CN107848204B - 用于制造包括整合有小的壁的凹部状末端的叶片的方法 - Google Patents

用于制造包括整合有小的壁的凹部状末端的叶片的方法 Download PDF

Info

Publication number
CN107848204B
CN107848204B CN201680038370.1A CN201680038370A CN107848204B CN 107848204 B CN107848204 B CN 107848204B CN 201680038370 A CN201680038370 A CN 201680038370A CN 107848204 B CN107848204 B CN 107848204B
Authority
CN
China
Prior art keywords
tip
blade
surface wall
concave
recess
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201680038370.1A
Other languages
English (en)
Other versions
CN107848204A (zh
Inventor
马修·让·卢克·沃勒布雷特
科拉列·盖拉尔
帕特里克·埃米利安·保罗·埃米尔·胡彻
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=54329695&utm_source=***_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=CN107848204(B) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of CN107848204A publication Critical patent/CN107848204A/zh
Application granted granted Critical
Publication of CN107848204B publication Critical patent/CN107848204B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/25—Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
    • 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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
    • B29C64/10—Processes of additive manufacturing
    • B29C64/141—Processes of additive manufacturing using only solid materials
    • B29C64/153—Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
    • B29C64/10—Processes of additive manufacturing
    • B29C64/188—Processes of additive manufacturing involving additional operations performed on the added layers, e.g. smoothing, grinding or thickness control
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F2005/005—Article surface comprising protrusions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/10—Working turbine blades or nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)

Abstract

本发明涉及一种用于制造涡轮发动机叶片(16)的方法，该涡轮发动机叶片包括彼此分隔的拱内表面壁(17)和拱外表面壁(18)，该叶片(16)包括末端，该末端具有使拱内表面壁(17)和拱外表面壁(18)在该末端的区域中聚合在一起的封闭壁，以限定出位于叶片的末端处的凹部状形状的末端的底部(23)，该方法包括使用限定出凹部状形状的末端的型芯实施的模制步骤。根据本发明，具有通过激光直接增材制造(CLAD)方法对凹部状末端的底部(23)添加金属的步骤，以将材料沉积到凹部状末端的底部上，以在该凹部状末端中形成被其底部(23)支承的内部隔壁(28)。

