公开(公告)号：US20160312627A1

公开(公告)日：2016-10-27

申请号：US15103077

申请日：2014-12-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lei Chen ,  Zhiwei Yang ,  William J. Brindley ,  Monika D. Kinstler ,  Bruce R. Saxton

IPC: F01D5/28 ,  F01D25/00 ,  C22C19/05 ,  C25D5/50 ,  C25D5/40 ,  C25D7/00 ,  F01D9/02 ,  C25D3/12

CPC classification number: F01D5/288 ,  C22C19/058 ,  C25D3/12 ,  C25D3/562 ,  C25D3/665 ,  C25D5/18 ,  C25D5/40 ,  C25D5/50 ,  C25D7/00 ,  F01D9/02 ,  F01D25/005 ,  F01D25/007 ,  F05D2220/30 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/132 ,  F05D2300/175 ,  F05D2300/177

Abstract: A nickel-chromium (Ni—Cr) alloy and a method for electrodepositing the Ni—Cr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by re-building wall thickness with the Ni—Cr alloy including from 2 to 50 wt % chromium balanced with nickel. The turbine component coated with the Ni—Cr alloy is heat-treated at a high temperature to homogenize composition of the alloy to mimic the base alloy and to restore materials lost during repair of the turbine component.

Abstract translation: 描述了一种镍 - 铬（Ni-Cr）合金和用于将Ni-Cr合金电沉积在涡轮发动机部件上用于尺寸恢复发动机部件的方法。 发动机部件通过Ni-Cr合金重新构造壁厚恢复，包括与镍平衡的2至50重量％的铬。 涂覆有Ni-Cr合金的涡轮机部件在高温下进行热处理，以使合金的组成均匀化，以模拟基体合金，并恢复在涡轮部件修复期间损失的材料。

公开(公告)号：US20180085867A1

公开(公告)日：2018-03-29

申请号：US15276021

申请日：2016-09-26

Applicant: United Technologies Corporation

Inventor： Wangen Lin ,  William J. Brindley ,  Bruce R. Saxton ,  Steven Ivory

IPC: B23P6/00 ,  B23K20/12 ,  B23K20/22 ,  B23P6/04 ,  C21D9/50 ,  C22F1/18 ,  C22F1/10 ,  C22F1/04 ,  B23K37/00

CPC classification number: B23P6/002 ,  B23K20/12 ,  B23K20/122 ,  B23K20/22 ,  B23K37/00 ,  B23K2101/001 ,  B23P6/005 ,  B23P6/045 ,  C21D9/50 ,  C22F1/04 ,  C22F1/10 ,  C22F1/183 ,  F01D5/005 ,  F01D25/243 ,  F05D2230/239 ,  F05D2230/80 ,  Y02T50/672

Abstract: A method is provided that involves a component including a first fastener aperture that extends through the component. During the method, the component is machined to enlarge the first fastener aperture to provide an enlarged aperture. The component is friction plug welded to plug the enlarged aperture with friction plug welded material. A second fastener aperture is machined in the friction plug welded material, where the second fastener aperture extends through the component.

公开(公告)号：US20160230557A1

公开(公告)日：2016-08-11

申请号：US14617628

申请日：2015-02-09

Applicant: United Technologies Corporation

Inventor： Mark T. Ucasz ,  Bruce R. Saxton ,  Daniel A. Bales ,  William J. Brindley

IPC: F01D5/00 ,  C23C14/32 ,  F01D5/28

CPC classification number: F01D5/005 ,  C23C14/325 ,  F01D5/288 ,  F05D2230/10 ,  F05D2230/313 ,  F05D2230/80 ,  F05D2230/90

Abstract: Aspects of the disclosure are directed to a servicing of an airfoil of an aircraft engine. A first portion of a first bondcoat layer may be removed from the airfoil while leaving a second portion of the first bondcoat layer intact on the airfoil. A second bondcoat layer may be applied to the airfoil using a coating technique subsequent to the removal of the first portion of the first bondcoat layer.

Abstract translation: 本公开的方面涉及飞机发动机的翼型件的维修。 第一粘合涂层的第一部分可以从机翼上去除，同时在翼型件上完整地留下第一粘结涂层的第二部分。 第二粘合涂层可以在除去第一粘结涂层的第一部分之后使用涂覆技术施加到翼型件。