CN1336265A - 带有受压整体端部带的金属制品及其制造方法 - Google Patents
带有受压整体端部带的金属制品及其制造方法 Download PDFInfo
- Publication number
- CN1336265A CN1336265A CN01124664.2A CN01124664A CN1336265A CN 1336265 A CN1336265 A CN 1336265A CN 01124664 A CN01124664 A CN 01124664A CN 1336265 A CN1336265 A CN 1336265A
- Authority
- CN
- China
- Prior art keywords
- blade
- wing blade
- compression
- band
- wing
- 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.)
- Granted
Links
Images
Classifications
-
- 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
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P9/00—Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings; Features of such surfaces not otherwise provided for, their treatment being unspecified
- B23P9/02—Treating or finishing by applying pressure, e.g. knurling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B39/00—Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zone; Accessories therefor
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D7/00—Modifying the physical properties of iron or steel by deformation
- C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
- C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D2221/00—Treating localised areas of an article
- C21D2221/01—End parts (e.g. leading, trailing end)
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D2221/00—Treating localised areas of an article
- C21D2221/02—Edge parts
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Clamps And Clips (AREA)
Abstract
一种带有受压整体端部带的金属制品(10)及其制造方法,该金属制品包括一个本体(12)和一个与本体(12)形成一体的端部(18),端部(18)包括一个基本上在整个端部(18)上形成的金属材料带(20),所述带(20)处于压应力状态,且压应力大于本体的应力。上述制品(10)可以是燃气轮机的叶片,其中,本体(12)是叶片的翼形叶身,带(20)设置在翼形叶身(12)径向向外的叶尖(18)上。本发明还提供一种形成所述带(20)的方法,其包括在端部(18)上进行滚压变形,直到基本上在整个端部(18)的带(20)上形成所需的压应力为止。
Description
技术领域
本发明涉及一种包括一个可承受例如裂纹等损坏的整体端部或尖部的金属制品。具体的是,本发明涉及一种由金属合金制成的燃气轮机叶片等金属制品,其包括一个叶尖,该叶尖可承受在工作过程中所造成的叶尖裂缝或开裂,并可承受这种损坏从叶尖扩展到下部材料。
背景技术
发电设备例如燃气轮机包括叶片形部件,例如:叶片和叶轮,其具有一个与另外的部件相邻并置并可相对运动或转动的自由端部或尖部。这种部件包括旋转压缩机叶片和旋转涡轮机叶片,其具有一个翼形叶身(airfoil),该翼形叶身带有一个与固定壳体或横跨较窄缝隙设置的密封件相对设置的翼形叶尖。将这种缝隙设计成可限制工作流体(例如:空气和/或燃料)通过缝隙发生泄漏。
众所周知,涡轮机叶片可周期循环地进行工作,这种周期循环包括较高的转速,有时是高温。因此,除了叶片会发生热膨胀和收缩以外,在叶片的叶尖处会形成局部较高的拉伸和振动应力。这种应力发展到一定程度就会在叶尖产生裂缝或裂纹,并进一步扩展到相邻的整个叶片本体上。相对运动部件之间的摩擦会使裂缝和裂纹增大。Mannava等人(1997.4.15获得专利权)的美国专利US5620307和Prevey,III(1998.10.27获得专利权)的美国专利US5826453中就描述了上述这种情况。
Mannava等人和Prevey,III的专利公开了一种在制品的表面部位、区域或表层上形成残留压应力并将其从处理表面延伸到制品上的方法和装置。Mannava等人通过利用激光冲击喷丸处理法(LaserShockPeening)来形成这种残留压应力区,并将压应力从激光冲击喷丸处理表面延伸到翼形叶身上。Prevey,III利用低塑性抛光法(LowPlasticity Burnishing)来进行表面抛光处理。根据Prevey,III的专利附图中的数据记载,这可在部件表面的表层中形成压应力,例如在深至0.05″的地方,同时使冷加工量被限制到约小于3.5%。
发明内容
本发明就是要提供一种由金属材料制成的制品,该制品包括一个本体和一个与该本体形成一体的端部。所述端部包括一个基本上在整个端部上形成的金属材料整体带,所述带处于压应力状态,且该压应力大于本体的应力。例如,这种制品可以是一种由金属合金制成的叶片部件,该叶片部件包括一个翼形叶身,翼形叶身具有形成一体的翼形叶尖,该叶尖包括处于压应力状态的带。所述带向翼形叶身延伸到一个选定的深度,该深度由工作经验确定,并足以防止叶片工作中所带来的损坏。
本发明还提供了一种制造这种处于压应力状态的带的方法,首先,选定所述带延伸到端部或翼形叶尖中的深度,在选定的带上进行滚压变形,直到基本上在整个带上形成压应力。
附图说明
附图1是本发明燃气轮机的压缩机叶片的透视图,该叶片包括翼形叶身,该叶身带有本发明的受压叶尖带。
具体实施方式
涡轮机叶片振动会使叶片表面产生裂纹和裂缝。这种表面包括翼形叶身的边缘部分,例如:前缘、后缘和叶尖。提高叶片材料的疲劳强度可降低产生裂纹并使其扩展到叶片从而导致叶片损坏的可能性。旋转叶片的径向外叶尖承受上述类型的工作损坏,这不仅来自于工作状态过程中,而且可能来自于维修过程中与其它对应的配合部件之间的摩擦。这种工作损坏的可能深度可通过检查维修叶片的损坏来确定。在一些情况下,这种损坏的深度从叶尖向叶片的翼形叶身扩展达到约0.1″。叶尖磨损会降低材料在磨损区域的疲劳强度。邻近这种损坏发生区域的残留压应力可防止裂纹产生和/或扩展。
目前的叶片由高疲劳强度的材料制成。通常利用诸如普通喷丸处理、激光冲击喷丸处理(Mannava等人描述的)和低塑性抛光(Prevey,III描述的)这样的表面处理方法来增大材料的疲劳强度。另外,Proceedings of 5th National High Cycle Fatigue Conference(2000)中Prevey等人的论文和题为“FOD Resistance and FatigueCrank Arrest in Low Plasticity Burnished IN718”的论文都描述了涡轮机部件的高循环疲劳和各种表面增强方法的历史沿革并对其加以讨论。
根据本发明,为避免对制品端部如叶片部件的叶尖造成损坏,在其端部或尖部的大致整个横截面上设置一个材料带。该带基本上在整个带的范围内处于压应力状态,而不是仅仅在表面层或区域内,且其压应力值大于部件本体的值。在此情况下,就可避免在叶片的端部或叶尖处产生裂纹并使其扩展。对于涡轮机叶片,该带从翼形叶身的叶尖处径向延伸入翼形叶身一定的深度,从而使其可承受工作中所造成的损坏,例如,通过对已损坏进行维修的叶片进行检查来确定出上述深度可达到约0.1″。但是,所述带从翼形叶身的叶尖处延伸的径向深度小于翼形叶身中为平衡所述带中的压应力所需要的拉应力所处的位置,而上述位置是如此的高,以致于对每个特定翼形叶身结构才有的一个或多个已知振动响应模态是不利的。通常,这种不利位置的深度自叶尖起约大于翼形叶身长度的10%,例如,对于一个2″长的翼形叶身,从叶尖起的径向深度大约为0.2″。
下面将结合附图对本发明进行详细描述。图1是燃气轮机的压缩机叶片的透视图,其表示一个旋转压缩机或旋转涡轮机的叶片。压缩机叶片10包括一个翼形叶身12和一个底部14。在一些情况下,叶片通常还包括一个设置在翼形叶身12和底部14之间的平台16。翼形叶身12包括一个端部或尖部18,其与翼形叶身12的其余部分或下部本体形成一体并沿径向向外延伸。通常,燃气轮机叶片由基于Ti、Fe、Ni和Co中的至少一种的合金材料制成。例如,可从市场上购买到的这类合金包括Ti6-4合金、Ti6-2-4-2合金、A-286合金、C450合金、In718合金和Rene’95合金。
根据本发明的实施例,翼形叶身12带有叶尖18,叶尖18具有与翼形叶身12形成一体的叶片合金带20,且其残留的压应力大于与带20相邻的并与带20形成一体的翼形叶身12。带20大致在翼形叶身12的前缘22、后缘24、压力侧26和背压侧28之间的整个横截面上延伸。叶片具有雏鸟(squealer)形的叶尖,所述带在雏鸟形叶尖的整个横截面上延伸。
最好,所述带中的残留压应力处于约10ksi(每平方英寸千磅)到材料弹性极限的范围内。对于In718Ni基合金,带20中的残留压应力最好约为50-150ksi。最好,带20到翼形叶身12中的深度达到虚线30所表示的位置。每个翼形叶身中带的深度可在维修翼形叶身时对其损坏范围程度进行检查来确定,并将深度选定到足以抵抗这种工作损坏。另外,如上所述,选定的深度小于翼形叶身中为平衡所述带的压应力而需要的过大的且可能不利的残留拉应力的深度。
在现有技术中,在制品表面层中进行冷加工可将其残留压应力限定到约小于3.5%。但是,本发明的压应力带可包括大约达到材料弹性极限而不损坏所述带的冷加工。例如,对于Ni基合金,可冷加工到至少约15%,而对于Ti基合金,约为10%。
在制造叶片的过程中,在精加工之前,预制翼形叶身的压应力带深度通常大于最终的成品。这种预制的深度包括在制造过程中叶尖要修整的总深度(有时称为修整长度)以获得一定的设计裕度或公差,以及所选定的可防止工作损坏的成品的深度。
一种将带20设置于翼形叶身12上的优选方法是带的滚压冷加工变形。例如,利用单点加压或冷加工法在叶尖18处横向加工翼形叶身12,并延伸到深度30处,从而形成带20。如上所述,深度30被选定为带20到翼形叶身12中的延伸部分。然后,在整个翼形叶身作用有压力并到达深度30位置处,直到基本上在整个翼形叶身的带20中形成选定的残留压应力。Prevey,III的上述美国专利US5826453公开了一种可用于形成带20的装置。
上面结合附图对本发明的优选实施例进行了描述,应当认为,这只是示例性的,而不是限定了本发明的范围。显然,在本发明的基础上,本领域普通技术人员可作出多种的变型和改进,而这都未脱离本发明权利要求书所限定的保护范围。
Claims (19)
1.一种由金属材料制成的制品(10),所述制品(10)包括:
一个本体(12);和
一个与所述本体(12)形成一体的端部(18);
