CN1231384A - 燃气轮机中引导热燃气的集气管 - Google Patents
燃气轮机中引导热燃气的集气管 Download PDFInfo
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Abstract
本发明涉及一燃气轮机中设置在燃烧室与涡轮叶片之间的用以引导热气的集气管(1),设有用以接收热气的两个进气口(2)和出口。集气管的材料是在一耐高温和抗腐蚀的基础金属(9)上在其内侧和外侧涂覆一抗高温腐蚀和氧化的涂层(4)。在内锥(13)的区域内,基础金属的一侧涂覆一HKO涂层,在其对面的一侧涂覆一绝热层(8)。
Description
本发明涉及一燃气轮机中在燃烧室与涡轮叶片的进气口凸缘之间用以引导热燃气的集气管，它是由一耐高温和抗腐蚀的基础金属M(衬底)在其内侧涂覆以抗高温腐蚀和氧化的涂层而制成的。
在燃气轮机设备中，在燃烧室外壳与涡轮叶片的进气接管之间的双臂集气管或叉形管，在热的工作状态下由于温度、压力和腐蚀而受到较大的应力和磨损。
燃烧用的空气在一压缩机中被压缩到很高的压力，其主要部分用来在两个燃烧室内燃烧，一小部分用来冷却受热的金属部件。
在燃烧室内，空气中的主要氧气部分通过载碳体的燃烧而使之氧化，而氮气仍作为碴质而保留在排气中，排气通过高压的燃烧而处于很高的温度，并从燃烧室流出而进入叉形管，再从那里进入涡轮机的叶片上而使之以高速进行旋转。
集气管或叉形管由一铁镍的基础材料制成，它在高压下特别是在高的气体温度下而受到腐蚀，其中氧气使金属表面氧化。
镍基合金的合金元素如铝、铬或其他类似元素，可通过固定氧化层的形成而减少一种其他的氧化层。
但这种钝态的氧化层不能防止氮的渗透，因此氮能逐渐同上述的合金元素形成氮化物或碳氮化物。这种形成通过气体的高压压热力学上是很容易的。
其结果是根据合金的成分和氮的溶解度在氧化层下面能形成AIN(氮化物)和/或铬-碳氮化物。
这一方面将导致金属中铝浓度的分解而降低其氧化的阻力，并形成AIN针和/或铬-碳氮化物，它会使金属变脆。
这种机理不仅发生在叉形管的燃烧室中，而且也发生在供有冷却空气的外表面上，如果它未被冷却到使所述的气体-金属反应不能发生的程度的话。
作为高温腐蚀的保护，集气管的整个内侧覆盖以单层的MCrAlY涂层，它的特征是具有一较高的铬和铝的含量，在这里使用的是在镍基上施以31％铬、11％铝和0.6％钇的粉末喷涂。
通过提高铬和铝的含量并同钇相结合而成的HKO涂层提高了抗氧化和渗氮的阻力，从而提高了抗高温腐蚀和氧化的阻力。
作为附加的腐蚀和热的防护，在集气管内锥面的受热表面上涂有绝热涂层(TBC)。
绝热涂层是一个由一粘合层和一陶瓷覆盖层所组成的等离子喷涂系统，它起着涂层系统的绝热作用。
粘合涂层除了用来粘合覆盖层以外，还用以避免材料的高温腐蚀/氧化。为了能最佳地满足此两种功能起见，此粘合层由一双层的MCrAlY涂层组成，即所谓的粘合层A和B。
粘合层A是一种具有降低的铬和铝含量的可延伸的MCrAlY涂层，以保证长期最佳地粘合在衬底上。
粘合层B是一种具有增高的铬和铝含量的MCrAlY涂层，因此它除了提高抗高温或氧化的阻力以外还能防止基础材料的渗氮。
覆盖层(顶层)由一ZrO2-Y2-O3陶瓷组成，由于其导热性很小，所以能起到涂层的绝热作用。
对于燃气轮机部件所需的在中、高温下，与从燃烧室排出的热燃气直接相接触的耐高温和抗腐蚀的保护层合金已经发展了多种组成并可从市埸获得，它们主要包括镍、铬、钴、铝和稀土金属的混合物。
从WO89/07159中已知有用于金属物体，特别是用于燃气轮机叶片的多重保护层。据了解它对于这种物体的使用寿命而言具有极为重要的两种不同的抗腐蚀机理。它有两层相叠的保护层，其中内层是用来保护温度在600℃-800℃时的抗腐蚀作用，而外层是在800℃-900℃时为最佳。外部的覆盖层还能附加作为一绝热层。第一覆盖层最好是一个扩散层，其含铬量大于50％和铁和/或锰的含量大于10％；作为第二覆盖层是一MCrAlY涂层，例如约有30％的铬，约7％的铝和0.7％的钇，它是在降低的压力下，通过等离子喷涂来涂覆的。
从WO91/02108中已知有一种在温度范围从600℃-1150℃内具有良好的抗腐蚀特性的保护层，特别适用于燃气轮机部件，保护层的重量百分比为：25-40％的镍，28-32％的铬，7-9％的铝，1-2％的硅，0.3-1％的钇，其余为至少5％的钴，以及不可避免的杂质。也可采用不同的组分。通过额外附加一些铼能使保护层的特性进一步提高。此效果只需添加少量铼便能达到。最好是铼的含量在4-10％之间。
涂层可通过等离子喷涂或蒸涂(PVD)来进行，它特别适用于在镍基或钴基上的超级合金所制的燃气轮机叶片上。其他燃气轮机部件，特别是在入口温度超过1200℃的燃气轮机中，也能采用这种保护涂层。
从WO96/34128中已知有一种镍或钴的合金，在其上涂覆对来自燃气轮机燃烧室的热燃气的高温腐蚀作用的保护层。
三重的保护层包括第一层由MCrAlY组成的粘合层叠合在待保护的金属基体上，以及叠合外部氧化层上的第二层锚固层。
从WO96/34129中已知有一种在镍或钴合金基板上的金属衬底，在其上涂覆以一抗高温腐蚀的保护系统。
