公开(公告)号：US12083625B2

公开(公告)日：2024-09-10

申请号：US16839753

申请日：2020-04-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xiaomei Fang ,  Christopher J. Hertel ,  John D. Riehl ,  John W. Connell ,  Frank L. Palmieri ,  John W. Hopkins

IPC: B23K26/359 ,  B23K26/0622 ,  B23K103/04

CPC classification number: B23K26/359 ,  B23K26/0622 ,  B23K2103/05

Abstract: Methods and systems for the laser surface treatment on stainless steel alloys and nickel alloys may include a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the substrate along the predefined geometric pattern. The pulsed laser beam may have a laser power between 0.1 W and 100 W, single pulse fluence 1 mJ/mm2 and 1025 mJ/mm2 and a laser speed between 25.4 cm/s and 127 cm/s. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 0.1-1 μm, an open pore distance of 0.05-1 μm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain open pore structures and promote adhesive bond performance.

公开(公告)号：US20190331127A1

公开(公告)日：2019-10-31

申请号：US15966109

申请日：2018-04-30

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  John D. Riehl

IPC: F04D29/38 ,  F04D29/02 ,  F04D29/32 ,  F02K3/06 ,  B32B5/02 ,  B32B27/12 ,  B32B27/38

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip and a root section in a spanwise direction. A composite core defines the root section and a portion of the airfoil section. First and second skins extend along opposed sides of the composite core. 12. A method of forming a composite airfoil is also disclosed.

公开(公告)号：US20190024256A1

公开(公告)日：2019-01-24

申请号：US15656262

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： John D. Riehl ,  William Bogue ,  Gary A. Wigell ,  John Harner

IPC: C25D11/16 ,  C25D11/24 ,  F01D5/28

Abstract: A method of repairing an erosion coating coupled to a substrate, wherein the coating comprises an anodization layer on the substrate, a bond primer layer on the anodization layer, a corrosion-resistant primer on the bond primer, and an erosion coating on the corrosion-resistant primer the method comprising abrading an erosion coating; abrading a corrosion-resistant primer; creating an abraded surface comprising a bond primer over an anodization layer coupled to the substrate, chemically etching the anodization layer; abrading the bond primer; applying an anodization layer to the substrate; applying a bond primer layer over the anodization layer; applying a corrosion-resistant layer over the bond primer layer; and applying an erosion coating layer over the corrosion-resistant layer.

公开(公告)号：US20180051705A1

公开(公告)日：2018-02-22

申请号：US15243066

申请日：2016-08-22

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  Rajiv A. Naik ,  John D. Riehl

IPC: F04D29/02 ,  F04D29/38 ,  F04D29/52 ,  F04D29/54

CPC classification number: F04D29/023 ,  B29C70/24 ,  B29L2031/08 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D9/041 ,  F01D25/162 ,  F01D25/24 ,  F04D29/38 ,  F04D29/522 ,  F04D29/542 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2240/30 ,  F05D2300/6034

Abstract: A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.

公开(公告)号：US20170292402A1

公开(公告)日：2017-10-12

申请号：US15095235

申请日：2016-04-11

Applicant: United Technologies Corporation

Inventor： Alan C. Barron ,  James Masloski ,  John D. Riehl

IPC: F01D25/00 ,  B05D7/00 ,  F01D25/24

CPC classification number: F01D25/005 ,  B05D7/50 ,  C08J5/12 ,  C08J2379/08 ,  F01D5/282 ,  F01D5/288 ,  F01D25/24 ,  F05D2250/63 ,  F05D2300/2102 ,  F05D2300/2106 ,  F05D2300/211 ,  F05D2300/601 ,  F05D2300/6012 ,  F05D2300/603 ,  F05D2300/614

Abstract: A modified organic matrix composite having a thermal barrier coating comprising a substrate comprising an organic matrix composite; a roughness layer coupled to the substrate; a bonding layer coupled to the roughness layer opposite the substrate; and a thermal barrier coating coupled to the bonding layer opposite the roughness layer.

公开(公告)号：US11346363B2

公开(公告)日：2022-05-31

申请号：US15966109

申请日：2018-04-30

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  John D. Riehl

IPC: F04D29/38 ,  B32B5/02 ,  B32B27/12 ,  B32B27/38 ,  F02K3/06 ,  F04D29/02 ,  F04D29/32 ,  B29C70/48 ,  B29K63/00 ,  B29K307/04 ,  B29L31/08

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip and a root section in a spanwise direction. A composite core defines the root section and a portion of the airfoil section. First and second skins extend along opposed sides of the composite core. 12. A method of forming a composite airfoil is also disclosed.

公开(公告)号：US11260421B2

公开(公告)日：2022-03-01

申请号：US15656275

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： John Harner ,  John D. Riehl ,  William Bogue ,  Gary A. Wigell

IPC: B05D3/00 ,  B05D3/10 ,  B05D3/12 ,  B05D5/00 ,  B05D7/00 ,  F01D5/00 ,  F01D5/28 ,  C23C18/12 ,  C25D11/24

Abstract: A method of repairing an erosion coating coupled to a substrate, wherein the coating comprises an anodization layer on the substrate, a bond primer layer on the anodization layer, a corrosion-resistant primer on the bond primer, and an erosion coating on the corrosion-resistant primer. The method comprises abrading an erosion coating; abrading a corrosion-resistant primer; creating an abraded surface comprising a bond primer over an anodization layer coupled to the substrate, applying a sol-gel adhesion promoter layer to said abraded surface; applying a corrosion-resistant layer over the sol-gel adhesion promoter layer; and applying an erosion coating layer over the corrosion-resistant layer.

公开(公告)号：US11156104B2

公开(公告)日：2021-10-26

申请号：US16255976

申请日：2019-01-24

Applicant: United Technologies Corporation

Inventor： Jesse C. Meyer ,  Joseph Jalowka ,  John D. Riehl ,  Raymond P. Martina ,  James O. Hansen

IPC: F01D5/28 ,  C09J5/02 ,  C09J5/04 ,  C09J5/06 ,  B32B15/04 ,  C22C21/00

Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.

公开(公告)号：US10717109B2

公开(公告)日：2020-07-21

申请号：US15964998

申请日：2018-04-27

Applicant: United Technologies Corporation

Inventor： Rajiv A. Naik ,  John D. Riehl ,  Larry Foster

IPC: B05D3/12 ,  B32B7/08 ,  B32B27/08 ,  B29C70/08

Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.

公开(公告)号：US20190153878A1

公开(公告)日：2019-05-23

申请号：US16255976

申请日：2019-01-24

Applicant: United Technologies Corporation

Inventor： Jesse C. Meyer ,  Joseph Jalowka ,  John D. Riehl ,  Raymond P. Martina ,  James O. Hansen

IPC: F01D5/28 ,  C09J5/02 ,  C09J5/04 ,  C09J5/06 ,  C22C21/00 ,  B32B15/04

Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.