Description

用于制造包括整合有小的壁的凹部状末端的叶片的方法
技术领域
本发明涉及涡轮发动机(诸如例如为涡轮喷气发动机或涡轮螺旋桨发动机)类型的航空器发动机的制造。
背景技术
在图1中被标记为1的这种发动机中，空气进入到入口套管2中，以在被分为中央主流和包围主流的次级流之前穿过包括一系列旋转叶片3的风机。
主流在到达燃烧室7之前被涡轮4和涡轮6压缩，在这之后，该主流膨胀，在被释放产生推力之前穿过涡轮8。次级流被风机直接推动以产生额外的推力。
每个涡轮8均包括一系列的叶片，该一系列的叶片被径向地定向并且围绕旋转轴线AX均匀地分隔开，该旋转轴线被包围组件的外部壳体9支撑。
通过使在燃烧室的上游采集并进入叶片的基部的空气在每个叶片中流通来确保对叶片进行冷却，该空气通过贯穿这些叶片的壁的孔被释放。
在图2中被标记为11的这种轮叶包括根部P和叶片12，旋转本体通过该根部进行附接，该叶片被该根部P支撑，根部和叶片被平台部13分隔开。
叶片12具有非平直的、围绕轴线EV旋曲的形状，该轴线被称为叶展轴线，该叶展轴线垂直于轴线AX。该叶片包括基部，该叶片通过该基部被连接到平台部13并且该叶片径向延伸直至末端S，该末端为该叶片的自由端部。叶片的两个主壁为其拱内表面壁14和拱外表面壁，该拱内表面壁与拱外表面壁彼此分隔开。
轮叶11的末端S包括封闭壁，该封闭壁垂直于方向EV并连接拱内表面壁和拱外表面壁。在图2中不可见的该封闭壁相对于拱内表面壁的和拱外表面壁的自由端部朝向轴线AX缩进。该封闭壁与这些边缘沿与轴线AX相对的方向共同限定出一凹的、敞开的部段，该部段被称为凹部状末端，该凹部状末端位于叶片的顶部处，换言之，位于该叶片的末端处。
通过下述方式以对金属材料进行模制来制造这种叶片：使用尤其是包括第一型芯和第二型芯的型芯，以一方面限定出叶片本体的内部空间，以及另一方面限定出凹部状末端的内部空间。这两个型芯沿着叶展方向EV彼此分隔开一小的距离。
提高性能需要优化对凹部状末端的冷却，例如通过设置被凹部状末端底部支撑的小的隔壁或内部隔壁。这些隔壁或肋状件目的是在于优化凹部状末端中的空气动力，以尤其通过限制从拱内表面到拱外表面的泄漏来改善叶片的末端处的冷却。
添加这种肋状件或隔壁使第二型芯的研制显著地复杂化。实际上，使用型芯箱，换言之，使用两段式模具来制造该叶片，该两段式模具是通过沿脱模方向将一个型芯从另一型芯移除来打开的，该脱模方向在正交于叶片的叶展轴线的法向平面中延伸。
该脱模方向的限制性是制造必要性的结果，意思是限定出用于凹部状末端的底部的肋状件的狭槽不能被设置在第二型芯的端部处。这种狭槽将构成切边(undercut)区域，该切边区域使得在制造该叶片的期间不能够对第二型芯进行脱模，原因是该狭槽的定向与脱模方向不同。
一种可能性在于以数个陶瓷部段制造第二型芯，这数个陶瓷部段彼此在顶部处通过粘合被组装。这样使得制造显著地复杂化，并且因此使废品率趋于增大，并且进一步地趋于导致型芯无法具有足够的坚固性。
本发明的目的在于提供一种制造方法，该制造方法使得能够在凹部状末端处生产出各种各样的内部形状，而不会在废品率方面产生不利因素。
发明内容
为此，本发明目的在于一种用于制造涡轮发动机叶片的方法，该涡轮发动机叶片包括彼此分隔的拱内表面壁和拱外表面壁，该叶片包括末端，该末端具有使拱内表面壁和拱外表面壁在该末端的区域中聚合在一起的封闭壁，以限定出位于叶片的末端处的凹部状形状的末端的底部，该方法包括使用限定出凹部状形状的末端的型芯实施的模制步骤，其特征在于，该方法包括通过增材制造对凹部状末端的底部添加金属的步骤，该步骤通过下述方式实施：尤其通过沉积金属粉末来添加金属，以使材料沉积在凹部状末端的底部上，以在该凹部状末端中构成被其底部支承的内部隔壁。
根据本发明，通常用于完全构成部件的几何形状的增材制造方法在本文中被用于完成由铸造制成的部件。使用这种解决方案，可在凹部状末端的底部上构成任意的隔壁形状，而不会影响模制操作或影响待使用的型芯的形状。
可使用不同的增材制造方法，例如通常涉及商标CLAD的激光直接增材制造方法、通常涉及首字母缩略词LMD的被称为激光金属沉积的方法、通常涉及首字母缩略词DMD的被称为直接金属沉积的方法或者通常涉及首字母缩略词DLMD的被称为激光直接金属沉积的方法。
本发明目的还在于一种由此限定的方法，该方法包括在添加材料的步骤之后的机加工步骤，该机加工步骤使用诸如对沉积的材料进行电熔蚀的机加工方法之类的方法。
本发明目的还在于一种由此限定的方法，其中，材料被沉积成从拱内表面壁的边缘延伸至拱外表面壁的边缘。
