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    Method for fabricating a thick Ti64 alloy article
    12.
    发明公开
    Method for fabricating a thick Ti64 alloy article 有权
    用于制造强合金Ti64制品的方法

    公开(公告)号：EP1538226A3

    公开(公告)日：2006-02-01

    申请号：EP04256461.7

    申请日：2004-10-20

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Wayte, Peter ,  Li, Ming Cheng

    IPC: C22F1/18 ,  C22C14/00 ,  C21D9/00 ,  B21K3/04

    CPC classification number: B21K3/04 ,  C21D9/00 ,  C22C14/00 ,  C22F1/183

    Abstract: A Ti-6Al-4V-0.20 (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2-1/4 inches. The forged article is heat treated by solution heat treating at a temperature of from about 50°F to about 75°F below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900°F to about 1000°F. The resulting machined gas turbine engine component has a 0.2 percent yield strength of from about 120 ksi to about 140 ksi at its centerline (54), and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about 1/2 inch below a surface (56) thereof.

    Method for inspecting a titanium-base component
    13.
    发明公开
    Method for inspecting a titanium-base component 有权
    Verfahren zurPrüfungvon Titan enthaltendenWerkstücken

    公开(公告)号：EP1498731A2

    公开(公告)日：2005-01-19

    申请号：EP04254292.8

    申请日：2004-07-16

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Wayte, Peter

    IPC: G01N33/20 ,  G01N31/00

    CPC classification number: C23F1/20 ,  F05B2260/80 ,  F05C2201/021 ,  F05C2201/0412 ,  G01N21/8803 ,  G01N21/91 ,  G01N33/20

    Abstract: A process for detecting an aluminum-based material deposited onto a titanium-based gas turbine engine component during engine operation is disclosed. The process comprises immersing at least a portion of the titanium-based component, which has been subjected to engine operation, into an acid solution to form an etched component. The acid solution comprises sodium fluoride, sulphuric acid and water. The etched component may then be removed from the solution and visually inspected for dark areas in contrast to light areas, the dark areas indicating deposited aluminum-based material.

    Abstract translation: 公开了一种用于在发动机操作期间检测沉积在钛基燃气涡轮发动机部件上的铝基材料的方法。 该方法包括将经过发动机操作的钛基组分的至少一部分浸入酸溶液中以形成蚀刻组分。 酸溶液包含氟化钠，硫酸和水。 然后可以从溶液中除去蚀刻的组分，并与光区域相比目视检查暗区，暗区表示沉积的铝基材料。

    Turbine blade wear protection system with multilayer shim
    14.
    发明公开
    Turbine blade wear protection system with multilayer shim 失效
    带多层垫片的涡轮叶片磨损保护系统

    公开(公告)号：EP0495586A1

    公开(公告)日：1992-07-22

    申请号：EP92300200.0

    申请日：1992-01-09

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Herzner, Frederick Charles ,  Wayte, Peter ,  Juenger, Jerome Allen

    IPC: F01D5/28 ,  F01D5/30

    CPC classification number: F01D5/3007 ,  F01D5/28 ,  F01D5/3092 ,  Y10S416/50

    Abstract: A metallic reinforced shim (40) is attached to the dovetail of turbine or compressor blades (18). The shim reduces frictionally induced wear damage to the rotor (16). In one form, a single ply shim (40) reinforced with a metallic doubler (44) has an anti-fretting layer deposited on the shim face contacting the dovetail slot pressure face, and a doubler layer fastened to the anti-fretting layer in the non-contacting regions to prevent slippage of the shim on the blade. In another form, a multi-layer shim (40) has two layers (50,52) interposed between the blade dovetail and the disk dovetail slot, with the layers treated so that they do not readily slip relative to the titanium pieces, but do slip relative to each other. The shim is also reinforced with a metallic doubler (66). Fretting is confined to the consumable shim, and therefore the disk dovetail slot and the mating blade dovetails are not subject to surface degradation with corresponding reduction in fatigue capability.

    Abstract translation: 金属强化垫片（40）连接到涡轮机或压缩机叶片（18）的燕尾上。 垫片减少摩擦引起的转子（16）的磨损损坏。 在一种形式中，用金属倍增器（44）增强的单层垫片（40）具有沉积在与燕尾槽压力面接触的垫片面上的抗微动磨损层，以及紧固到第二层中的抗微动磨蚀层 非接触区域以防止叶片上的垫片滑动。 在另一种形式中，多层垫片（​​40）具有介于刀片燕尾和盘燕尾槽之间的两层（50,52），其中这些层被处理成使得它们不容易相对于钛片滑动，但是 相对于彼此滑动。 垫片还用一个金属加倍器（66）加固。 微动局限于消耗性垫片，因此盘式燕尾槽和配合叶片式燕尾槽不会受到表面退化的影响，从而相应降低疲劳能力。

    Method for fabricating a thick Ti64 alloy article
    17.
    发明公开
    Method for fabricating a thick Ti64 alloy article 有权
    Methodefürdas Fabrizieren eines starken Legierung Ti64 Artikels

    公开(公告)号：EP1538226A2

    公开(公告)日：2005-06-08

    申请号：EP04256461.7

    申请日：2004-10-20

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Wayte, Peter ,  Li, Ming Cheng

    IPC: C21D9/00

    CPC classification number: B21K3/04 ,  C21D9/00 ,  C22C14/00 ,  C22F1/183

    Abstract: A Ti-6Al-4V-0.20 (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2-1/4 inches. The forged article is heat treated by solution heat treating at a temperature of from about 50°F to about 75°F below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900°F to about 1000°F. The resulting machined gas turbine engine component has a 0.2 percent yield strength of from about 120 ksi to about 140 ksi at its centerline (54), and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about 1/2 inch below a surface (56) thereof.

    Abstract translation: 通过锻造工件来制造具有厚度大于2-1 / 4英寸的厚度的锻造燃气涡轮发动机部件，制造Ti-6Al-4V-0.20（Ti64）锻造制品。 通过在合金的β转子温度以下约50°F〜约75°F的温度下进行固溶热处理，对该锻造品进行热处理，然后将燃气轮机引擎部件水淬至室温， 燃气涡轮发动机部件，温度为约900°F至约1000°F。 所得到的机加工的燃气涡轮发动机部件在其中心线（54）处具有约120ksi至约140ksi的0.2％屈服强度，并且在约1/1的位置处具有约160ksi至约175ksi的0.2％屈服强度， 在其表面（56）下方2英寸。

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