CN101793195A - 用于增强涡轮发动机部件的热传递的方法和系统 - Google Patents
用于增强涡轮发动机部件的热传递的方法和系统 Download PDFInfo
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- CN101793195A CN101793195A CN200910266855A CN200910266855A CN101793195A CN 101793195 A CN101793195 A CN 101793195A CN 200910266855 A CN200910266855 A CN 200910266855A CN 200910266855 A CN200910266855 A CN 200910266855A CN 101793195 A CN101793195 A CN 101793195A
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- 230000002708 enhancing effect Effects 0.000 title abstract 2
- 239000011248 coating agent Substances 0.000 claims abstract description 62
- 238000000576 coating method Methods 0.000 claims abstract description 62
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- 229910000943 NiAl Inorganic materials 0.000 claims description 17
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- 229910052759 nickel Inorganic materials 0.000 description 9
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- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
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- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 2
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- 239000012535 impurity Substances 0.000 description 2
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- MRELNEQAGSRDBK-UHFFFAOYSA-N lanthanum(3+);oxygen(2-) Chemical compound [O-2].[O-2].[O-2].[La+3].[La+3] MRELNEQAGSRDBK-UHFFFAOYSA-N 0.000 description 2
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 2
- 239000000395 magnesium oxide Substances 0.000 description 2
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- PLDDOISOJJCEMH-UHFFFAOYSA-N neodymium(3+);oxygen(2-) Chemical compound [O-2].[O-2].[O-2].[Nd+3].[Nd+3] PLDDOISOJJCEMH-UHFFFAOYSA-N 0.000 description 2
- UZLYXNNZYFBAQO-UHFFFAOYSA-N oxygen(2-);ytterbium(3+) Chemical compound [O-2].[O-2].[O-2].[Yb+3].[Yb+3] UZLYXNNZYFBAQO-UHFFFAOYSA-N 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 229910001404 rare earth metal oxide Inorganic materials 0.000 description 2
- 229910052702 rhenium Inorganic materials 0.000 description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 2
