CN105177392A - 燃气涡轮机部件和用于制造燃气涡轮机部件的方法 - Google Patents
燃气涡轮机部件和用于制造燃气涡轮机部件的方法 Download PDFInfo
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- CN105177392A CN105177392A CN201510295470.XA CN201510295470A CN105177392A CN 105177392 A CN105177392 A CN 105177392A CN 201510295470 A CN201510295470 A CN 201510295470A CN 105177392 A CN105177392 A CN 105177392A
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 26
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- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 12
- 229910045601 alloy Inorganic materials 0.000 claims description 12
- 239000000956 alloy Substances 0.000 claims description 12
- 229910052804 chromium Inorganic materials 0.000 claims description 12
- 239000011651 chromium Substances 0.000 claims description 12
- 230000008021 deposition Effects 0.000 claims description 12
- 229910052742 iron Inorganic materials 0.000 claims description 12
- 239000010941 cobalt Substances 0.000 claims description 11
- 229910017052 cobalt Inorganic materials 0.000 claims description 11
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 11
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 11
- 229910052721 tungsten Inorganic materials 0.000 claims description 11
- 239000010937 tungsten Substances 0.000 claims description 11
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 9
- 229910052748 manganese Inorganic materials 0.000 claims description 9
- 239000011572 manganese Substances 0.000 claims description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 8
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- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 7
- 229910052796 boron Inorganic materials 0.000 claims description 7
- 229910052746 lanthanum Inorganic materials 0.000 claims description 7
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims description 7