本发明还涉及一种使用由此限定的方法得到的涡轮发动机叶片。
本发明还涉及一种包括由此限定的叶片的涡轮发动机。
附图说明
已被限定的图1为以侧面横截面的形式示出的双流涡轮喷气发动机的概要视图；
已被限定的图2为喷气发动机叶片的概要视图；
图3为铸造制成的叶片凹部状末端的局部透视图；
图4为在本发明中使用以将材料添加到叶片凹部状末端的底部的方法的示意性图示；
图5为根据本发明的凹部状末端的局部透视图，材料已被沉积在该凹部状末端的底部，该被沉积的材料由于机加工操作而被设置为隔壁的形状；
图6为根据本发明的包括隔壁的叶片凹部状末端的局部透视图，该隔壁是通过对由机加工得到的材料进行沉积而得到的。
具体实施方式
如在图1中可见的，诸如由铸造制成的叶片16包括拱内表面壁17和拱外表面壁18，该拱内表面壁和拱外表面壁大致沿该叶片的叶展方向EV延伸，并且其被标记为19和21的顶部边缘限定出该叶片16的末端。
这些拱内表面壁17和拱外表面壁18彼此分隔，同时，一方面在叶片的被标记为22的前缘处，另一方面在附图中未示出的叶片的后缘处，该拱内表面壁和拱外表面壁相互连接，该前缘和后缘这两个边缘几乎平行于叶展方向EV延伸。
这些壁在叶片末端处由被称为封闭壁的壁再次相互连接，该封闭壁被标记为23，该封闭壁垂直于叶展方向延伸，同时该封闭壁沿着叶展方向以一定的高度远离边缘19和21的末端。因此，边缘19和21延伸超过其所包围的封闭壁，使得该边缘与该封闭壁限定出叶片末端的凹部状末端24，该边缘构成该凹部状末端的边缘，封闭壁构成该凹部状末端的底部。
本发明的基本原理是使用被称为增材制造方法的方法来将材料添加到诸如由铸造制成的叶片的凹部状末端的底部，以在该凹部状末端中形成内部隔壁。所使用的方法是通过激光束来熔融金属粉末并呈接续的层进行沉积的方法。也可考虑其它的金属沉积方法。
通常指的是商标CLAD(即激光直接增材制造方法)的这种方法在于使用设备26来产生激光束27，以将由喷嘴31添加的一种或数种金属粉末29熔融在基质上，以接续地构成金属材料的沉积层32，该基质在这里是凹部状末端24的底部23。该喷嘴为同轴的喷嘴，其能够实施将金属粉末均匀地喷注通过激光束。
使用该方法，被激光熔融的粉末在表面上构成了均匀的和密实的沉积物或支承该粉末的层，在过程期间该表面或层自身也被熔融。因为尤其在喷嘴与基质之间不存在接触，所以本方法免于磨损和划伤。本方法从始至终地通过惰性气体来保护接续的沉积物或叠层，以免于氧化问题。
该方法使得能够通过以一定的精度对准添加材料的位置来进行沉积。如果有必要，还可以使用两种不同的金属添加物来根据高度而产生比例变化的合金。这使得能够优化不同的方面，例如质量、与基质的粘附性(换言之，稀释度和多孔性)以及耐磨性、磨耗性、膨胀度或其它的特性。
通常，所沉积的材料是根据基质来选择的，以具有合适的机械稳定性、耐磨性以及与基质的相容性，该材料尤其在稀释度和多孔性方面是合适的。
如在图1中可见的，由铸造制成的叶片凹部状末端半成品包括平的底部23，并且根据本发明，内部隔壁以下述方式形成在该平的底部上：按照CLAD方法添加材料，之后对由此添加的材料进行机加工，以给予该材料以对应于预定的标准的表面条件和标注尺寸(rating)。
如在图5中可见的，通过CLAD方法添加的材料按照待生产的隔壁的轨迹和形状被沉积，以构成材料添加部25，该材料添加部具有对应于待得到的隔壁的形状的总体形状。如在图5中示出的，所添加的材料构成了沉积部，考虑到涉及完成的隔壁的几何尺寸限定而得到的公差，该沉积部可能相对较粗糙。这些尺寸公差是由叶片凹部状末端在运行时所必须符合的空气动力学限制规定的。因此，在图5中被标记为25的金属沉积部构成了将形成隔壁的半成品材料。
该沉积部之后被机加工，以构成图6中示出的实际最终的隔壁，在图6中该隔壁被标记为28。可根据由首字母缩略词EDM(意指电火花加工(Electrical DischargeMachining))已知的方法、通过电熔蚀来实施该机加工。还可通过钻具或相似类型的切削工具来确保该机加工，这使得能够实施形状修整，从而使得能够构成这种隔壁28。
本发明被限定为通过以激光束熔融粉末从而沉积接续的层的方式来使用增材制造方法，但也可使用其它的方法。特别地，还可考虑SWET方法，其意指升高的温度下的超容许熔接(Superallow Welding at Elevated Temperature)。
总体而言，根据本发明的方法因此使得能够在不对在制造该叶片时发生的模制过程增加任何额外的限制的情况下制造一种叶片，该叶片在其凹部状末端处包括可具有任何类型的形状的小的壁。