- HYXGAEYDKFCVMU-UHFFFAOYSA-N scandium oxide Chemical compound O=[Sc]O[Sc]=O HYXGAEYDKFCVMU-UHFFFAOYSA-N 0.000 description 2
- 229910052715 tantalum Inorganic materials 0.000 description 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 229910052721 tungsten Inorganic materials 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- 229910003454 ytterbium oxide Inorganic materials 0.000 description 2
- 229940075624 ytterbium oxide Drugs 0.000 description 2
- 229910052727 yttrium Inorganic materials 0.000 description 2
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 2
- KJTLSVCANCCWHF-UHFFFAOYSA-N Ruthenium Chemical compound [Ru] KJTLSVCANCCWHF-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- CETPSERCERDGAM-UHFFFAOYSA-N ceric oxide Chemical compound O=[Ce]=O CETPSERCERDGAM-UHFFFAOYSA-N 0.000 description 1
- 229910000422 cerium(IV) oxide Inorganic materials 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910001235 nimonic Inorganic materials 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 229910000484 niobium oxide Inorganic materials 0.000 description 1
- URLJKFSTXLNXLG-UHFFFAOYSA-N niobium(5+);oxygen(2-) Chemical compound [O-2].[O-2].[O-2].[O-2].[O-2].[Nb+5].[Nb+5] URLJKFSTXLNXLG-UHFFFAOYSA-N 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 229910001173 rene N5 Inorganic materials 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 229910052707 ruthenium Inorganic materials 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- -1 yittrium oxide Chemical compound 0.000 description 1
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Abstract
本发明涉及用于增强涡轮发动机部件的热传递的方法和系统，其包括将具有高热导率的含金属敷层应用到涡轮机部件的冷侧面上，从而增强离开部件的热传递。该含金属敷层可被粗糙化以改善热传递。敷层可以是NiAl结合敷层，其具有大于约50％重量的铝含量。
Description
技术领域
本公开致力于一种用于改进涡轮发动机部件(component)的运行的方法和装置。具体地说，本公开涉及具有增强了热传递的敷层(coating)的涡轮发动机部件。
背景技术
涡轮发动机的，例如燃气轮机的效率随着涡轮机的燃烧温度(换句话说作为工作温度而已知)的提高而提高。这种温度上的提高在使用相同的(若不是更少的)燃料的情况下导致功率方面的至少某些提升。因而，期望升高涡轮机的燃烧温度以提高效率。
然而，随着燃气轮机的燃烧温度升高，包括但不局限于燃烧衬套(combustion liner)和过渡连接件(换句话说作为导管而已知)等的燃烧部件(combustion component)的金属温度(metal temperature)会提高。燃烧衬套结合到涡轮机中，并部分地与过渡连接件或导管一起限定了供火焰燃烧燃料的区域。这些部件，以及气路环境中的其它部件，遭受极高的温度极限和由于氧化的和腐蚀性的环境带来的老化(degradation)。