所述端部(18)包括一个基本上在整个端部(18)上形成的金属材料带(20);
所述带(20)处于压应力状态,且该压应力大于本体(12)的应力。
2.根据权利要求1所述的制品(10),其特征在于:该制品(10)呈叶片部件的形式,其中
本体(12)是叶片部件(10)的翼形叶身;且
所述端部(18)是翼形叶身(12)的叶尖。
3.根据权利要求2所述的制品(10),其特征在于,
金属材料是基于选自Ti、Fe、Ni和Co中的至少一种的合金;
带(20)沿径向向翼形叶身(12)延伸到一个通过工作经验选定以防止工作损坏的深度(30)。
4.根据权利要求3所述的制品(10),其特征在于,所述带(20)向翼形叶身(12)延伸的深度(30)小于这样的一个位置,在该位置处,翼形叶身(12)中为平衡所述带(20)中的压应力所需要的拉应力值不利于翼形叶身(12)独有的至少一种振动响应模式。
5.根据权利要求4所述的制品(10),其特征在于,所述的位置约大于翼形叶身(12)长度的10%。
6.根据权利要求3所述的制品(10),其特征在于,压应力的范围为约10ksi到金属材料的弹性极限。
7.根据权利要求6所述的制品(10),其特征在于,压应力约为50-150ksi。
8.权利要求1所述的制品(10),其特征在于,该制品为一种燃气轮机叶片部件的形式,包括:
一个金属翼形叶身(12),该翼形叶身包括前缘(22)、后缘(24)、压力侧(26)、背压侧(28)和一个在它们之间延伸的径向向外的叶尖部(18);
叶尖部(18)包括基本上在整个叶尖部(18)上形成的径向向外的带(20),所述带(20)处于压应力状态,且压应力大于翼形叶身(12)的应力。
9.根据权利要求8所述的叶片(10),其特征在于,
金属材料是基于选自Ti、Fe、Ni和Co中的至少一种的合金;以及
带(20)向翼形叶身(12)延伸到一个通过工作经验选定以防止工作损坏的深度(30)。
10.根据权利要求9所述的制品(10),其特征在于,所述带(20)向翼形叶身(12)延伸的深度(30)小于这样的一个位置,在该位置处,翼形叶身(12)中为平衡所述带(20)中的压应力所需要的拉应力值不利于翼形叶身(12)独有的至少一种振动响应模式。
11.根据权利要求10所述的制品(10),其特征在于,所述的位置约大于翼形叶身(12)长度的10%。
12.根据权利要求10所述的叶片部件(10),其特征在于,压应力的范围为约10ksi到金属材料的弹性极限。
13.根据权利要求12所述的叶片部件(10),其特征在于,压应力约为50-150ksi。
14.一种制造权利要求1所述制品(10)的方法,其包括以下步骤:
选定所述带(20)延伸到端部(18)中的深度(30);然后,
在端部(18)上进行滚压变形至所述深度(30),直到基本上在整个端部(18)上形成压应力为止。
15.根据权利要求14所述的制造叶片部件(10)的翼形叶身(12)的方法,其特征在于,
端部(18)是翼形叶身(12)的叶尖;且
所述带(20)的深度(30)通过检查在工作过程中损坏的叶片部件(10)的翼形叶身(12)来确定,且选定的深度(30)足以防止上述工作过程中的损坏。
16.根据权利要求14所述的方法,其特征在于,选定的深度(30)小于这样的一个位置,在该位置处,翼形叶身(12)中为平衡所述带(20)中的压应力所需要的拉应力值不利于翼形叶身(12)独有的至少一种振动响应模式。
17.根据权利要求16所述的方法,其特征在于,所述的位置约大于翼形叶身(12)长度的10%。
18.根据权利要求14所述的制造叶片部件(10)的翼形叶身(12)的方法,其特征在于,
金属材料是基于选自Ti、Fe、Ni和Co中的至少一种的合金;且
压应力的范围为约10ksi到金属材料的弹性极限。
19.根据权利要求18所述的方法,其特征在于,压应力约为50-150ksi。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/627,143 US6672838B1 (en) | 2000-07-27 | 2000-07-27 | Method for making a metallic article with integral end band under compression |
US09/627143 | 2000-07-27 |
Publications (2)
Publication Number | Publication Date |
---|---|
CN1336265A true CN1336265A (zh) | 2002-02-20 |
CN100519055C CN100519055C (zh) | 2009-07-29 |
Family
ID=24513365
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN01124664.2A Expired - Fee Related CN100519055C (zh) | 2000-07-27 | 2001-07-27 | 带有受压整体端部带的金属制品及其制造方法 |
Country Status (11)
Country | Link |
---|---|
US (2) | US6672838B1 (zh) |
EP (1) | EP1175956B1 (zh) |
JP (1) | JP2002155702A (zh) |
CN (1) | CN100519055C (zh) |
BR (1) | BR0103027B1 (zh) |
CA (1) | CA2353265C (zh) |
DE (1) | DE60114943T2 (zh) |
MX (1) | MXPA01007587A (zh) |
MY (1) | MY129152A (zh) |
RU (1) | RU2281402C2 (zh) |