Claims (5)

1.用于制造涡轮发动机叶片(16)的方法，所述涡轮发动机叶片包括彼此分隔的拱内表面壁(17)和拱外表面壁(18)，该叶片(16)包括末端，所述末端具有使所述拱内表面壁(17)和所述拱外表面壁(18)在该末端的区域中聚合在一起的封闭壁，以限定出位于所述叶片的末端处的凹部状形状的末端(24)的底部(23)，所述方法包括使用限定出所述凹部状形状的末端的型芯实施的模制步骤，其特征在于，所述方法包括使用增材制造方法对凹部状末端的底部(23)添加金属的步骤，所述步骤通过下述方式实施：通过将金属粉末沉积到所述凹部状末端的底部上来添加金属材料(25)，以在该凹部状末端中构成被底部(23)支承的内部隔壁(25，28)。
2.根据权利要求1所述的方法，所述方法包括在添加材料的步骤之后的机加工步骤，所述机加工步骤使用对所沉积的材料(25)进行电熔蚀的机加工方法。
3.根据权利要求1所述的方法，其中，所述材料(25)被沉积成从所述拱内表面壁(17)的边缘(19)延伸至所述拱外表面壁(18)的边缘(21)。
4.涡轮发动机叶片，所述涡轮发动机叶片是使用根据权利要求1所述的方法得到的。
5.涡轮发动机，所述涡轮发动机包括根据权利要求4所述的叶片。
CN201680038370.1A 2015-06-29 2016-06-27 用于制造包括整合有小的壁的凹部状末端的叶片的方法 Active CN107848204B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1556065A FR3037974B1 (fr) 2015-06-29 2015-06-29 Procede de fabrication d'une aube comportant une baignoire integrant un muret
FR1556065 2015-06-29
PCT/FR2016/051580 WO2017001751A1 (fr) 2015-06-29 2016-06-27 Procede de fabrication d'une aube comportant une baignoire integrant un muret

Publications (2)

Publication Number Publication Date
CN107848204A CN107848204A (zh) 2018-03-27
CN107848204B true CN107848204B (zh) 2020-05-05

Family

ID=54329695

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201680038370.1A Active CN107848204B (zh) 2015-06-29 2016-06-27 用于制造包括整合有小的壁的凹部状末端的叶片的方法

Country Status (5)

Country Link
US (1) US11925986B2 (zh)
EP (1) EP3313597B1 (zh)
CN (1) CN107848204B (zh)
FR (1) FR3037974B1 (zh)
WO (1) WO2017001751A1 (zh)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3037830B1 (fr) 2015-06-29 2024-02-16 Snecma Ensemble de moulage d'une aube de turbomachine, comprenant une portion en relief de grande section
FR3048374B1 (fr) 2016-03-01 2018-04-06 Snecma Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un conduit de depoussierage traversant une cavite de part en part
US11154956B2 (en) 2017-02-22 2021-10-26 General Electric Company Method of repairing turbine component using ultra-thin plate
US10702958B2 (en) 2017-02-22 2020-07-07 General Electric Company Method of manufacturing turbine airfoil and tip component thereof using ceramic core with witness feature
US20180238173A1 (en) * 2017-02-22 2018-08-23 General Electric Company Method of manufacturing turbine airfoil and tip component thereof
US10610933B2 (en) * 2017-02-22 2020-04-07 General Electric Company Method of manufacturing turbine airfoil with open tip casting and tip component thereof
US10870159B2 (en) 2017-11-02 2020-12-22 Hamilton Sunstrand Corporation Electrical discharge machining system including in-situ tool electrode
FR3079551B1 (fr) * 2018-03-29 2020-04-24 Safran Helicopter Engines Aube de distributeur de turbine comportant une paroi interne de refroidissement issue de fabrication additive
US20190360541A1 (en) * 2018-05-23 2019-11-28 General Electric Company Additively Manufactured Brake Rotor