涡轮机燃烧部件，例如但不局限于燃烧衬套、导管、燃烧器偏转器、燃烧器中心体、喷嘴以及其它结构硬件，通常由耐热材料形成。这种耐热材料常覆有其它耐热材料。例如，涡轮机部件可由锻造的(wrought)超级合金形成，其例如为但不局限于哈斯特洛伊镍基耐蚀耐热合金(Hasteloy alloy)、尼莫尼克镍铬系耐热合金、因科内尔镍铬铁耐热耐蚀合金、以及其它类似的合金。这些超级合金在高温下，例如在大于约1500°F的温度下不具有所期望的抗氧化性。因此，为了降低涡轮机部件温度并为了提供抵抗热燃烧气体的氧化和腐蚀保护，常将耐热敷层，例如但不局限于结合敷层和热障敷层(TBC)应用到暴露在热的燃烧气体下的涡轮机部件的(或换句话说作为热侧表面而已知的)表面上。例如，涡轮机部件可包括热喷涂的(thermallysprayed)MCrAlY重叠敷层作为结合覆层(bond coat)，以及空气等离子体喷涂的(APS)氧化锆基(zirconia-based)陶瓷作为隔热的TBC。通常，TBC是用氧化钇陶瓷稳定的氧化锆。
近年来，带有低热导率(thermal conductivity)的陶瓷顶面层成分提高了运行温度，并使仅将热障敷层应用到涡轮机部件的热侧面的性能变紧张。目前的TBC系统在某些应用中已经在使用中很好地完成任务，然而还在寻求改进的敷层，以达到用于更长的维修间隔的更大的温度-热循环时间性能或温度性能。
所需要的是这样一种敷层系统，其增强了自涡轮机部件的热传递，容许涡轮机部件在更高的系统温度下运行。
发明内容
在一示例性的实施例中，公开了一种涡轮机燃烧部件，其包括具有热侧表面(hot side surface)和冷侧表面(cold side surface)的衬底(substrate)，以及具有高热导率的外表面(outside surface)。该外表面是该冷侧表面或第二结合覆层的表面。
在另一示例性的实施例中，公开了一种用于衬底的热障敷层系统，其包括沉积在衬底的热侧表面上并与之相接触的第一结合覆层、沉积在该第一结合覆层上并与之相接触的陶瓷层(ceramiclayer)、以及具有高热导率的外表面。该外表面是该衬底的冷侧表面或第二结合覆层的表面。
在另一示例性的实施例中，公开了一种改善部件的热传递的工艺，其包括提供具有第一表面和第二表面的衬底，使第一结合覆层沉积在第一表面上并与之相接触，使陶瓷层沉积在第一结合覆层上并与之相接触，以及提供具有高热导率的外表面。该外表面是该第二表面或第二结合覆层的表面。
本公开的一个优势包括结合覆层温度的降低。
本公开的另一优势包括提高的部件寿命。
本公开的另一优势是在较低的冷却空气流量情况下的运行，由此改善了发动机效率。
本公开的另一优势是在更高的温度下运用TBC表面，由此改善了发动机效率。
本公开的另一优势是更轻的结合敷层的使用。
联系以示例性的方式显示了本公开的原理的附图，从以下的优选实施例的更详细的描述中将明晰本公开的其它特征和优势
附图说明
图1显示了具有根据依据本公开的一个示例性实施例的结合覆层的热障敷层系统的示意图。
图2显示了针对NiAl敷层和NiCrAlY敷层的热导率的比较。
在任何可能的地方，遍及附图将使用相同的参考标号来代表相同的零件。
具体实施方式
在一个实施例中，本公开通常适用于这样的金属部件，其受到热障敷层(TBC)系统的保护以抵抗热有害环境。这种部件的值得注意的示例包括燃气涡轮发动机的高压和低压涡轮喷嘴(导叶)、护罩、燃烧衬套、过渡连接件、涡轮框架和增压器硬件。虽然本公开特别适用于涡轮发动机部件，但是本公开的知识通常适用于任何这样的部件，即，在该部件上，热障可用于使该部件与其环境热隔离开。
图1显示了根据本公开的具有TBC系统(敷层系统)10的涡轮发动机部件5的局部横截面图。涡轮发动机部件5包括衬底20，敷层系统10沉积在该衬底20上。衬底20包括第一表面22和相对的第二表面24。第一表面22是热侧表面，或换句话说，是面向部件5的热运行温度的表面。例如，第一表面22可面向热涡轮气体流。第二侧表面24是冷侧表面，或换句话说，是远离部件5的热运行温度的表面。第二侧表面24可面向冷却气体。在图1所示的横截面中，第一表面22和第二表面24是平行的，然而，在备选的布置中，衬底20可包括与发动机部件5相适应的任意布置的表面。
