CN101117898A - 进行耐冲蚀涂覆的部件的预涂层抛光 - Google Patents
进行耐冲蚀涂覆的部件的预涂层抛光 Download PDFInfo
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Abstract
一种燃气轮机叶片具有平台。叶根自所述平台向下伸出且翼面自所述平台中延伸出。所述翼面具有前缘和后缘以及压力侧和吸力侧。所述叶片包括具有表面的基底。在所述表面的第一区下面存在压缩应力。所述第一区在位于自顶端开始的沿翼展方向的距离大于顶端至平台的跨距的50%的部位延伸遍及翼面的大部分顺气流方向的周界。涂层位于包括所述部位的所述表面上面。
Description
技术领域
本发明涉及燃气轮机。特别是,本发明涉及进行耐冲蚀涂覆的叶片。
背景技术
在现代飞行器的燃气轮机中运转的压缩机叶片常常会遭受冲蚀损伤。该损伤可能是由于吸入(例如来自于机场跑道上的)灰尘和砂子而造成的。由于存在降低性能和缩短疲劳寿命的空气动力学特征的改变,因此冲蚀损伤缩短了叶片的使用寿命。
一种用以延长叶片寿命的手段是对叶片翼面上的那些常遭受最强冲蚀作用(Erosion)的区域施涂耐冲蚀涂层例如Co-WC和NiCr-CrC。然而,这些涂层对典型地为钛基和镍基合金的叶片基底的疲劳特性具有有害影响。因此,耐冲蚀涂层仅被施涂到翼面上的那些工作应力不超过减小的叶片疲劳强度的区域上。所希望的应该是具有用于减轻所述耐冲蚀涂层对基底疲劳特性的有害影响的方法。
发明内容
本发明的一个方面涉及一种燃气轮机叶片。所述叶片具有平台。叶根自所述平台向下伸出且翼面自所述平台中延伸出。所述翼面具有前缘和后缘以及压力侧和吸力侧。所述叶片包括具有表面的基底。在所述表面的第一区下面存在压缩应力。所述第一区在位于自顶端开始的沿翼展方向的距离大于顶端至平台的跨距的50%的部位延伸遍及翼面的大部分顺气流方向的周界。涂层位于所述表面第一区的至少一部分上面,所述部分包括所述部位。
本发明的另一个方面涉及一种制造金属材料制品的方法。所述制品包括基底和耐冲蚀涂层。选择一定范围的基底区域进行抛光,从而减轻涂层的疲劳效应。在所述区域上面产生滚动形变,然后施涂涂层。
在附图和下面的说明书中对一个或更多本发明实施例的细节进行了图示和描述。通过阅读该说明书、附图和权利要求书将使本发明的其它特点、目标和优点更加明了。
附图说明
图1是叶片的视图。
图2是用于生产或重新生产叶片的第一种工艺方法的流程图。
在各个附图中使用相似的附图标号和标记表示相似的元件。
具体实施方式
图1示出了一种典型的叶片40。该叶片包括翼面42、平台44和附接叶根46。翼面包括前缘48、后缘50和在前缘与后缘之间进行延伸的压力侧52和吸力侧54。该翼面从平台外侧表面58的内侧端部56延伸至外侧端部或顶端60。叶根自平台44的下侧62向下伸出且可具有盘旋的外形轮廓(例如所谓的燕尾形或枞树形轮廓)用于把叶片40紧固到叶片盘的互补沟槽(图中未示出)上。局部跨距S为顶端60与翼面内侧端部56之间的径向距离。该跨距S沿翼面的弦长而变化。
一种典型的翼面可能会遭受一种或更多种形式的磨损和/或损伤。磨损可包括分布较广的冲蚀。损伤可包括通常位于前缘48附近或位于顶端60处的由于外物损伤(FOD)而形成的刻痕和碎屑。典型地沿翼面的外侧部分(例如沿区域66)集中发生冲蚀。典型的区域66沿着压力侧和吸力侧大致沿大部分翼面跨度从顶端60延伸至边界68。在该区域内,典型地沿翼面外侧的三分之一(即翼面最接近顶端60的三分之一部分)发生最严重的冲蚀。典型的边界68为自顶端开始的径向距离S1。典型的径向距离S1略大于沿整个弦长的距离S的50%。冲蚀损伤的实际范围受到翼面设计和发动机运行特性的影响。
为了提供抗冲蚀能力,金属叶片基底上可沿区域72设有涂层70。典型的钛基基底合金包括Ti-6Al-4V、Ti-8Al-1Mo-1V、Ti-6Al-2Sn-4Mo-2Zr、Ti-6Al-2Sn-4Mo-6Zr和Ti-5.5Al-3.5Sn-3Zr-1Nb。其它的基底包括,但不限于,不锈钢(例如17-4PH)和镍基超合金(例如718合金)。典型的涂层包括Co-WC、NiCr-CrC、Ti-N和Ti-AlN。典型的区域72沿着压力侧和吸力侧沿大部分翼面跨度从顶端60延伸至边界74。典型的边界74为自顶端开始的径向距离S2。典型的径向距离S2大于沿整个弦长的距离S的50%并且大于径向距离S1。该涂层可延伸超出受到最严重冲蚀的区域并且提供增强的防外物损伤性能。
所述涂层可对叶片结构特性(例如疲劳特性)具有有害影响。传统上,耐冲蚀涂层在叶片翼面上受到相对较低应力的区域上的应用有限。根据本发明,对叶片进行抛光从而减轻这些影响作用中的一种或更多种并且允许在更大的叶片翼面上施涂涂层。典型的抛光工艺为低塑性抛光工艺。
