公开(公告)号：US20150240661A1

公开(公告)日：2015-08-27

申请号：US14628263

申请日：2015-02-22

Applicant: United Technologies Corporation

Inventor： Brian K. Holland ,  Michael A. Morden ,  Brandon A. Gates ,  William Bogue

IPC: F01D25/24 ,  F01D25/00 ,  B23P6/00

CPC classification number: F01D25/24 ,  B23P6/005 ,  B29C73/04 ,  B29C73/26 ,  F01D25/005 ,  F02C9/00 ,  Y02T50/672 ,  Y10T29/49318

Abstract: A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.

Abstract translation: 一种用于燃气涡轮发动机的衬板的再制造方法包括从损坏的部件移除衬套; 并用材料成型模制衬套。 用于燃气涡轮发动机的衬板包括前风扇出口壳衬里面板，其具有来自损坏的前风扇出口壳衬套板的供体衬套。 用于燃气涡轮发动机的衬板包括由包括多个层的材料装料模制的前风扇出口壳衬里面板。 层的多重中的至少一个包括不连续性。

公开(公告)号：US20140093367A1

公开(公告)日：2014-04-03

申请号：US13630822

申请日：2012-09-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael Parkin ,  Mark Quinn ,  Leland Wiegman ,  Brandon A. Gates

IPC: F03B1/00

CPC classification number: F01D5/28 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/95 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/603 ,  Y02T50/672

Abstract: An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side.

Abstract translation: 机翼包括由具有前缘，后缘，压力侧和吸力侧的第一金属制成的翼型件; 具有由第二金属制成的第一和第二侧面的护套; 第一层非导电材料粘合在第一侧面的端部的一部分和翼型体之间并且延伸超过压力侧的第一侧面的端部; 以及第二层非导电材料，粘合地在第二侧面的端部的一部分和翼型体之间延伸超过吸力侧上的第二侧面的端部。