在一个实施例中，衬底20由任何可运用的材料所形成。例如，衬底20可由多种金属或金属合金中的任意者所形成，包括那些基于镍、钴和/或铁的合金或超级合金。在一个实施例中，衬底20由镍基合金制成，并且在另一实施例中，衬底20由镍基超级合金制成。镍基超级合金可由γ主要的或相关的相的沉淀(precipitation ofgamma prime or a related phase)所强化。在一个示例中，镍基超级合金具有如下成分(以重量百分比为单位)：从大约4％至大约20％的钴、从大约1％至大约10％的铬、从大约5％至大约7％的铝、从大约0％至大约2％的钼、从大约3％至大约8％的钨、从大约4％至大约12％的钽、从大约0％至大约2％的钛、从大约0％至大约8％的铼、从大约0％至大约6％的钌、从大约0％至大约1％的铌、从大约0％至大约0.1％的碳、从大约0％至大约0.01％的硼、从大约0％至大约0.1％的钇、从大约0％至大约1.5％的铪、平衡量的镍和附带的杂质。例如，合适的镍基超级合金可通过商标名Rene N5而获得，其具有按重量的7.5％的钴、7％的铬、1.5％的钼、6.5％的钽、6.2％的铝、5％的钨、3％的铼、0.15％的铪、0.004％的硼和0.05％的碳以及平衡量的镍和较少的杂质的公称成分。
根据本公开的一个实施例，敷层系统10包括位于第一侧表面22之上并与之相接触的结合覆层30，以及位于第二侧表面24之上并与之相接触的含金属层(metallic layer)32。敷层系统10还包括覆盖第一结合覆层30的陶瓷层。
在一个实施例中，结合覆层30和含金属层32可以是金属，含金属的材料(metallic)，金属间化合物(intermetallic)，金属合金，复合物和其组合。结合覆层30和含金属层32可具有相同或不同的成分。在一个实施例中，结合覆层30和含金属层32可以是NiAl。在一个实施例中，结合覆层30是NiAl，例如主要为βNiAl相，带有有限的合金化附加物。NiAl敷层可具有从大约9％重量至大约12％重量的铝含量，平衡量主要为镍，并且在另一实施例中，具有从大约18％重量至大约21％重量的铝含量，平衡量主要为镍。结合敷层的整体(bulk)可由利用例如空气等离子体喷涂(APS)、线电弧喷涂、高速氧化燃料(HVOF)喷涂和低压等离子体喷涂(LPPS)工艺等的沉积工艺所形成的密集的NiAl层组成。在一个实施例中，结合覆层的成分并不局限于NiAl结合敷层，而是可以是任何带有合适的结合性能和温度性能的含金属敷层。例如，结合覆层30可以是NiCrAlY敷层。结合覆层30可具有大约100至大约300微米的厚度。结合敷层的厚度可根据部件和运行环境而变化。
根据本公开，含金属层32是高热导率的含金属材料。在一个实施例中，含金属层32具有大约20和大约60BTU/hr ft°F之间的热导率。在另一实施例中，含金属层32具有大约30和大约45BTU/hr ft°F之间的高热导率。在又一实施例中，含金属层32具有大约38和大约42BTU/hr ft°F之间的热导率。在一个实施例中，含金属层32可以是具有高热导率的NiAl敷层。例如，含金属层32可以是具有大于大约50％重量的铝含量的NiAl。在一个实施例中，通过沉积方法，例如通过空气等离子体喷涂(APS)、线电弧喷涂、高速氧化燃料(HVOF)喷涂和低压等离子体喷涂(LPPS)工艺而沉积出含金属层32。在一个实施例中，含金属层32可具有从大约50至大约600微米的、更优选地从大约200至大约400微米的厚度。含金属层32的厚度可根据部件和运行环境而变化。
通过如图2中所示的、空气等离子体喷涂(APS)的NiAl和NiCrAlY敷层的热导率的比较，可懂得使用NiAl的含金属层32的好处。如从图2中可看出的，APS NiAl敷层在涡轮机部件的运行的温度范围上具有高的热导率，其增强了自衬底20的热传递。
在一个实施例中，可使用低热导率的含金属结合覆层作为第一结合覆层30，并且，可使用高热导率的含金属层作为含金属层32。例如，在一个实施例中，第一结合覆层30可以是NiCrAlY结合覆层，并且含金属层32可以是具有高热导率的NiAl结合覆层。
在一个实施例中，陶瓷层34可以是低热导率的陶瓷。例如，低热导率陶瓷可具有为大约0.1至1.0BTU/ft hr°F的，优选在为0.3至0.6BTU/ft hr°F的范围中的热导率。在一个实施例中，低热导率陶瓷可以是氧化锆、氧化钇、氧化镱和氧化铌(nyodenium oxide)的混合物。在另一实施例中，低热导率陶瓷可以是氧化钇稳定的氧化锆(YSZ)。在一个实施例中，陶瓷层34可以是具有大约3％重量至大约10％重量的氧化钇的成分的YSZ。在另一实施例中，陶瓷层34可以是其它陶瓷材料，例如氧化钇，非稳定的氧化锆、或通过其它氧化物，例如氧化镁(MgO)、二氧化铈(CeO2)、氧化钪(Sc2O3)或氧化铝(Al2O3)等而稳定的氧化锆。在又一些实施例中，陶瓷层34可包括一种或多种稀土氧化物，例如但不局限于氧化镱、氧化钪、氧化镧、氧化钕、氧化铒和其组合。在该又一些实施例中，稀土氧化物可代替稳定的氧化锆系统中的一部分或所有氧化钇。陶瓷层34沉积到足以为下层衬底提供所要求的热保护的厚度，通常从大约75至大约350微米左右。如在现有技术的结合敷层的情况下一样，第一结合覆层30包括氧化物表面层(氧化皮)31，陶瓷层34以化学方式结合到其上。
