部件的氧化。压力更优选在大约10-4毫巴。在这些条件下，通常不使用焊剂(flnx)。
在钎焊过程中温度优选在预定的时间期间逐步增加，接着逐步冷却以形成钎焊连接(braze joint)。应该指出，与焊接不同，钎焊不熔化涡轮机部件的基体或母材金属。所以钎焊温度始终低于基体金属的熔点。但是选择钎焊材料，即合金组成，以便在比涡轮机部件的基体金属低的温度下熔化。钎焊材料的熔点优选小于大约25℃，更优选小于大约50℃，甚至更优选小于100℃，最优选小于大约200℃。钎焊材料在熔化时，优选润湿基底金属的表面，填充损坏部分的任何空隙和裂缝，并流入预制品和涡轮机部件形成的接触面内。在进一步机械加工和冷却过程中，在涡轮机部件基底金属和钎焊材料间形成钎焊连接。
完成钎焊过程后，接着优选将表面机械加工为其适当的外形。优选表面机械加工为涡轮机部件规定的原始尺寸。虽然任选，当认为在表面上的阶梯高度差(step height difference)是涡轮机部件的缺陷时，可能需要机械加工。优选，机械加工过程不过度升高涡轮机部件的温度。
在可选择的实施方式中，损坏部分从涡轮机部件除去，以形成涡轮机部件的凹陷。优选只除去损坏部分。损坏部分的除去可以使用许多不同的方法实施，例如通过冶金学分析并确定涡轮机部件的损坏部分，可以使用研磨工艺从涡轮机部件除去损坏部分。然后钎焊材料的一种或多种预制品切成除去部分的侧向尺寸，并点焊进凹陷中。在点焊的预制品和涡轮机部件间形成的焊缝可以任选地用熔合剂(fluxing agent)覆盖。然后，开始钎焊循环，以在钎焊材料和涡轮机部件间形成钎焊连接，例如涡轮机部件进行如图2所示的加热处理。
任选地，涡轮机部件首先进行清洗步骤。取决于使用的钎焊方法类型，清洗步骤可以利用许多形式或结合，例如碱洗、酸洗、气体净化、脱脂剂、包含上述至少一种清洗方法的结合等。使用的清洗方法的选择将取决于待修理的部分和希望形成钎焊连接的钎焊方法类型。清洗步骤也可以包含轻喷钢砂(light grit blasting)处理，以选一步除去来自清洗步骤的污渍等。清洗步骤优选在升温下进行，促进与各种清洗方法相联系的化学反应增大。
还任选地，在钎焊步骤前使用保护气体，防止金属氧化物形成。例如，在高温真空熔炉钎焊中，优选使用惰性气体帮助降低在暴露的表面上金属氧化物的形成。该惰性气体不必具有还原效果，其防止金属氧化物的形成就足够了。但是，优选使用选自还原性的气体例如H2，代替惰性气体。如果使用还原气体，通过与惰性气体的还原组分的化学反应，除去存在的任何金属氧化物。反应的程度通常取决于金属氧化物的键焓(boad enthalpy)和惰性气体的干燥性。
提供下面的实施例来解释本发明的一些实施方式。它们并不是要以任何方式限制本发明。
实施例1
在该实施例中，使用预烧结的钎焊材料预制品和金属合金基材，模拟涡轮机部件的修理。将来自Howmet Castings的商品名FSX414的市购的1英寸×1英寸的空腔研磨成合金基材。预烧结的预制品是从AerospaceInternational Materials公司市购的商品名X40/D15的钎焊合金。作为预制品得到的钎焊合金具有以下尺寸：4英寸×英寸×60密耳(mil)。图1解释了钎焊预制品到FSX414基材的过程。在机械加工前，FSX414基材在2100°F下暴露于氢气中大约2小时。另外，将糊剂(paste)施加到点焊的预制品和基材之间形成的焊缝中。然后，逐步加热基材和预制品，从大约室温升至大约2100°F，并冷却至室温。得自Praxair公司的所涂钎料填料金属糊剂包含分布在粘合剂中的钎焊合金组合物，具有90∶10的金属对粘合剂比例。在或大约钎焊温度下，粘合剂蒸发，留下钎焊合金熔化并进一步密封钎焊的预制品和基材之间的焊缝。冷却时，检查修理的基材。图3描述的显微照片为钎焊步骤后的基材，和研磨使基材恢复到原始尺寸后的基材。在研磨后，基材在1800°F熔炉中暴露500循环。提供了对比基材(witness substrate)以比较。
实施例2
在该实施例中，一部分喷嘴除去了，并进行如实施例1的钎焊步骤。在钎焊后，该表面机械加工为其原始尺寸。图3是喷嘴部分的平面图，并确定了替换部分的位置。显微照片观察清楚地表明孔基本未受钎焊步骤的影响。
实施例3
在该实施例中，在室温和1500°F下测量了抗拉强度。测试结构尺寸如图4所示。FSX414合金作为基体金属。钎焊合金是X40/D15合金。按照实施例1中定义的钎焊步骤而形成钎焊连接。对具有和不具有钎焊连接(母体部件自身和按测试结构的尺寸配置的形状)的测试结构进行对比。在Instron型号1125的螺旋驱动架(screw driven frame)中，以0.02英寸/分钟测量抗拉强度。结果如表1所示，其清楚地表明与母体材料自身相比，钎焊材料的抗拉强度、屈服应力和延伸率大致相同或更高。结果解释了与母体结构相比，钎焊连接提供了结构相当或更好的结构稳固性。

Claims (10)

1.一种修理涡轮机部件的方法，包括：
将钎焊材料的预制品铺到涡轮机部件的表面，其中所述表面包含损坏的部分；
将钎焊材料预制品固定到所述表面上；
加热所述涡轮机部件至在钎焊材料和涡轮机部件间形成有效钎焊连接的温度。
2.根据权利要求1的方法，还包括机械加工涡轮机部件，以将涡轮机部件恢复到原始尺寸。
3.根据前述权利要求中任意一项的方法，还包括将预制品点焊到涡轮机部件之前，用惰性气体保护涡轮机部件。
4.根据前述权利要求中任意一项的方法，还包括将预制品点焊到涡轮机部件之前，用还原气体保护涡轮机部件。
5.根据权利要求4的方法，其中所述还原气体是氢气。
6.根据前述权利要求中任意一项的方法，其中所述加热涡轮机部件包括温度逐步加热至高于钎焊材料的熔化温度并低于涡轮机部件的熔化温度。
7.根据前述权利要求中任意一项的方法，其中所述钎焊材料包含两种或多种金属的合金或超级合金。
8.根据前述权利要求中任意一项的方法，其中所述加热涡轮机部件包括真空和惰性气氛。
9.根据前述权利要求中任意一项的方法，其中所述将预制品固定到表面上包含点焊。
10.使用前述权利要求中任意一项的方法的修理过的涡轮机部件。
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JP2005003003A (ja) 2005-01-06

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