SG (1) | SG101992A1 (zh) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10245396A1 (de) * | 2002-09-28 | 2004-04-15 | Mtu Aero Engines Gmbh | Vorrichtung und Verfahren zur Oberflächenbearbeitung von Werkstücken |
FR2871399B1 (fr) * | 2004-06-15 | 2006-09-22 | Snecma Moteurs Sa | Procede de reparation d'un element d'aube |
US7229253B2 (en) | 2004-11-30 | 2007-06-12 | General Electric Company | Fatigue-resistant components and method therefor |
US7384244B2 (en) * | 2004-12-16 | 2008-06-10 | General Electric Company | Fatigue-resistant components and method therefor |
WO2006117847A1 (ja) * | 2005-04-27 | 2006-11-09 | Hitachi, Ltd. | マイクロガスタービン |
US7217099B2 (en) * | 2005-05-24 | 2007-05-15 | General Electric Company | Coated forward stub shaft dovetail slot |
US20060280612A1 (en) * | 2005-06-09 | 2006-12-14 | Prevey Paul S Iii | Metallic article with integral end band under compression |
US7805972B2 (en) * | 2005-10-12 | 2010-10-05 | Surface Technology Holdings Ltd. | Integrally bladed rotating turbo machinery and method and apparatus for achieving the same |
US8024846B2 (en) * | 2006-01-27 | 2011-09-27 | General Electric Company | Preparation of an article surface having a surface compressive texture |
US20070281088A1 (en) * | 2006-06-02 | 2007-12-06 | United Technologies Corporation | Low plasticity burnishing of coated titanium parts |
US7530792B2 (en) | 2006-06-30 | 2009-05-12 | General Electric Company | Component of variable thickness having residual compressive stresses therein, and method therefor |
KR20080012744A (ko) * | 2006-08-03 | 2008-02-12 | 유나이티드 테크놀로지스 코포레이션 | 부식 코팅되는 부품의 코팅전 버니싱 |
US8079120B2 (en) * | 2006-12-30 | 2011-12-20 | General Electric Company | Method for determining initial burnishing parameters |
US8051565B2 (en) * | 2006-12-30 | 2011-11-08 | General Electric Company | Method for increasing fatigue notch capability of airfoils |
GB0704426D0 (en) * | 2007-03-08 | 2007-04-18 | Rolls Royce Plc | Aerofoil members for a turbomachine |
ES2343397B1 (es) * | 2008-03-07 | 2011-06-13 | GAMESA INNOVATION & TECHNOLOGY, S.L. | Una pala de aerogenerador. |
US8539659B2 (en) | 2008-04-23 | 2013-09-24 | United Technologies Corporation | Method of repairing an article |
US8753065B2 (en) * | 2012-09-27 | 2014-06-17 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
CN114292994A (zh) * | 2021-12-30 | 2022-04-08 | 西北工业大学 | 一种薄壁叶片低塑性滚压强化方法 |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB302657A (en) * | 1927-12-19 | 1929-03-07 | Gen Electric | Improvements in and relating to turbine blades |
GB1127157A (en) * | 1966-06-13 | 1968-09-11 | Orenda Ltd | Method for improving the fatigue resistance of turbine blades |