该保护系统由一中间层组成，它包括一叠合在镍衬底上的粘合层和一叠合在锆氧化物基体的外部陶瓷层上的锚固层。此外部的陶瓷层在这里是作为一绝热层。
从DE424299已知有一种装置，特别是燃气轮机装置，它的部件上具有一涂层。
那里，在燃气轮机系统和在工作中与热燃气接触的类似装置中的部件设有一涂层，它不仅具有防腐蚀作用，而且还有催化作用。这里在温度范围超过600℃时部件设有一具有氧化催化作用的涂层，而温度范围在350℃-600℃时部件则设有一具有还原催化作用的涂层。对于第一种涂层采用在镧锰基体上的具有钙钛矿型结构或尖晶石结构的混合氧化物，而对于第二种涂层采用在镧铜基体上的具有与上述同样结构的混合氧化物。
本发明的任务在于阻止或远远推迟在集气管热的内表面上的燃气与金属的反应，使部件的使用寿命显著延长，并在集气管经冷却的外表面上也阻止或推迟燃气与金属的反应，使部件的使用寿命显著延长。
此任务是根据权利要求1来解决的。从属的权利要求涉及引导热燃气用的集气管的有利的安排。
按照本发明，在燃烧室外壳与涡轮之间用以引导热燃气的集气管或叉形管不仅在内部而且在外部均设有一抗高温腐蚀和氧化的涂层，它是由一单层的MCrAlY涂层组成，以阻止或推迟氮与集气管金属的反应。在这里金属基体M由一铁-镍或铁-铬合金(M=Ni或Cr)组成。
在具有31％的铬，11％的铝，0.6％的钇和其余为镍的含量的抗高温腐蚀和氧化的涂层中，铬与铝的含量是很高的，所以保护层对于氧化和渗氮具有很大的阻止潜力，因此具有很高的抗高温腐蚀和氧化的能力。
整个叉形管内部和外部的涂层是通过手动或程序控制的MCrAlY等离子喷涂来实现的，其涂层厚度为60±40微米。
集气管的内锥在过渡到燃气轮机处，在其单面附加覆盖一绝热层。此绝热层如已知的那样由一双层的MCrAlY-涂层A和B-以及一陶瓷的覆盖层组成。
粘合层A是一具有降低的铬和铝含量的可延伸的MCrAlY涂层，以便把此涂层粘合在集气管的基础材料上。
粘合层B符合于抗高温腐蚀和氧化层的组成。
绝热层通过一在锆基上的陶瓷覆盖层来作为补充，由于它的导热性很小，所以能起绝热作用。绝热层由一厚度为60/60/250微米的涂层所组成。
集气管在两个进气口上附加设有一耐磨的涂层。
本发明的实施例将按照以下的示意图予以说明，其中：
图1集气管的多维视图，
图2通过具有两侧HKO涂层的叉形管的截面图
图3通过集气管在两个进气口中之一的区域的截面图
图4通过绝热层的截面图
图1表示集气管或叉形管1的多维视图，在其上部区域设有两个用于来自图中未表示的燃烧室的热燃气进气口2。
集气管1不仅在外部而且在内部均覆盖以一抗高温腐蚀和氧化的涂层4。
热气(如箭头所示)从两个燃烧室通过进气口2而流入集气管1，在其下部的集气室3内集合，然后离开集气管1而流向涡轮机，在那里集气管1借助一外部凸缘5和一内部凸缘6连接在涡轮机的相应的凸缘上。
图2表示具有抗高温腐蚀和氧化(HKO)涂层的叉形管侧壁的一个截面，在基础金属9的两侧涂有一厚度为60微米的HKO涂层4。
图3表示通过集气管1的一个截面，集气管1设置在未表示的燃烧室与其后面所连接的涡轮机之间。
热的有腐蚀性的排气离开燃烧室的混合管并通过进气口2而流入设在一未表示的外壳内的燃烧室外壳凸缘与涡轮机凸缘之间的集气管1内。
在其两侧涂覆以HKO涂层4的集气管1的基体金属9的外部通过一冷却介质予以冷却。
压缩的热燃气被引入在凸缘5和6之间的集气室3中，然后流入涡轮机中推动带有涡轮叶片的涡轮转子旋转。
集气管1的进气口2在气体入口区域内附加设有一耐磨的涂层7。
内锥13在凸缘区域内附加覆盖一绝热层8来取代HKO涂层4。
根据图4，绝热层8由一双层(A和B)MCrAlY涂层组成，其中A层10作为粘合基层叠合在基础金属9上，而B层11作为叠合在陶瓷层12上的粘合基层。
在内锥区域内，衬底/基础金属9的一侧由HKO涂层4来保护，在另一侧由绝热层8来保护。
Claims (6)
1．一个燃气轮机中在燃烧室与涡轮叶片的进气凸缘之间用以引导热燃气的集气管是由一在耐高温和抗腐蚀的基础金属M上的内侧涂覆以抗高温腐蚀和氧化的涂层而制成，其特征在于：集气管(1)的基础金属(9)不仅在其内侧而且在其外侧涂覆以一抗高温腐蚀和氧化的涂层(4)。
2．根据权利要求1的引导热燃气的集气管，其特征在于：基础金属M由一镍基的合金制成。
3．根据权利要求1和2的引导热燃气的集气管，其特征在于：抗高温腐蚀和氧化涂层或MCrAlY涂层(4)的组成成分包括31％铬，11％铝和0.6％钇。
4．根据权利要求1-3的引导热燃气的集气管，其特征在于：内锥(13)的基础金属(9)附加地覆盖一单层的绝热涂层(8)。
5．根据权利要求4的引导热燃气的集气管，其特征在于：绝热层(8)由一双层(A和B)的MCrAlY涂层(10,11)和一陶瓷覆盖层(12)组成。
6．根据权利要求5的引导热燃气的集气管，其特征在于：A层(10)是一可延伸的具有降低的铬和铝含量的MCrAlY涂层，而涂层B(11)是一具有增高的铬和铝含量的MCrAlY涂层。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19815473.9 | 1998-04-07 | ||