- 229910000679 solder Inorganic materials 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 claims description 6
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 4
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 abstract description 16
- 238000000151 deposition Methods 0.000 abstract description 11
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- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 3
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- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
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- 230000003647 oxidation Effects 0.000 description 1
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- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
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- 239000004575 stone Substances 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
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- 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
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- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
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- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
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Abstract
本发明提供了一种制造陶瓷基体复合材料燃气涡轮机部件的方法和一种陶瓷基体复合材料燃气涡轮机部件。所述方法包括改性陶瓷基体复合材料燃气涡轮机部件的表面,以制造表面粗糙度小于6微米的经改性的表面。所述改性选自由如下组成的技术的组:将未增强的基体层片施用至表面、在表面上气相沉积硅、珩磨表面、将钎料膏施用至表面,以及它们的组合。所述部件包括表面粗糙度小于6微米的经改性的表面。经改性的表面选自施用至陶瓷基体复合材料燃气涡轮机部件的表面的未增强的基体层片、气相沉积至表面上的硅、经珩磨的表面、施用至表面的钎料膏,以及它们的组合。
Description
技术领域
本发明涉及一种燃气涡轮机部件以及用于制造燃气涡轮机部件的方法。更具体地,本发明涉及一种陶瓷基体复合材料燃气涡轮机部件以及用于制造陶瓷基体复合材料燃气涡轮机部件的方法。
背景技术
某些陶瓷基体复合材料(CMC)包括具有由涂布纤维增强的陶瓷基体的组合物。所述组合物提供牢固、轻质和耐热性质,以及在多种不同的系统中的可能的应用。然而,例如在涡轮机部件的密封槽区域中的暴露纤维难以机械加工,由此难以获得密封所需的高精整表面。
当涡轮机部件在燃气涡轮机的热气体路径内时,密封槽区域可暴露于高操作温度。在高温下的在该区域中的暴露纤维是不希望的,并可导致降低的部件寿命。
相比于现有技术显示一个或多个改进的方法和制品是本领域希望的。
发明内容
本申请通过提供一种制造陶瓷基体复合材料燃气涡轮机部件的方法及陶瓷基体复合材料燃气涡轮机部件,以解决本领域中所存在的以上技术问题。