在美国专利5,826,453、6,672,838和6,893,225以及公布的专利申请2005-0155203中对宇航部件的低塑性抛光进行了讨论。在P.Prevéy、N.Jayaraman和R.Ravindranath在Proc.10th Nat.HCF Conf.,New Orleans,LA,Mar.8-11,2005发表的“Use of Residual Compressionin design to Improve Damage Tolerance in Ti-6Al-4V Aero EngineBlade Dovetail”和P.Prevéy、N.Jayaraman和J.Cammett在Proceedings of ICSP 9,Paris,Marne la Vallee,France,Sept.6-9,2005发表的“Overview of Low Plasticity Burnishing for mitigationof Fatigue Damage Mechanisms”中也对这种抛光在钛基部件上的应用进行了讨论。
在施涂耐冲蚀涂层之前,可沿区域80对叶片翼面进行低塑性抛光(“LPB”)。典型的区域80沿着压力侧和吸力侧沿大部分翼面从顶端60延伸至边界82。典型的边界82为自顶端开始的径向距离S3。典型的径向距离S3大于沿整个弦长的距离S的50%并且大于径向距离S1和S2。
与未进行抛光的叶片相比,所述抛光可允许所述涂层70从顶端60朝向平台44被施涂在更大的跨距上。例如,在现有技术的工艺中,S2可相对较小(例如小于径向距离S1并且小于距离S的50%)。例如,CFM56型压缩机中的叶片使用了从顶端延伸了跨距的大致30%-40%的耐冲蚀涂层,而多种其它发动机系列中的叶片根本就不使用耐冲蚀涂层。
虽然对顶端区域进行抛光是以公知的,但是本发明中的抛光特性相对于本领域的常规抛光技术而言可具有一项或更多项差异。在没有适当考虑耐冲蚀涂层而进行施涂的情况下,现有技术抛光技术可能在翼面的更小范围上进行。现有技术可能涉及从顶端延伸出的更小的径向跨距并且可能位于前缘附近更限于局部(从而针对外物损伤而不是叶片上的工作应力)。针对未经涂覆的叶片上的外物损伤(FOD)进行的所述抛光很可能比结合耐冲蚀涂层使用的抛光更深。然而,有可能将对顶端和/或前缘部分进行的更深的抛光与对多个近端和/或后缘/下游部分进行的更浅的抛光相结合。
图2示出了一种典型的抛光和涂覆工艺100。该工艺可接收干净的叶片基底。对该基底进行抛光102。使用流体滚动元件进行典型的抛光。典型的滚动元件是球体/滚珠。在上面引用的参考文献中披露了单点抛光和相对的两点卡钳抛光(opposed two-point caliperburnishing)。
典型的抛光102是在与翼面的相邻区域略微重叠的大体上要进行涂覆的整个区域上面进行的。典型的抛光较浅(即传递残余压应力不延伸穿过基底的整个厚度/深度)。一种典型的抛光将残余压应力传递到达约0.015英寸的深度区域上面(即更窄范围为0.004英寸-0.008英寸)。
对于Ti-6-4而言,该深度区域中的典型的残余应力的峰值为100-110ksi,更宽范围为90-120ksi。该范围的上端极限可受到基底强度的限制。在该深度区域下面,残余应力将会下降。这种较浅深度的应力分布可能会使部件的扭曲变形受到限制。在另一个实例中,由于材料的屈服强度更大,因此718合金中的残余应力可能会接近150ksi。
与常规工艺如喷丸硬化处理工艺相比,低塑性抛光工艺导致产生明显更小的冷作。这与当前应用特别相关。上文引用的Prevéy等的文献已表明:在暴露于高达600摄氏度的温度之后低塑性抛光工艺得到增强的疲劳特性。在考虑与在超过500摄氏度的条件下运行的压缩机叶片相关的基底加热时,这一点变得十分明显。喷丸硬化应力倾向于在中等温度下随时间而减小,由此不利于其有益效果。低塑性抛光应力与更低水平的冷作相关联,所述更低水平的冷作看来似乎在这些温度下更加稳定。因此,相对于喷丸硬化处理工艺,低塑性抛光工艺对于耐冲蚀涂层区域而言是有利的。
可以通过反复进行的破坏性试验工艺研究得到提供所需应力分布所需要的抛光参数。在一种典型的试验工艺中,可以使用一种限于局部的检查工艺(例如X射线衍射法)来算出残余应力的深度和大小分布并且可以表示出用于改变所述部位的抛光参数的需要。
在该典型的方法中,可能存在对超出通过涂覆要被覆盖的且受到抛光处理的叶片区域进行的进一步的机械处理。例如,所述方法中可包括喷丸硬化处理104。可对附接叶根46进行喷丸硬化处理。喷丸硬化处理可提供更浅但是比抛光处理具有更高峰值压应力的应力分布。
例如可采用高速氧-燃料喷涂工艺(HVOF)或其它高能热喷涂工艺,或者采用物理气相沉积(PVD)工艺施涂106涂层。
上面已对本发明的一个或更多个实施例进行了描述。然而,应该理解:可在不偏离本发明的精神和范围的情况下对本发明作出多种改进。例如,本发明可被实施作为一种变型或使用各种现有涂层、抛光、和其它技术和设备的一种变型。同样,各种边界和过渡区域可具有与上述讨论不同的性质。虽然图中示出的是被施涂到叶片翼面上,但是也可以在其它区域或其它部件上施涂耐冲蚀涂层。因此,其它实施例落入由下面的权利要求书所限定出的保护范围内。
Claims (20)
1.一种燃气轮机叶片,包括:
平台;
自所述平台向下伸出的叶根;
翼面,所述翼面具有:
前缘和后缘;和
压力侧和吸力侧,
其中所述叶片包括:
具有表面的基底;
在所述表面的第一区下面存在压缩应力,所述第一区在位于自顶端开始的沿翼展方向的距离大于顶端至平台的跨距的50%的部位延伸遍及翼面的大部分顺气流方向的周界;并且
位于所述表面第一区的至少一部分上面的涂层,所述部分包括所述部位。
