公开(公告)号：US20140082940A1

公开(公告)日：2014-03-27

申请号：US13626929

申请日：2012-09-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven J. Feigleson ,  Dennis R. Tremblay ,  Michael E. McMahon ,  Nathan Johnson

IPC: B23P15/04

CPC classification number: B23P15/04 ,  B23P15/06 ,  F01D9/04 ,  F01D9/041 ,  F01D25/285 ,  F05D2230/60 ,  F05D2230/68 ,  F05D2230/70 ,  Y10T29/49323 ,  Y10T29/53961

Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Abstract translation: 组装涡轮机翼型阵列的示例性方法包括将部分翼型阵列固定在固定装置内，部分翼型阵列具有至少一个现有的翼型件，该翼型件在内部和外部整流罩与开放区域之间径向延伸，至少至少 一个现有的翼型已被拆除。 该方法包括相对于固定装置的基座安装定位鞍座，定位鞍座与开放区域对准，使用定位鞍座保持替换机翼，在替换机翼与内外整流罩之间的界面处施加可固化材料 并固化可固化材料，同时保持替换翼型件与内外整流罩之间的相对位置。

公开(公告)号：US09434031B2

公开(公告)日：2016-09-06

申请号：US13626929

申请日：2012-09-26

Applicant: United Technologies Corporation

Inventor： Steven J. Feigleson ,  Dennis R. Tremblay ,  Michael E. McMahon ,  Nathan Johnson

IPC: B25B27/14 ,  B23P15/04 ,  B23P15/06 ,  F01D9/04 ,  F01D25/28

CPC classification number: B23P15/04 ,  B23P15/06 ,  F01D9/04 ,  F01D9/041 ,  F01D25/285 ,  F05D2230/60 ,  F05D2230/68 ,  F05D2230/70 ,  Y10T29/49323 ,  Y10T29/53961

Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Abstract translation: 组装涡轮机翼型阵列的示例性方法包括将部分翼型阵列固定在固定装置内，部分翼型阵列具有至少一个现有的翼型件，该翼型件在内部和外部整流罩与开放区域之间径向延伸，至少至少 一个现有的翼型已被拆除。 该方法包括相对于固定装置的基座安装定位鞍座，定位鞍座与开放区域对准，使用定位鞍座保持替换机翼，在替换机翼与内外整流罩之间的界面处施加可固化材料 并固化可固化材料，同时保持替换翼型件与内外整流罩之间的相对位置。