再次参看图1，含金属层32具有外表面36。外表面36可暴露于比陶瓷层34所暴露于的温度低的温度下。在一个实施例中，外表面36粗糙化至大约300和900微英寸之间，以增强热传递。在另一实施例中，外表面36粗糙化至大约500和700微英寸之间。外表面36的粗糙度可在含金属层32的沉积期间形成，并可通过控制包括但不局限于粒径和喷涂速度等的沉积工艺参数而被控制。粗糙化可呈凹痕和/或凹槽的形式。在另一实施例中，在含金属层32的沉积之后，通过例如机械的或化学的粗糙化工艺可使外表面36粗糙化和/或额外地粗糙化。
在另一示例性的实施例中，含金属层32不存在，并且外表面36是衬底20的第二侧表面24。在这个实施例中，衬底20可由高热导率的含金属成分形成。在一个实施例中，衬底20可以是高热导率的金属、含金属的材料、金属间化合物、金属合金、复合物和其组合。
在一个实施例中，衬底可具有大约20和大约60BTU/hrft°F之间的热导率。在另一实施例中，衬底20具有大约30和大约45BTU/hr ft°F之间的高的热导率。在又一实施例中，衬底20具有大约38和大约42BTU/hr ft°F之间的热导率。在一个实施例中，衬底20可以是具有高热导率的NiAl。例如，衬底20可由具有超过大约50％重量的铝的铝含量的NiAl所形成。此外，可对外表面36进行粗糙化，以提高热传递。在一个实施例中，外表面36粗糙化至大约300和900微英寸之间，以提高热传递。在另一实施例中，外表面36可粗糙化至大约500和700微英寸之间。外表面36的粗糙度可在衬底20的成形期间被形成。例如，外表面36的粗糙度可在衬底20的铸造期间被形成。粗糙化可呈凹痕和/或凹槽的形式。在另一实施例中，可在第二结合覆层32的沉积之后通过例如机械的或化学的粗糙化工艺而使外表面36粗糙化和/或额外粗糙化。
虽然已经参照优选实施例描述了本发明，但是本领域中的技术人员应该懂得，可进行各种变化且可用等效物来替代其元件而而不会脱离本发明的范围。另外，还可作出许多改型以使特定的情形或材料适应本发明的教导而不会脱离本发明的本质范围。因此，所意图的是，本发明并不局限于作为被构思用于实现本发明的最佳模式而公开的特定的实施例，相反，本发明将包括落在所附权利要求范围内的所有实施例。
Claims (10)
1.一种涡轮机燃烧部件(5)，其包括：
衬底(2)，其具有热侧表面(22)和冷侧表面(24)；和
具有高热导率的外表面；
其中，所述外表面是所述冷侧表面(24)或含金属层(32)的表面。
2.根据权利要求1所述的部件(5)，其特征在于，所述高热导率在大约20和大约60 BTU/hr ft°F之间。
3.根据权利要求1所述的部件(5)，其特征在于，所述外表面具有在大约300和大约900微英寸之间的粗糙度。
4.根据权利要求1所述的部件(5)，其特征在于，所述衬底(20)是具有高热导率的NiAl。
5.根据权利要求1所述的部件(5)，其特征在于，还包括沉积在所述热侧表面(22)上并与之相接触的结合覆层(30)，以及沉积在所述结合覆层(30)上并与之相接触的陶瓷层(34)。
6.根据权利要求1所述的部件(5)，其特征在于，所述冷侧表面(24)是所述外表面。
7.根据权利要求1所述的部件(5)，其特征在于，所述部件(5)还包括：
沉积在所述热侧表面(22)上并与之相接触的结合覆层(30)；和
沉积在所述结合覆层(30)上并与之相接触的陶瓷层(34)；
其中，所述外表面是沉积在所述冷侧表面(24)上并与之相接触的含金属层(32)的表面。
8.根据权利要求7所述的部件(5)，其特征在于，所述含金属层(32)是包含大于大约50％重量的铝的NiAl。
9.根据权利要求8所述的部件(5)，其特征在于，所述含金属层(32)具有在大约50μm和大约600μm之间的厚度。
10.根据权利要求7所述的部件(5)，其特征在于，所述含金属层(32)具有在大约50μm和大约600μm之间的厚度。
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| CN112739663A (zh) * | 2018-09-07 | 2021-04-30 | 西门子能源全球有限两合公司 | 基于氧化锆且具有另外的氧化物的陶瓷材料和层体系 |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN101793195B (zh) | 2015-04-08 |
| JP5815920B2 (ja) | 2015-11-17 |
| EP2204540A3 (en) | 2013-02-13 |
| JP2010156327A (ja) | 2010-07-15 |
| EP2204540A2 (en) | 2010-07-07 |
| US20100162715A1 (en) | 2010-07-01 |
| US8722202B2 (en) | 2014-05-13 |
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