2.根据权利要求1所述的叶片,其中所述第一区包括沿前缘的大部分跨距。
3.根据权利要求1所述的叶片,其中所述涂层位于大体上整个第一区上面。
4.根据权利要求1所述的叶片,其中所述第一区延伸遍及该部位外侧的大体上整个翼面。
5.根据权利要求1所述的叶片,其中所述涂层中包含Co-WC和NiCr-CrC中的至少一种。
6.根据权利要求1所述的叶片,其中所述叶片是压缩机叶片。
7.一种制造金属材料制品的方法,所述制品包括基底和耐冲蚀涂层,所述方法包括以下步骤:
选择一定范围的基底区域进行抛光,从而减轻涂层的疲劳效应;
在所述区域上面产生滚动形变;以及
施涂涂层。
8.根据权利要求7所述的方法,其中所述区域大于施涂涂层的区域。
9.根据权利要求7所述的方法,其中所述区域沿翼面延伸。
10.根据权利要求9所述的方法,其中所述区域延伸至翼面的内侧一半的位置。
11.一种生产经过涂覆的部件的方法,所述方法包括以下步骤:
对金属基底进行抛光,从而提供第一残余应力分布;并且
在所述第一表面的至少一部分上面施涂涂层。
12.根据权利要求11所述的方法,其中所述涂层中包含Co-WC和NiCr-CrC中的至少一种。
13.根据权利要求11所述的方法,其中备选的第二残余应力分布:
与第一残余应力分布相比为未经涂覆的基底提供了更大的疲劳阻力,并且
与第一残余应力分布相比为经过涂覆的基底提供了更小的疲劳阻力。
14.根据权利要求13所述的方法,其中与所述第二残余应力分布提供的残余压应力相比,所述第一残余应力分布提供了在更大区域上面遍布的残余压应力。
15.根据权利要求11所述的方法,进一步包括对基底进行喷丸硬化处理。
16.根据权利要求11所述的方法,进一步包括对基底进行喷丸硬化处理,所述喷丸硬化处理是在抛光和非覆盖之后进行的。
17.根据权利要求11所述的方法,其中所述抛光工艺是低塑性流体滚动抛光工艺。
18.根据权利要求11所述的方法,其中所述抛光包括对从叶片翼面的顶端到沿翼面跨距的内侧一半的部位的连续区域进行抛光。
19.根据权利要求18所述的方法,其中所述抛光沿所述连续区域的大部分表面区域将压缩应力传递至0.004-0.008英寸的深度。
20.根据权利要求18所述的方法,其中所述抛光沿所述连续区域的大部分表面区域将压缩应力传递至不超过0.015英寸的深度。
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EP (1) | EP1862643B1 (zh) |
JP (1) | JP2008038896A (zh) |
KR (1) | KR20080012744A (zh) |
CN (1) | CN101117898A (zh) |
CA (1) | CA2590496A1 (zh) |
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US8065898B2 (en) | 2008-07-29 | 2011-11-29 | Hamilton Sundstrand Corporation | Method and article for improved adhesion of fatigue-prone components |
DE102011007224A1 (de) * | 2011-04-12 | 2012-10-18 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren und Herstellung eines einstückigen Rotorbereiches und einstückiger Rotorbereich |
US8906181B2 (en) * | 2011-06-30 | 2014-12-09 | United Technologies Corporation | Fan blade finishing |
US9404172B2 (en) | 2012-02-22 | 2016-08-02 | Sikorsky Aircraft Corporation | Erosion and fatigue resistant blade and blade coating |
DE102012018604A1 (de) | 2012-09-20 | 2014-03-20 | Rolls-Royce Deutschland Ltd & Co Kg | Walzwerkzeugvorrichtung |
DE102012018605A1 (de) | 2012-09-20 | 2014-03-20 | Rolls-Royce Deutschland Ltd & Co Kg | Walzwerkzeugvorrichtung |
US20150107072A1 (en) * | 2013-10-22 | 2015-04-23 | Kazim Ozbaysal | Fatigue resistant turbine through bolt |
JP6246666B2 (ja) | 2014-06-11 | 2017-12-13 | 日本発條株式会社 | 積層体の製造方法 |
