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    Method for repairing a damaged blade of a BLISK
    2.
    发明申请
    Method for repairing a damaged blade of a BLISK 有权
    修复BLISK损坏刀片的方法

    公开(公告)号：US20050274008A1

    公开(公告)日：2005-12-15

    申请号：US10853050

    申请日：2004-05-25

    Applicant: Peter Wayte ,  Thomas Broderick

    Inventor： Peter Wayte ,  Thomas Broderick

    IPC: B23P6/00 ,  B23P19/04 ,  F01D5/34

    CPC classification number: B23P6/007 ,  F01D5/34 ,  Y10T29/49318 ,  Y10T29/49732 ,  Y10T29/49737 ,  Y10T29/49742 ,  Y10T29/49746

    Abstract: A BLISK having a damaged blade, with a repair region that has a thickness less than a specified thickness as a result of damage during manufacture or prior service, is repaired by depositing repair metal onto the repair region to increase its thickness to greater than its specified thickness dimension. Only the repair region is stress relieved by heating the repair region to a stress-relieving temperature of from about 1150° F. to about 1250° F. for a time of at least about 1 hour. The intentional manipulation of microstructure in only the thinner airfoil sections allows multiple repairs, which are not possible in the thicker sections of the BLISK. An alpha-case thickness of repair metal, preferably of at least about 0.0002 inches of repair metal, is removed from a surface of the repair region.

    Abstract translation: 具有损坏的叶片的BLISK，其具有由于在制造或事先服务期间损坏而具有小于指定厚度的修复区域，通过将修复金属沉积到修复区域上来将其厚度增加到大于其指定值 厚度尺寸。 只有修复区域通过将修复区域加热至约1150°F至约1250°F的应力消除温度至少约1小时来减轻应力。 只有更薄的翼型部分有意操纵微结构才允许多次维修，这在BLISK的较厚部分是不可能的。 修复金属的α壳厚度，优选为至少约0.0002英寸的修复金属，从修复区域的表面去除。

    Method for fabricating a thick Ti64 alloy article to have a higher surface yield and tensile strengths and a lower centerline yield and tensile strengths
    4.
    发明申请
    Method for fabricating a thick Ti64 alloy article to have a higher surface yield and tensile strengths and a lower centerline yield and tensile strengths 失效
    用于制造厚Ti64合金制品以具有更高的表面产量和拉伸强度以及较低的中心线屈服和拉伸强度的方法

    公开(公告)号：US20050087272A1

    公开(公告)日：2005-04-28

    申请号：US10692985

    申请日：2003-10-24

    Applicant: Peter Wayte ,  Ming Li

    Inventor： Peter Wayte ,  Ming Li

    IPC: B21K3/04 ,  B44C1/17 ,  C21D9/00 ,  C22F1/18

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

    Abstract: A Ti-6Al-4V-0.2O (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 2¼ 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, and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about ½ inch below a surface thereof.

    Abstract translation: 通过锻造工件来制造Ti-6Al-4V-0.2O（Ti64）锻造制品，以制造具有厚度大于2¼英寸的厚度的锻造燃气涡轮发动机部件。 通过在合金的β转子温度以下的约50°F至约75°F的温度下通过固溶热处理对锻造制品进行热处理，然后将燃气涡轮发动机部件水淬至室温，之后 在约900°F至约1000°F的温度下老化燃气涡轮发动机部件。所得机加工的燃气涡轮发动机部件在其中心线处具有约120ksi至约140ksi的0.2％屈服强度， 在其表面下方约1/2英寸处的屈服强度为约160ksi至约175ksi的0.2％屈服强度。

    Wear protection system for turbine engine rotor and blade
    5.
    发明授权
    Wear protection system for turbine engine rotor and blade 失效
    涡轮发动机转子和叶片的磨损保护系统

    公开(公告)号：US5240375A

    公开(公告)日：1993-08-31

    申请号：US819245

    申请日：1992-01-10

    Applicant: Peter Wayte

    Inventor： Peter Wayte

    IPC: F01D5/28 ,  F01D5/30

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

    Abstract: An improved type wear protection system for a turbine engine rotor and blade, in which a multilayer clad shim is interposed between a dovetail portion of a blade and the dovetail slot portion of a rotor, is described. The shim, preferably comprised of surface layers of phosphor bronze and a center layer of austenitic stainless steel, is especially effective in preventing fretting damage to titanium engine components.

    Abstract translation: 描述了一种用于涡轮发动机转子和叶片的改进的型式磨损保护系统，其中将多层包覆垫片插入在叶片的燕尾部分和转子的燕尾槽部分之间。 优选由磷青铜的表面层和奥氏体不锈钢的中心层构成的垫片特别有效地防止对钛发动机部件的微动损坏。

    Turbine blade wear protection system with multilayer shim
    6.
    发明授权
    Turbine blade wear protection system with multilayer shim 失效
    涡轮叶片磨损保护系统与多层SHIM

    公开(公告)号：US5160243A

    公开(公告)日：1992-11-03

    申请号：US641230

    申请日：1991-01-15

    Applicant: Fredrick C. Herzner ,  Jerome A. Juenger ,  Peter Wayte

    Inventor： Fredrick C. Herzner ,  Jerome A. Juenger ,  Peter Wayte

    IPC: F01D5/28 ,  F01D5/30

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

    Abstract: A metallic reinforced shim is attached to the dovetail of turbine or compressor blades. The shim reduces frictionally induced wear damage to the rotor. In one form, a single ply shim reinforced with a metallic doubler 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 has two layers 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. 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.

    Method for fabricating a thick Ti64 alloy article to have a higher surface yield and tensile strengths and a lower centerline yield and tensile strengths
    7.
    发明授权
    Method for fabricating a thick Ti64 alloy article to have a higher surface yield and tensile strengths and a lower centerline yield and tensile strengths 失效
    用于制造厚Ti64合金制品以具有更高的表面产量和拉伸强度以及较低的中心线屈服和拉伸强度的方法

    公开(公告)号：US07481898B2

    公开(公告)日：2009-01-27

    申请号：US10692985

    申请日：2003-10-24

    Applicant: Peter Wayte ,  Ming Cheng Li

    Inventor： Peter Wayte ,  Ming Cheng Li

    IPC: C22F1/18

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

    Abstract: A Ti-6Al-4V-0.2O (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 2¼ 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, and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about ½ inch below a surface thereof.

    Abstract translation: 通过锻造工件来制造Ti-6Al-4V-0.2O（Ti64）锻造制品，以制造具有厚度大于2¼英寸的厚度的锻造燃气涡轮发动机部件。 通过在合金的β转子温度以下的约50°F至约75°F的温度下通过固溶热处理对锻造制品进行热处理，然后将燃气涡轮发动机部件水淬至室温，之后 在约900°F至约1000°F的温度下老化燃气涡轮发动机部件。所得机加工的燃气涡轮发动机部件在其中心线处具有约120ksi至约140ksi的0.2％屈服强度， 在其表面下方约1/2英寸处的屈服强度为约160ksi至约175ksi的0.2％屈服强度。

    Method for inspecting a titanium-based component
    9.
    发明授权
    Method for inspecting a titanium-based component 有权
    检测钛基成分的方法

    公开(公告)号：US07097783B2

    公开(公告)日：2006-08-29

    申请号：US10622304

    申请日：2003-07-17

    Applicant: Peter Wayte

    Inventor： Peter Wayte

    IPC: C23F1/00

    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: 公开了一种在发动机运转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至少一部分钛基组分浸入酸溶液中以形成蚀刻组分。 酸溶液包括氟化钠，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。

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