| DE19815473A DE19815473A1 (de) | 1998-04-07 | 1998-04-07 | Heißgasführendes Gassammelrohr einer Gasturbine |
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| CN1231384A true CN1231384A (zh) | 1999-10-13 |
| CN1143056C CN1143056C (zh) | 2004-03-24 |
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| CNB991036093A Expired - Fee Related CN1143056C (zh) | 1998-04-07 | 1999-03-05 | 燃气轮机中引导热燃气的集气管 |
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| US (1) | US6226978B1 (zh) |
| EP (1) | EP0949410B1 (zh) |
| JP (1) | JP3823282B2 (zh) |
| CN (1) | CN1143056C (zh) |
| CA (1) | CA2263834C (zh) |
| DE (2) | DE19815473A1 (zh) |
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| CN1740641B (zh) * | 2004-02-12 | 2011-01-19 | 通用电气公司 | 燃烧器部件及制造燃烧器组件的方法 |
| CN102177222B (zh) * | 2008-09-05 | 2014-06-18 | 英特凯特设备有限公司 | 调节一个或者多个单元中材料藏量的材料提取设备和方法 |
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| DE19934418A1 (de) * | 1999-07-22 | 2001-01-25 | Abb Alstom Power Ch Ag | Verfahren zum Beschichten einer lokal unterschiedlich beanspruchten Komponente |
| DE10032454A1 (de) * | 2000-07-04 | 2002-01-17 | Man Turbomasch Ag Ghh Borsig | Vorrichtung zum Kühlen eines ungleichmäßig stark temperaturbelasteten Bauteiles |
| US6673467B2 (en) | 2001-10-01 | 2004-01-06 | Alstom (Switzerland) Ltd | Metallic component with protective coating |
| DE10163171A1 (de) * | 2001-12-21 | 2003-07-03 | Solvay Fluor & Derivate | Neue Verwendung für Legierungen |
| DE10239534A1 (de) | 2002-08-23 | 2004-04-22 | Man Turbomaschinen Ag | Heißgas führendes Gassammelrohr |
| DE102005060243A1 (de) | 2005-12-14 | 2007-06-21 | Man Turbo Ag | Verfahren zum Beschichten einer Schaufel und Schaufel einer Gasturbine |
| EP1798300A1 (de) * | 2005-12-16 | 2007-06-20 | Siemens Aktiengesellschaft | Legierung, Schutzschicht zum Schutz eines Bauteils gegen Korrosion und/oder Oxidation bei hohen Temperaturen und Bauteil |
| DE102007048484A1 (de) * | 2007-10-09 | 2009-04-16 | Man Turbo Ag | Heißgasgeführte Komponente einer Strömungsmaschine |
| EP2224167A1 (de) * | 2009-02-25 | 2010-09-01 | Siemens Aktiengesellschaft | Gehäuse einer Gasturbine |
| EP3372707B1 (en) * | 2013-03-15 | 2022-06-29 | Raytheon Technologies Corporation | Spallation resistant thermal barrier coating |
| US10054008B2 (en) * | 2015-02-09 | 2018-08-21 | United Technologies Corporation | Turbomachine accessory gearbox bracket |
| USD818502S1 (en) | 2015-12-17 | 2018-05-22 | General Electric Company | Turbocharger transition section |
| USD814522S1 (en) * | 2016-06-21 | 2018-04-03 | General Electric Company | Transition section for a turbocharged engine |
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| US5223045A (en) * | 1987-08-17 | 1993-06-29 | Barson Corporation | Refractory metal composite coated article |
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| US5116690A (en) * | 1991-04-01 | 1992-05-26 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Oxidation resistant coating for titanium alloys and titanium alloy matrix composites |
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- 1998-04-07 DE DE19815473A patent/DE19815473A1/de not_active Withdrawn
-
1999
- 1999-02-18 EP EP99103176A patent/EP0949410B1/de not_active Expired - Lifetime
- 1999-02-18 DE DE59906280T patent/DE59906280D1/de not_active Expired - Lifetime
- 1999-03-02 CA CA002263834A patent/CA2263834C/en not_active Expired - Lifetime
- 1999-03-05 CN CNB991036093A patent/CN1143056C/zh not_active Expired - Fee Related
- 1999-03-05 US US09/263,036 patent/US6226978B1/en not_active Expired - Lifetime
- 1999-03-17 JP JP11268399A patent/JP3823282B2/ja not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1740641B (zh) * | 2004-02-12 | 2011-01-19 | 通用电气公司 | 燃烧器部件及制造燃烧器组件的方法 |
| CN102177222B (zh) * | 2008-09-05 | 2014-06-18 | 英特凯特设备有限公司 | 调节一个或者多个单元中材料藏量的材料提取设备和方法 |
Also Published As
| Publication number | Publication date |
|---|---|
| DE59906280D1 (de) | 2003-08-21 |
| JP3823282B2 (ja) | 2006-09-20 |
| CN1143056C (zh) | 2004-03-24 |
| DE19815473A1 (de) | 1999-10-14 |
| EP0949410B1 (de) | 2003-07-16 |
| CA2263834C (en) | 2004-10-19 |
| EP0949410A2 (de) | 1999-10-13 |
| CA2263834A1 (en) | 1999-10-07 |
| JPH11336563A (ja) | 1999-12-07 |
| EP0949410A3 (de) | 2000-11-02 |
| US6226978B1 (en) | 2001-05-08 |
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