US4839245A (en) * | 1985-09-30 | 1989-06-13 | Union Carbide Corporation | Zirconium nitride coated article and method for making same |
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 |
US6215097B1 (en) * | 1994-12-22 | 2001-04-10 | General Electric Company | On the fly laser shock peening |
US5591009A (en) * | 1995-01-17 | 1997-01-07 | General Electric Company | Laser shock peened gas turbine engine fan blade edges |
US5531570A (en) * | 1995-03-06 | 1996-07-02 | General Electric Company | Distortion control for laser shock peened gas turbine engine compressor blade edges |
IL117347A (en) * | 1995-03-06 | 1999-10-28 | Gen Electric | Laser shock peened gas turbine engine compressor airfoil edges |
US5620307A (en) | 1995-03-06 | 1997-04-15 | General Electric Company | Laser shock peened gas turbine engine blade tip |
US5735044A (en) * | 1995-12-12 | 1998-04-07 | General Electric Company | Laser shock peening for gas turbine engine weld repair |
JP3728006B2 (ja) * | 1996-03-29 | 2005-12-21 | ゼネラル・エレクトリック・カンパニイ | ガスタービン機関のファンの羽根 |
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 |
US5932120A (en) * | 1997-12-18 | 1999-08-03 | General Electric Company | Laser shock peening using low energy laser |
US6005219A (en) * | 1997-12-18 | 1999-12-21 | General Electric Company | Ripstop laser shock peening |
US5951790A (en) * | 1998-06-26 | 1999-09-14 | General Electric Company | Method of monitoring and controlling laser shock peening using an in plane deflection test coupon |
JP2000087897A (ja) * | 1998-09-08 | 2000-03-28 | Hitachi Ltd | ガスタービンの圧縮機翼およびガスタービン |
-
2000
- 2000-07-27 US US09/627,143 patent/US6672838B1/en not_active Expired - Fee Related
-
2001
- 2001-07-19 CA CA002353265A patent/CA2353265C/en not_active Expired - Fee Related
- 2001-07-25 BR BRPI0103027-2A patent/BR0103027B1/pt not_active IP Right Cessation
- 2001-07-26 JP JP2001225350A patent/JP2002155702A/ja active Pending
- 2001-07-26 DE DE60114943T patent/DE60114943T2/de not_active Expired - Lifetime
- 2001-07-26 EP EP01306416A patent/EP1175956B1/en not_active Expired - Lifetime
- 2001-07-26 RU RU2001121022/06A patent/RU2281402C2/ru not_active IP Right Cessation
- 2001-07-26 MX MXPA01007587A patent/MXPA01007587A/es active IP Right Grant
- 2001-07-27 MY MYPI20013573A patent/MY129152A/en unknown
- 2001-07-27 CN CN01124664.2A patent/CN100519055C/zh not_active Expired - Fee Related
- 2001-07-27 SG SG200104540A patent/SG101992A1/en unknown
-
2003
- 2003-05-22 US US10/444,105 patent/US6893225B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CN100519055C (zh) | 2009-07-29 |
BR0103027B1 (pt) | 2010-05-04 |
EP1175956B1 (en) | 2005-11-16 |
SG101992A1 (en) | 2004-02-27 |
MXPA01007587A (es) | 2004-07-30 |
RU2281402C2 (ru) | 2006-08-10 |
CA2353265C (en) | 2008-10-21 |
US6672838B1 (en) | 2004-01-06 |
JP2002155702A (ja) | 2002-05-31 |
US20040109767A1 (en) | 2004-06-10 |
MY129152A (en) | 2007-03-30 |
US6893225B2 (en) | 2005-05-17 |
DE60114943D1 (de) | 2005-12-22 |
DE60114943T2 (de) | 2006-08-03 |
EP1175956A1 (en) | 2002-01-30 |
BR0103027A (pt) | 2002-02-26 |
CA2353265A1 (en) | 2002-01-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN1336265A (zh) | 带有受压整体端部带的金属制品及其制造方法 | |
JP5178016B2 (ja) | 表面圧縮組織を有する物体表面の作成方法 | |
US5531570A (en) | Distortion control for laser shock peened gas turbine engine compressor blade edges | |
US7805972B2 (en) | Integrally bladed rotating turbo machinery and method and apparatus for achieving the same | |
US20090313823A1 (en) | Imparting deep compressive residual stresses into a gas turbine engine airfoil peripheral repair weldment | |
JP4974106B2 (ja) | レーザショック誘起翼形部捻りの打ち消し | |
US20060147311A1 (en) | Fatigue-resistant components and method therefor | |
US5671628A (en) | Laser shock peened dies | |
KR100416012B1 (ko) | 가스터빈엔진부품및가스터빈엔진압축기블레이드 | |
RU2007120712A (ru) | Способ изготовления изделия из металлического материала, способ изготовления детали с покрытием и лопатка газотурбинного двигателя с покрытием | |
US9803258B2 (en) | Post processing of components that are laser peened | |
Telesman et al. | Effect of broaching machining parameters, residual stresses and cold work on fatigue life of Ni-based turbine disk P/M alloy at 650° C | |
US20130216391A1 (en) | Method for the production of a one-piece rotor area and one-piece rotor area | |
EP2804718B1 (en) | Method of surface treatment for dovetail in gas turbine engine fan blade | |
EP1721063B1 (de) | Strömungsmaschine und verfahren zur anpassung von stator und rotor einer strömungsmaschine | |
US20060280612A1 (en) | Metallic article with integral end band under compression | |
Rahman et al. | Effects of surface finish and treatment on the fatigue behaviour of vibrating cylinder block using frequency response approach | |
Carek | Shot peening for Ti-6Al-4V alloy compressor blades | |
Ortolano et al. | Shot peening in steam turbines | |
EDITION | SHOT PEENING | |
GB2393673A (en) | Prestressing of components | |
RU2003103736A (ru) | Способ ремонта лопаток газотурбинного двигателя |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090729 Termination date: 20160727 |
|
CF01 | Termination of patent right due to non-payment of annual fee |