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US3689311A (en) * | 1970-11-06 | 1972-09-05 | Ler Son Co Inc | Method for external coating of cylindrical objects |
US4585395A (en) * | 1983-12-12 | 1986-04-29 | General Electric Company | Gas turbine engine blade |
EP0188057A1 (en) * | 1984-11-19 | 1986-07-23 | Avco Corporation | Erosion resistant coatings |
US4904528A (en) * | 1987-12-24 | 1990-02-27 | United Technologies Corporation | Coated gas turbine engine compressor components |
US5476363A (en) * | 1993-10-15 | 1995-12-19 | Charles E. Sohl | Method and apparatus for reducing stress on the tips of turbine or compressor blades |
US6095755A (en) * | 1996-11-26 | 2000-08-01 | United Technologies Corporation | Gas turbine engine airfoils having increased fatigue strength |
US5826453A (en) * | 1996-12-05 | 1998-10-27 | Lambda Research, Inc. | Burnishing method and apparatus for providing a layer of compressive residual stress in the surface of a workpiece |
CN2371342Y (zh) | 1999-06-04 | 2000-03-29 | 中国科学院金属研究所 | 一种抗腐蚀疲劳汽轮机叶轮 |
US6415486B1 (en) * | 2000-03-01 | 2002-07-09 | Surface Technology Holdings, Ltd. | Method and apparatus for providing a residual stress distribution in the surface of a part |
US6672838B1 (en) * | 2000-07-27 | 2004-01-06 | General Electric Company | Method for making a metallic article with integral end band under compression |
US6465040B2 (en) * | 2001-02-06 | 2002-10-15 | General Electric Company | Method for refurbishing a coating including a thermally grown oxide |
US7188398B2 (en) * | 2004-01-17 | 2007-03-13 | Surface Technology Holdings, Ltd. | Method for improving the magnitude of compressive stress developed in the surface of a part |
US20050158460A1 (en) * | 2004-01-21 | 2005-07-21 | Williams Christopher C. | Method for protecting new/used engine parts |
US7229253B2 (en) * | 2004-11-30 | 2007-06-12 | General Electric Company | Fatigue-resistant components and method therefor |
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CA2590496A1 (en) | 2008-02-03 |
RU2007120712A (ru) | 2008-12-10 |
EP1862643B1 (en) | 2015-07-15 |
KR20080012744A (ko) | 2008-02-12 |
SG139615A1 (en) | 2008-02-29 |
EP1862643A2 (en) | 2007-12-05 |
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