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1629449A (zh) * 2003-12-16 2005-06-22 通用电气公司 涡轮叶片的经频率调节的销组
EP2639405A1 (en) * 2012-03-14 2013-09-18 Honeywell International Inc. Turbine blade tip cooling

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5738491A (en) * 1997-01-03 1998-04-14 General Electric Company Conduction blade tip
US7282681B2 (en) * 2005-05-05 2007-10-16 General Electric Company Microwave fabrication of airfoil tips
US8500396B2 (en) * 2006-08-21 2013-08-06 General Electric Company Cascade tip baffle airfoil
US8512003B2 (en) * 2006-08-21 2013-08-20 General Electric Company Tip ramp turbine blade
US20080317597A1 (en) * 2007-06-25 2008-12-25 General Electric Company Domed tip cap and related method
US8348612B2 (en) * 2008-01-10 2013-01-08 General Electric Company Turbine blade tip shroud
US20100200189A1 (en) * 2009-02-12 2010-08-12 General Electric Company Method of fabricating turbine airfoils and tip structures therefor
US9312066B2 (en) * 2012-01-09 2016-04-12 Apple Inc. Magnetic shape optimization
US9334742B2 (en) * 2012-10-05 2016-05-10 General Electric Company Rotor blade and method for cooling the rotor blade
US20150034266A1 (en) * 2013-08-01 2015-02-05 Siemens Energy, Inc. Building and repair of hollow components
US10436039B2 (en) * 2013-11-11 2019-10-08 United Technologies Corporation Gas turbine engine turbine blade tip cooling
DE102014106178A1 (de) * 2014-05-02 2015-11-05 Ask Chemicals Gmbh Verfahren zum schichtweisen Aufbau von Körpern umfassend feuerfesten Formgrundstoff und Resole und Formen oder Kerne hergestellt nach diesem Verfahren

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1629449A (zh) * 2003-12-16 2005-06-22 通用电气公司 涡轮叶片的经频率调节的销组
EP2639405A1 (en) * 2012-03-14 2013-09-18 Honeywell International Inc. Turbine blade tip cooling

Also Published As

Publication number Publication date
FR3037974A1 (fr) 2016-12-30
CN107848204A (zh) 2018-03-27
FR3037974B1 (fr) 2017-07-21
US20180193920A1 (en) 2018-07-12
EP3313597B1 (fr) 2020-06-17
EP3313597A1 (fr) 2018-05-02
US11925986B2 (en) 2024-03-12
WO2017001751A1 (fr) 2017-01-05

Similar Documents

Publication Publication Date Title
CN107848204B (zh) 用于制造包括整合有小的壁的凹部状末端的叶片的方法
EP2841703B1 (en) Gas turbine engine airfoil geometries and cores for manufacturing process
US10934865B2 (en) Cooled single walled blisk for gas turbine engine
EP2841701A1 (en) Gas turbine engine airfoil impingement cooling
US11220918B2 (en) Gas turbine component with cooling aperture having shaped inlet and method of forming the same
US10766065B2 (en) Method and assembly for a multiple component core assembly
US11230929B2 (en) Turbine component with dust tolerant cooling system
CN110735665B (zh) 具有可调节冷却构造的翼型件
US20160017724A1 (en) Variable thickness trailing edge cavity and method of making
US11541452B2 (en) Manufacturing method and tooling for ceramic cores
JP2000199402A (ja) 先端を切断した面取り部を持つタ―ビン動翼
US20210172336A1 (en) Turbine vane with dust tolerant cooling system
EP3184198B1 (en) Method and assembly for forming components having internal passages using a jacketed core
US20150202702A1 (en) Gas turbine engine cast structure method for finishing
EP3354368A1 (en) A ceramic core for an investment casting process
CN116568455A (zh) 包括凹槽状顶端下方的腔体的高压涡轮轮叶

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant