公开(公告)号：US10138732B2

公开(公告)日：2018-11-27

申请号：US15194028

申请日：2016-06-27

Applicant: United Technologies Corporation

Inventor： Brian K. Holland

IPC: B32B38/10 ,  F01D5/00 ,  F01D5/14 ,  F04D29/32 ,  F04D29/38 ,  B23P15/02 ,  B23P15/04 ,  B32B43/00

Abstract: Aspects of the disclosure are directed to milling a nose of a first shield of a blade to leave at least one strip of the first shield coupled to a blade body, subsequent to the milling, applying a cryogenic technique to the blade to weaken a bond between the first shield and the blade body, and subsequent to the applying of the cryogenic technique, removing the at least one strip of the first shield from the blade body.

公开(公告)号：US20170334547A1

公开(公告)日：2017-11-23

申请号：US15162104

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian K. Holland

IPC: B64C11/14 ,  F04D29/32 ,  F02C7/04 ,  F04D29/38

CPC classification number: B64C11/14 ,  B29C73/10 ,  F01D5/005 ,  F01D5/3015 ,  F02C7/04 ,  F04D29/329 ,  F04D29/38 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/80 ,  F05D2300/603 ,  Y02T50/673

Abstract: A system and method for nose cone edge delamination repair is provided. A nose cone may comprise an outer skirt having an aft edge, a flange, and a pin landing. The system and method may comprise trimming the aft edge of the nose cone to form a repaired edge. A first layer of fiberglass may be placed over repaired edge. A second layer of fiber glass may be placed over the first layer and the repaired edge. The first layer and second layer may be trimmed to create a spot face to allow for lower tolerances when installing the nose cone into a gas turbine engine.

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：US10753277B2

公开(公告)日：2020-08-25

申请号：US15221207

申请日：2016-07-27

Applicant: United Technologies Corporation

Inventor： Brian K. Holland

IPC: F02C7/04 ,  B64D27/10 ,  F02K3/06 ,  F04D19/00 ,  F04D29/32

Abstract: Aspects of the disclosure are directed to an inlet cap, comprising: a first lug slot located proximate a perimeter of the inlet cap, and a second lug slot located proximate the perimeter of the inlet cap and located peripherally adjacent to the first lug slot, where the first lug slot includes a first ply, the second lug slot includes a second ply that is different from the first ply, and at least a third ply is common to the first lug slot and the second lug slot.

公开(公告)号：US10094242B2

公开(公告)日：2018-10-09

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: B29C73/04 ,  F01D25/24 ,  F02C9/00 ,  B23P6/00 ,  F01D25/00 ,  B29C73/26

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.

公开(公告)号：US20170370223A1

公开(公告)日：2017-12-28

申请号：US15194028

申请日：2016-06-27

Applicant: United Technologies Corporation

Inventor： Brian K. Holland

IPC: F01D5/00 ,  F04D29/38 ,  F01D5/14 ,  F04D29/32

CPC classification number: F01D5/005 ,  B23P15/02 ,  B23P15/04 ,  B32B38/10 ,  B32B43/006 ,  F01D5/147 ,  F04D29/324 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/10 ,  F05D2230/23 ,  F05D2230/70 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/603 ,  Y02T50/672

Abstract: Aspects of the disclosure are directed to milling a nose of a first shield of a blade to leave at least one strip of the first shield coupled to a blade body, subsequent to the milling, applying a cryogenic technique to the blade to weaken a bond between the first shield and the blade body, and subsequent to the applying of the cryogenic technique, removing the at least one strip of the first shield from the blade body.

公开(公告)号：US10434607B2

公开(公告)日：2019-10-08

申请号：US14909323

申请日：2014-07-29

Applicant: United Technologies Corporation

Inventor： Brian K. Holland ,  William Bogue ,  Jeffrey Denton

IPC: B23K31/02 ,  G01N21/94 ,  F01D5/00 ,  F02K1/78 ,  G01N21/3563 ,  G01N21/552 ,  G01N21/35

Abstract: A method of immobilizing a contaminant within a component includes identifying the contaminant. The component is thermally processed via a specific thermal cycle related to the contaminant. The specific thermal cycle is performed within an inert environment relative to a substrate. The specific thermal cycle is configured to effect a controlled evaporation of volatiles of the contaminant and a controlled coking of remaining contaminant.

公开(公告)号：US20180030892A1

公开(公告)日：2018-02-01

申请号：US15221207

申请日：2016-07-27

Applicant: United Technologies Corporation

Inventor： Brian K. Holland

IPC: F02C7/04 ,  F04D29/32 ,  F02K3/06 ,  B64D27/10 ,  F04D19/00

Abstract: Aspects of the disclosure are directed to an inlet cap, comprising: a first lug slot located proximate a perimeter of the inlet cap, and a second lug slot located proximate the perimeter of the inlet cap and located peripherally adjacent to the first lug slot, where the first lug slot includes a first ply, the second lug slot includes a second ply that is different from the first ply, and at least a third ply is common to the first lug slot and the second lug slot.

公开(公告)号：US10273830B2

公开(公告)日：2019-04-30

申请号：US14909391

申请日：2014-08-19

Applicant: United Technologies Corporation

Inventor： Brian K. Holland ,  Jeffrey Denton ,  William Bogue

IPC: F01D25/24 ,  B29C73/06 ,  F16B5/04 ,  F16B5/00 ,  F16B43/00 ,  F02C7/00 ,  F16B5/01 ,  F16B11/00 ,  B29C73/26

Abstract: An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an outer surface of the annular cylindrical portion and the flange. The multiple of spacers are operable to control a bond line thickness.

公开(公告)号：US10207792B2

公开(公告)日：2019-02-19

申请号：US15162104

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian K. Holland

IPC: B64C11/14 ,  F02C7/04 ,  F04D29/32 ,  F04D29/38 ,  B29C73/10 ,  F01D5/00 ,  F01D5/30

Abstract: A system and method for nose cone edge delamination repair is provided. A nose cone may comprise an outer skirt having an aft edge, a flange, and a pin landing. The system and method may comprise trimming the aft edge of the nose cone to form a repaired edge. A first layer of fiberglass may be placed over repaired edge. A second layer of fiber glass may be placed over the first layer and the repaired edge. The first layer and second layer may be trimmed to create a spot face to allow for lower tolerances when installing the nose cone into a gas turbine engine.