在一个实施例中,一种制造陶瓷基体复合材料燃气涡轮机部件的方法包括改性陶瓷基体复合材料燃气涡轮机部件的表面,以制造表面粗糙度小于6微米的经改性的表面。所述改性选自由如下技术组成的组:将未增强的基体层片施用至表面、在表面上气相沉积硅、珩磨表面、将钎料膏施用至表面,以及它们的组合。
其中,所述表面沿着所述陶瓷基体复合材料燃气涡轮机部件的热气体路径位于密封槽中;所述表面的改性减少了所述密封槽中的泄漏;该实施例的方法还包括在所述密封槽中设置密封件;所述经改性的表面抑制所述陶瓷基体复合材料燃气涡轮机部件的基体中的游离硅与所述密封件中的金属之间的反应;所述密封件包括陶瓷基体复合材料;所述密封件包括镍基合金;所述镍基合金具有如下以重量计的组成:约0.015%的硼,约0.05%至约0.15%的碳,约20%至约24%的铬,约3%的铁,约0.02%至约0.12%的镧,约1.25%的锰,约20%至约24%的镍,约0.2%至约0.5%的硅,约13%至约15%的钨,且余量为钴;或者所述镍基合金具有如下以重量计的组成:约19%至约21%之间的铬、约15%的钨、约9%至约11%之间的镍、约3%的铁、约1%至约2%之间的锰、约0.40%的硅、约0.030%的硫,且余量为钴;所述表面选自陶瓷基体复合材料燃气涡轮机部件中的减震器销的减震器腔体表面、陶瓷基体复合材料燃气涡轮机旋转机翼的楔形榫头附接面、陶瓷基体复合材料燃气涡轮机非旋转机翼的楔形榫头附接面;所述改性包括珩磨表面,且珩磨表面还包括使用研磨材料机械加工表面;所述改性包括珩磨表面,且珩磨表面还包括使用非研磨材料机械加工表面;使用非研磨材料机械加工表面还包括将材料沉积至表面上的裂缝中;所述裂缝由选自未增强的基体层片和纤维增强的层片的层片形成;该实施例的方法还包括将材料沉积至表面上的裂缝减小表面的摩擦系数;所述表面粗糙度小于3微米;或者所述表面粗糙度为1微米至2微米之间;所述方法为制造过程;或者所述方法为修复过程;所述经改性的表面基本上不含纤维;所述经改性的表面包括具有如下以重量计的组成的沉积材料:约0.015%的硼,约0.05%至约0.15%的碳,约20%至约24%的铬,约3%的铁,约0.02%至约0.12%的镧,约1.25%的锰,约20%至约24%的镍,约0.2%至约0.5%的硅,约13%至约15%的钨,且余量为钴;进一步地,本申请还涉及通过所述的方法制得的陶瓷基体复合材料燃气涡轮机部件,其具有经改性的表面。
在另一实施例中,一种制造陶瓷基体复合材料燃气涡轮机部件的方法包括沿着陶瓷基体复合材料燃气涡轮机部件的热气体路径改性位于密封槽中的表面,以制造表面粗糙度小于3微米的经改性的表面,以及将密封件设置于密封槽中。经改性的表面基本上不含纤维。所述改性选自由如下技术组成的组:将未增强的基体层片施用至表面、在表面上气相沉积硅、珩磨表面、将钎料膏施用至表面,以及它们的组合。
在另一实施例中,一种陶瓷基体复合材料燃气涡轮机部件包括表面粗糙度小于6微米的经改性的表面。经改性的表面选自施用至陶瓷基体复合材料燃气涡轮机部件的表面的未增强的基体层片、气相沉积至表面上的硅、经珩磨的表面、施用至表面的钎料膏,以及它们的组合。
在另一实施例中,一种珩磨陶瓷基体复合材料表面的方法包括提供非研磨材料、与陶瓷基体复合材料表面相邻设置所述非研磨材料,以及通过进行至少约300个珩磨循环而将所述非研磨材料的至少一部分沉积于陶瓷基体复合材料表面上。每个珩磨循环包括相对于彼此移动非研磨材料或陶瓷基体复合材料表面中的至少一者。
其中,所述方法还包括进行约500至约10,000个之间的珩磨循环;所述非研磨材料的沉积减小陶瓷基体复合材料表面的摩擦系数;所述非研磨材料的沉积减小陶瓷基体复合材料表面的粗糙度;所述非研磨材料的沉积增加陶瓷基体复合材料表面的适形性;所述的方法还包括提供约450°F至1200°F之间的珩磨温度;在减少数量的珩磨循环的情况下,增加所述珩磨温度减小陶瓷基体复合材料表面的摩擦系数;所述的方法还包括提供约40,000psi至约80,000psi之间的珩磨接触压力;在减少数量的珩磨循环的情况下,增加所述珩磨接触压力减小陶瓷基体复合材料表面的摩擦系数;所述珩磨循环中的每一个包括约0.0005英寸至0.040英寸之间的珩磨位移;所述非研磨材料包括镍基合金。
根据与以举例的方式说明本发明的原理的附图结合的如下更详细的描述,本发明的其他特征和优点将显而易见。
附图说明
图1为根据本公开的一个实施例的用于制造燃气涡轮机部件的方法的示意图。
图2为根据本公开的一个实施例的经基体层片改性的燃气涡轮机部件表面的示意图。
图3为根据本公开的一个实施例的经化学气相沉积改性的燃气涡轮机部件表面的示意图。
图4为根据本公开的一个实施例的经珩磨的燃气涡轮机部件表面的示意图。
只要有可能,将在整个附图中使用相同的附图标记以表示相同的部分。
具体实施方式
提供了一种燃气涡轮机部件和用于制造燃气涡轮机部件的方法。例如相比于未能包括本文公开的特征中的一个或多个的概念,本公开的实施例增加陶瓷基体复合材料部件的机械加工性、增加陶瓷基体复合材料部件的间隔寿命(intervallife)、提供修复陶瓷基体复合材料部件而不增加暴露纤维的数量的方法、减少暴露于热气体路径环境的陶瓷基体复合材料纤维、减少陶瓷基体复合材料纤维的氧化、提供降低的表面粗糙度、减少的泄漏、减少的密封磨损、减少的纤维涂层损坏,或它们的组合。
参照图1,在一个实施例中,方法100包括用于制造陶瓷基体复合材料(CMC)部件,如CMC燃气涡轮机部件110的制造方法。在另一实施例中,方法100包括改性CMC燃气涡轮机部件110的表面111,以制造具有降低的表面粗糙度的经改性的表面113。在一个实施例中,方法100包括用于制造经改性的表面113,并增加CMC部件的间隔寿命的修复方法。改性CMC燃气涡轮机部件110的表面111包括任何合适的技术,例如但不限于将未增强的基体层片201(图2)施用至表面111、将材料301(图3)沉积于表面111上、珩磨(图4)表面111、将钎料膏施用至表面111,或它们的组合。根据方法100,术语“珩磨”涵盖表面111的珩磨、磨光和/或抛光。用于降低的表面粗糙度的合适的值包括但不限于如下表面粗糙度:小于6微米,小于3微米,约3至约6微米之间,小于2微米,约1微米至约3微米之间,约1微米至约2微米之间,或它们的任意组合、子组合、范围或子范围。
表面111包括可具有暴露的CMC纤维的任意表面,例如但不限于热气体路径部件表面、涡轮机壳体表面、密封表面、密封槽表面、斜线面密封槽表面、CMC燃气涡轮机部件110中的减震器销的减震器腔体表面、CMC燃气涡轮机110的楔形榫头附接面上的表面、可具有暴露的CMC纤维的任何其他部件或特征的表面,或它们的组合。例如,在一个实施例中,表面111包括沿着CMC燃气涡轮机部件110的热气体路径的密封槽表面。在另一实施例中,表面111包括位于密封槽中的密封件。在又一实施例中,表面111包括CMC燃气涡轮机旋转机翼或非旋转机翼的楔形榫头附接面。
用于表面111的合适的材料包括但不限于CMC材料、镍基合金,或它们的组合。在一个例子中,镍基合金具有如下以重量计的组成:约0.015%的硼、约0.05%至约0.15%的碳、约20%至约24%的铬、约3%的铁、约0.02%至约0.12%的镧(lanthium)、约1.25%的锰、约20%至约24%的镍、约0.2%至约0.5%的硅、约13%至约15%的钨,且余量为钴。在另一例子中,镍基合金具有如下以重量计的组成:约19%至约21%之间的铬、约15%的钨、约9%至约11%之间的镍、约3%的铁、约1%至约2%之间的锰、约0.40%的硅、约0.030%的硫,且余量为钴。
经改性的表面113包括具有降低的表面粗糙度的任何合适的表面。在一个实施例中,经改性的表面113的组成类似于或基本上类似于表面111。在另一实施例中,经改性的表面113包括具有沉积于其上的材料301的表面111。用于沉积于表面111上的一种合适的材料包括硅。用于沉积于表面111上的其他合适的材料包括但不限于具有约0.015%的硼、约0.05%至约0.15%的碳、约20%至约24%的铬、约3%的铁、约0.02%至约0.12%的镧、约1.25%的锰、约20%至约24%的镍、约0.2%至约0.5%的硅、约13%至约15%的钨,且余量为钴的以重量计的组成的材料;具有约50%至约55%之间的镍、约17%至约21%的铬、约2.80%至约3.30%的钼、约0.35%的锰、约0.35%的硅、约0.08%的碳,且余量为铁的以重量计的组成的材料;或它们的组合。在另一实施例中,将材料301沉积至表面111中的纤维层片的裂缝中,以制造经改性的表面113并降低摩擦系数、表面粗糙度、密封件的磨损,或它们的组合。
参照图2,在一个实施例中,施用未增强的基体层片201包括在CMC燃气涡轮机部件110的密封表面处铺设任何合适数量的仅基体层片。合适数量的仅基体层片包括例如至少3个层片,至少4个层片,至少5个层片,3至5个之间的层片,或它们的任意组合、子组合、范围或子范围。如本文所用,术语“仅基体”指未增强的,例如不含或基本上不含纤维。在另一实施例中,施用至CMC燃气涡轮机部件110的未增强的基体层片201与密封表面一体化。例如,在另一实施例中,将未增强的基体层片201交织至CMC燃气涡轮机部件110中形成了CMC燃气涡轮机部件110的一体部分。
参照图3,在一个实施例中,将材料301沉积于表面111上包括材料301的气相沉积,例如化学气相沉积(CVD)或物理气相沉积(PVD)。在另一实施例中,使用大气压CVD、低压CVD、超高真空CVD、等离子体辅助的或等离子体增强的CVD、混合物理-化学CVD、扩散或它们的组合在密封槽腔体中将硅沉积至表面111上。
参照图4,在一个实施例中,表面111的珩磨包括使用研磨材料和/或非研磨材料机械加工表面111,以形成经珩磨的表面401。研磨材料的例子包括但不限于包括刚玉、碳化硅、立方氮化硼、金刚石和它们的组合的晶粒的磨石。在一个实施例中,使用研磨材料珩磨表面111包括使用振动金刚石板来减小密封槽中的表面111的粗糙度,并形成经珩磨的表面401。非研磨材料的例子包括但不限于具有约0.015%的硼、约0.05%至约0.15%的碳、约20%至约24%的铬、约3%的铁、约0.02%至约0.12%的镧、约1.25%的锰、约20%至约24%的镍、约0.2%至约0.5%的硅、约13%至约15%的钨,且余量为钴的以重量计的组成的镍基合金;具有约19%至约21%之间的铬、约15%的钨、约9%至约11%之间的镍、约3%的铁、约1%至约2%之间的锰、约0.40%的硅、约0.030%的硫,且余量为钴的以重量计的组成的镍基合金;其他镍基超合金,以及它们的组合。使用非研磨材料珩磨表面111会将材料沉积至未增强的基体层片201和/或经纤维增强的层片的裂缝中,以减小表面111的粗糙度和/或增加表面111的适形性。在另一实施例中,将非研磨材料沉积至表面111上(例如旋转或非旋转机翼的楔形榫头附接面)减小了表面111的摩擦系数。
在一个实施例中,表面111的珩磨包括至少约400°F,约400°至约1300°F之间,约450°至约1200°F之间,约550°至约1200°F之间,约550°至约850°F之间,约850°至约1200°F之间,约1000°至约1200°F之间,或它们的任意组合、子组合、范围或子范围的珩磨温度。增加珩磨温度进一步减小通过表面111的珩磨而形成的经改性的表面113的摩擦系数。在另一实施例中,表面111的珩磨包括至少约30,000psi,约30,000psi至约100,000psi之间,约40,000至约80,000psi之间,约60,000至约80,000psi之间,约70,000至约80,000psi之间,或它们的任意组合、子组合、范围或子范围的珩磨接触压力。珩磨接触压力为表面111上的法向力除以接触面积。在另一实施例中,表面111的珩磨包括约0.0001至约0.050英寸之间,约0.0001至约0.040英寸之间,约0.0005至约0.040英寸,约0.001至约0.040英寸,或它们的任意组合、子组合、范围或子范围的珩磨位移。珩磨位移为研磨材料或非研磨材料与表面111之间的相对运动。
至少基于珩磨温度、珩磨压力和/或珩磨位移选择珩磨循环的数量。在一个实例中,在减少数量的珩磨循环的情况下,增加珩磨温度和/或珩磨接触压力提供类似的或基本上类似的表面111的摩擦系数。在另一实例中,珩磨循环的数量随着珩磨位移的变化而变化。珩磨循环的合适数量包括至少约300个循环,至少约500个循环,约100至约10,000个之间的循环,约300至约10,000个之间的循环,约500至约10,000个之间的循环,或它们的任意组合、子组合、范围或子范围。
CMC燃气涡轮机部件110的表面111的改性减少或消除了暴露的CMC纤维。在一个实施例中,改性通过未增强的基体层片201的施用、硅301的气相沉积、钎料膏的施用,或用于提供单独的暴露表面的任何其他合适的技术而在表面111上提供单独的暴露表面。在另一实施例中,通过任何合适的精制技术(例如但不限于表面111的珩磨、放电机械加(EDM)或它们的组合)来精制单独的暴露表面。在一个可选择的实施例中,表面111的珩磨去除CMC纤维的暴露部分,以减少或消除表面111上的暴露的CMC纤维而不提供单独的暴露表面。
通过减少或消除暴露的CMC纤维,方法100形成不含或基本上不含CMC纤维和/或暴露的CMC纤维的经改性的表面113。在一个实施例中,经改性的表面113降低CMC燃气涡轮机部件110的表面粗糙度、减少CMC纤维暴露于高温氧环境以减少纤维涂层损坏,或它们的组合。在另一实施例中,经改性的表面113的降低的表面粗糙度有利于机械加工以获得高表面精整。在另一实施例中,降低的表面粗糙度和/或高表面精整减少部件的泄漏率、减少机械加工切割、增加密封件耐磨性,或它们的组合。另外,在一个实施例中,表面111的改性降低了硬的CMC界面与柔软的密封件之间的磨损联接、抑制CMC燃气涡轮机部件110的基体中的游离硅与密封件中的金属之间的反应,或它们的组合。
