公开(公告)号：US20200095171A1

公开(公告)日：2020-03-26

申请号：US16214533

申请日：2018-12-10

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Kevin Seymour ,  Agnieszka M. Wusatowska-Sarnek ,  Sergei F. Burlatsky

IPC: C04B35/622 ,  C04B35/10 ,  C04B35/46 ,  C04B35/12 ,  C04B35/48 ,  C04B35/185 ,  F01D25/00

Abstract: A method for coating a substrate with a ceramic coating, includes the steps of: applying a bond coat material to a surface of a substrate to form a bond coat on the surface; and applying a ceramic coat over the bond coat, wherein the step of applying the bond coat material produces a bond coat having a lower elastic modulus as compared to a conventionally applied bond coat.

公开(公告)号：US20160068282A1

公开(公告)日：2016-03-10

申请号：US14786838

申请日：2014-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Agnieszka M. Wusatowska-Sarnek ,  James S. Guest ,  Larry G. Housefield ,  Enrique E. Montero ,  Ruston M. Moore

IPC: B65B1/06 ,  B65B1/48 ,  B65B1/22 ,  B22F3/00 ,  B22F1/00

CPC classification number: B65B1/06 ,  B22F1/00 ,  B22F3/004 ,  B22F2999/00 ,  B65B1/22 ,  B65B1/26 ,  B65B1/48 ,  B65B39/12 ,  B22F2202/01 ,  B22F2201/02

Abstract: A powder filling method includes introducing a tube into a can so that the lower end of the tube is near the bottom of the can. The powder in the can is introduced through the tube. The proximity of the lower end of the tube to the powder is controlled by retracting the tube as the powder fills the can.

Abstract translation: 粉末填充方法包括将管引入罐中，使得管的下端靠近罐的底部。 罐中的粉末通过管引入。 管的下端与粉末的接近度通过在粉末填充罐时缩回管来控制。

公开(公告)号：US10662799B2

公开(公告)日：2020-05-26

申请号：US15887494

申请日：2018-02-02

Applicant: United Technologies Corporation

Inventor： Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D5/28 ,  F01D11/00 ,  C23C8/68 ,  F01D25/00

Abstract: A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

公开(公告)号：US20190242267A1

公开(公告)日：2019-08-08

申请号：US15887494

申请日：2018-02-02

Applicant: United Technologies Corporation

Inventor： Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D5/28 ,  F01D25/00 ,  C23C8/68

Abstract: A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

公开(公告)号：US20180128284A1

公开(公告)日：2018-05-10

申请号：US15344638

申请日：2016-11-07

Applicant: United Technologies Corporation

Inventor： Agnieszka M. Wusatowska-Sarnek ,  Sergei F. Burlatsky ,  David Ulrich Furrer ,  J. Michael McQuade

IPC: F04D29/38 ,  F04D29/16 ,  F04D29/52 ,  F04D29/02 ,  F01D11/12 ,  F01D5/28

CPC classification number: F04D29/388 ,  F01D5/20 ,  F01D5/288 ,  F01D11/122 ,  F04D29/023 ,  F04D29/164 ,  F04D29/327 ,  F04D29/526 ,  F05D2220/32 ,  F05D2230/53 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2300/609 ,  F05D2300/611

Abstract: A rotor for a turbomachine is provided which includes a hub; and a plurality of blades extending radially from the hub, the plurality of blades comprising a first subset of blades having first tips and an abrasive coating on the first tips, and a second subset of blades having second tips with no abrasive coating on the second tips, wherein a radius (R2) of the first subset of blades, including thickness of the abrasive coating, is greater than a radius (R1) of the second subset of blades, and wherein a base radius (R) of the first subset of blades, not including thickness of the abrasive coating, is less than the radius (R1) of the second subset of blades.

公开(公告)号：US11209010B2

公开(公告)日：2021-12-28

申请号：US15430783

申请日：2017-02-13

Applicant: United Technologies Corporation

Inventor： Pantcho P. Stoyanov ,  Agnieszka M. Wusatowska-Sarnek ,  Thomas D. Kasprow ,  David Ulrich Furrer ,  Sergei F. Burlatsky

IPC: C23C28/00 ,  F04D29/16 ,  C23C28/02 ,  F01D5/28 ,  F01D11/12 ,  C23C4/12 ,  C23C24/04 ,  F04D29/52

Abstract: A multilayer abradable coating includes at least one first abradable layer; and at least one second abradable layer, wherein the first abradable layer and the second abradable layer have different properties related to erosion resistance.

公开(公告)号：US20170362952A1

公开(公告)日：2017-12-21

申请号：US15616545

申请日：2017-06-07

Applicant: United Technologies Corporation

Inventor： Pantcho Stoyanov ,  Christopher W. Strock ,  Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D25/24 ,  F01D5/02 ,  F01D21/00

CPC classification number: F01D11/122 ,  F01D5/02 ,  F01D11/001 ,  F01D21/003 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2260/80 ,  F05D2300/516 ,  Y02T50/672

Abstract: An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

公开(公告)号：US10544698B2

公开(公告)日：2020-01-28

申请号：US15616545

申请日：2017-06-07

Applicant: United Technologies Corporation

Inventor： Pantcho Stoyanov ,  Christopher W. Strock ,  Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D5/02 ,  F01D21/00 ,  F01D25/24

Abstract: An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

公开(公告)号：US20190242261A1

公开(公告)日：2019-08-08

申请号：US15920878

申请日：2018-03-14

Applicant: United Technologies Corporation

Inventor： Agnieszka M. Wusatowska-Sarnek

IPC: F01D5/28 ,  F01D11/12

Abstract: A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

公开(公告)号：US20170306783A1

公开(公告)日：2017-10-26

申请号：US15137524

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Daniel Anthony Grande ,  Agnieszka M. Wusatowska-Sarnek ,  Thomas D. Kasprow ,  David Ulrich Furrer ,  Sergei F. Burlatsky

IPC: F01D11/12 ,  C23C4/073 ,  C23C4/134 ,  F01D25/00 ,  C23C4/126 ,  C23C4/131

CPC classification number: F01D11/122 ,  C23C4/073 ,  C23C4/126 ,  C23C4/131 ,  C23C4/134 ,  F01D11/125 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/2282 ,  F05D2300/514 ,  F05D2300/6032 ,  F05D2300/615

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.