公开(公告)号：US20060091182A1

公开(公告)日：2006-05-04

申请号：US10977853

申请日：2004-10-29

Applicant: Steven Ivory ,  Jose Echevarria ,  Gary Lomasney ,  David Malley ,  Kevin McMahon ,  James Moor ,  Joseph Rokicki

Inventor： Steven Ivory ,  Jose Echevarria ,  Gary Lomasney ,  David Malley ,  Kevin McMahon ,  James Moor ,  Joseph Rokicki

IPC: A47J36/02

CPC classification number: F01D5/005 ,  B23K1/0018 ,  B23K1/018 ,  B23K1/206 ,  B23K2101/001 ,  B23P6/002 ,  B23P6/007 ,  C11D7/06 ,  C11D7/08 ,  C11D7/105 ,  C11D11/0041 ,  C23F1/28 ,  C23G1/08 ,  C23G1/085 ,  C23G1/086 ,  C23G1/28 ,  C23G1/32 ,  F05D2230/237 ,  Y10T29/49318

Abstract: A method of repairing a braze joint and the resulting joint includes removing an unsuitable portion of a first joining material in a joint between a first member and a second member of an aerospace assembly and cleaning the joint. A stripping solution is used to remove the unsuitable portion of the first joining material. A first cleaning solution is used to clean the joint, and the joint is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material moves into a void left by the removed unsuitable portion from the removal step to form a new joint between the first member and the second member that includes the remaining first joining material and the second joining material.

Abstract translation: 修复钎焊接头和所得到的接头的方法包括去除在航空航天组件的第一构件和第二构件之间的接头中的第一接合材料的不适当部分并清洁接头。 剥离溶液用于去除第一接合材料的不合适部分。 使用第一清洁溶液来清洁接头，并且使用第二清洁溶液进一步清洁接头。 在重新启动步骤期间，第二接合材料由移除的不适合部分移动到留下的空隙中，以在第一构件和第二构件之间形成包括剩余的第一接合材料和第二接合材料的新接头。

公开(公告)号：US20050263220A1

公开(公告)日：2005-12-01

申请号：US10858365

申请日：2004-06-01

Applicant: David Malley ,  Carl Kelly ,  Robert Schaefer

Inventor： David Malley ,  Carl Kelly ,  Robert Schaefer

IPC: B23P6/00 ,  C21D9/50 ,  C21D6/02

CPC classification number: B23P6/005 ,  C21D9/50

Abstract: Systems and methods for repairing Thermo-Span® gas turbine engine components are described herein. Embodiments of these methods minimize post-weld residual stresses in a weld repaired Thermo-Span® component by solution heat treating the component by heating the component to about 2000° F.±25° F., holding the component at about 2000° F.±25° F. for about one hour; and cooling the component to below about 700° F. at a rate equivalent to cooling in air; and precipitation heat treating the component by heating the component to about 1325° F.±25° F., holding the component at about 1325° F.±25° F. for about 8 hours, cooling the component to about 1150° F.±25° F. at a maximum rate of about 100° F./hour, holding the component at about 1150° F.±25° F. for about 8 hours, and cooling the component at a predetermined cooling rate. Dimensions of the fully-machined and weld repaired component are maintained during solution heat treating and precipitation heat treating via custom designed furnace tools.

Abstract translation: 本文描述了用于修理Thermo-Span（R）燃气涡轮发动机部件的系统和方法。 这些方法的实施例通过将组件加热至约2000°F±25°F，将组件保持在约2000°，通过对部件进行固溶热处理，使焊接修补的Thermo-Span（R）部件中的焊后残余应力最小化 F.±25°F约1小时; 并以相当于在空气中冷却的速率将组分冷却至约700°F以下; 并通过将组分加热至约1325°F±25°F进行沉淀热处理，将组分保持在约1325°F±25°F下约8小时，将组分冷却至约1150°F ±25°F，最大速率为约100°F /小时，将组分保持在约1150°F±25°F约8小时，并以预定的冷却速率冷却组分。 在通过定制设计的炉具的固溶热处理和沉淀热处理期间，维持完全加工和焊接修补部件的尺寸。

公开(公告)号：US20070119528A1

公开(公告)日：2007-05-31

申请号：US11289199

申请日：2005-11-28

Applicant: David Malley

Inventor： David Malley

IPC: C22C19/05 ,  C22F1/10

CPC classification number: C22C19/056

Abstract: For a group of nickel-based superalloys, improved properties have been obtained by stabilizing at increased temperature for a reduced time relative to prior art specifications. In particular, improved creep properties have been obtained with a one-hour 1800° F. stabilization relative to a prior art four-hour 1500° F. stabilization.

Abstract translation: 对于一组镍基超级合金，通过在升高的温度下稳定，相对于现有技术规格而言减少的时间已经获得了改进的性能。 特别地，相对于现有技术的四小时1500°F稳定化，1800小时1800华氏度的稳定性获得了改进的蠕变性能。