尽管参照一个或多个实施例描述了本发明,但本领域技术人员应了解,在不偏离本发明的范围下,可进行各种改变,且等同物可替代本发明的元件。另外,在不偏离本发明的基本范围下,可进行许多修改以使特定的情况或材料适合本发明的教导。因此,本发明不旨在局限于作为进行本发明的预期最佳模式而公开的特定实施例,而本发明将包括落入所附权利要求书的范围内的所有实施例。
Claims (15)
1.一种制造陶瓷基体复合材料燃气涡轮机部件(110)的方法(100),所述方法包括:
改性陶瓷基体复合材料燃气涡轮机部件(110)的表面(111),以制造表面粗糙度小于6微米的经改性的表面(113);
其中所述改性选自由如下组成的技术的组:将未增强的基体层片(201)施用至所述表面(111)、在所述表面(111)上气相沉积硅、珩磨所述表面(111)、将钎料膏施用至所述表面(111),以及它们的组合。
2.根据权利要求1所述的方法,其特征在于,所述表面(111)沿着所述陶瓷基体复合材料燃气涡轮机部件(110)的热气体路径位于密封槽中,所述方法还包括在所述密封槽中设置密封件。
3.根据权利要求2所述的方法,其特征在于,所述密封件包括陶瓷基体复合材料。
4.根据权利要求2所述的方法,其特征在于,所述密封件包括镍基合金。
5.根据权利要求4所述的方法,其特征在于,所述镍基合金具有如下以重量计的组成:约0.015%的硼,约0.05%至约0.15%的碳,约20%至约24%的铬,约3%的铁,约0.02%至约0.12%的镧,约1.25%的锰,约20%至约24%的镍,约0.2%至约0.5%的硅,约13%至约15%的钨,且余量为钴;或者所述镍基合金具有如下以重量计的组成:约19%至约21%之间的铬、约15%的钨、约9%至约11%之间的镍、约3%的铁、约1%至约2%之间的锰、约0.40%的硅、约0.030%的硫,且余量为钴。
6.根据权利要求1所述的方法,其特征在于,所述表面(111)选自陶瓷基体复合材料燃气涡轮机部件中的减震器销的减震器腔体表面、陶瓷基体复合材料燃气涡轮机旋转机翼的楔形榫头附接面、陶瓷基体复合材料燃气涡轮机非旋转机翼的楔形榫头附接面。
7.根据权利要求1所述的方法,其特征在于,所述表面粗糙度小于3微米。
8.根据权利要求1所述的方法,其特征在于,所述表面粗糙度为1微米至2微米之间。
9.根据权利要求1所述的方法,其特征在于,所述经改性的表面基本上不含纤维。
10.根据权利要求1所述的方法,其特征在于,所述经改性的表面(113)包括具有如下以重量计的组成的沉积材料:约0.015%的硼,约0.05%至约0.15%的碳,约20%至约24%的铬,约3%的铁,约0.02%至约0.12%的镧,约1.25%的锰,约20%至约24%的镍,约0.2%至约0.5%的硅,约13%至约15%的钨,且余量为钴。
11.一种通过权利要求1所述的方法制得的陶瓷基体复合材料燃气涡轮机部件(110),其具有所述经改性的表面(113)。
12.一种陶瓷基体复合材料燃气涡轮机部件(110),其包括:
包括小于6微米的表面粗糙度的经改性的表面(113);
其中所述经改性的表面(113)选自施用至陶瓷基体复合材料燃气涡轮机部件(110)的表面(111)的未增强的基体层片、气相沉积至表面(111)上的硅、经珩磨的表面、施用至表面(111)的钎料膏,以及它们的组合。
13.一种珩磨陶瓷基体复合材料表面(111)的方法,所述方法包括:
提供非研磨材料;
与陶瓷基体复合材料表面(111)相邻设置所述非研磨材料;和
通过进行至少约300个珩磨循环而将所述非研磨材料的至少一部分沉积至陶瓷基体复合材料表面(111)上的裂缝中;
其中所述珩磨循环中的每一个包括相对于彼此移动所述非研磨材料或所述陶瓷基体复合材料表面(111)中的至少一者。
14.根据权利要求13所述的方法,其还包括进行约500至约10,000个之间的珩磨循环。
15.根据权利要求13所述的方法,其还包括提供约450°F至1200°F之间的珩磨温度,约40,000psi至约80,000psi之间的珩磨接触压力,以及约0.0005英寸至0.040英寸之间的珩磨位移。
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