公开(公告)号：US10982683B2

公开(公告)日：2021-04-20

申请号：US15039929

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee Drozdenko ,  James O. Hansen ,  Jesse C. Meyer ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Brandon A. Gates ,  Richard B. Bergethon

IPC: F04D29/38 ,  B32B7/12 ,  F01D5/28 ,  F01D5/14 ,  F01D5/12 ,  B32B5/02 ,  B32B15/14 ,  B32B15/20 ,  F04D29/02 ,  F04D29/32

Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

公开(公告)号：US20180202299A1

公开(公告)日：2018-07-19

申请号：US15408882

申请日：2017-01-18

Applicant: United Technologies Corporation

Inventor： James R. Murdock ,  James H. Moffitt ,  Scot A. Webb ,  Jay Thomas Abraham ,  Maria C. Kirejczyk

IPC: F01D5/28 ,  F04D29/02

CPC classification number: F01D5/28 ,  F01D5/3092 ,  F04D29/023 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/303 ,  F05D2260/95 ,  F05D2300/121 ,  F05D2300/125 ,  F05D2300/133 ,  F05D2300/1616 ,  F05D2300/50 ,  Y02T50/671

Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.

公开(公告)号：US20160215784A1

公开(公告)日：2016-07-28

申请号：US14917485

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee M. Drozdenko ,  James O. Hansen ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Jesse C. Meyer ,  Brandon A. Gates ,  Richard B. Bergethon ,  Michael A. Morden

IPC: F04D29/02 ,  F04D29/32 ,  F04D29/64 ,  F04D29/38

CPC classification number: F04D29/023 ,  F01D5/288 ,  F04D29/324 ,  F04D29/325 ,  F04D29/388 ,  F04D29/644 ,  F05D2240/303 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/6033

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.

Abstract translation: 翼型件（100）包括沿翼型件的翼型（102）的至少一部分具有基底（120）。 护套（122）具有容纳衬底的一部分（160）的通道（144）。 稀松布（200）在基材和护套之间。 间隔物（220）位于护套和衬底之间并且具有多个间隔开的部分（232,234），其间隔开间隔开的部分。

公开(公告)号：US10801515B2

公开(公告)日：2020-10-13

申请号：US16245484

申请日：2019-01-11

Applicant: United Technologies Corporation

Inventor： Lee Drozdenko ,  William R. Graves ,  Michael Li ,  Maria C. Kirejczyk

IPC: F04D29/34 ,  F04D29/32 ,  F01D21/04 ,  F01D5/30 ,  F02C3/04 ,  F02K3/06 ,  F04D29/38

Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

公开(公告)号：US20200025211A1

公开(公告)日：2020-01-23

申请号：US16245484

申请日：2019-01-11

Applicant: United Technologies Corporation

Inventor： Lee Drozdenko ,  William R. Graves ,  Michael Li ,  Maria C. Kirejczyk

IPC: F04D29/34 ,  F01D21/04 ,  F02C3/04 ,  F02K3/06 ,  F04D29/32 ,  F04D29/38 ,  F01D5/30

Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

公开(公告)号：US10400784B2

公开(公告)日：2019-09-03

申请号：US15075705

申请日：2016-03-21

Applicant: United Technologies Corporation

Inventor： Lee Drozdenko ,  William R. Graves ,  Michael Li ,  Maria C. Kirejczyk

IPC: F02C7/12 ,  F04D29/34 ,  F01D5/30 ,  F04D29/32 ,  F02C3/04 ,  F02K3/06 ,  F04D29/38 ,  F01D21/04

Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

公开(公告)号：US20170023010A1

公开(公告)日：2017-01-26

申请号：US15039929

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee Drozdenko ,  James O. Hansen ,  Jesse C. Meyer ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Brandon A. Gates ,  Richard B. Bergethon

IPC: F04D29/38 ,  B32B5/02 ,  F04D29/02 ,  B32B15/20 ,  F04D29/32 ,  B32B7/12 ,  B32B15/14

CPC classification number: F04D29/388 ,  B32B5/024 ,  B32B7/12 ,  B32B15/14 ,  B32B15/20 ,  B32B2262/101 ,  B32B2603/00 ,  F01D5/12 ,  F01D5/14 ,  F01D5/147 ,  F01D5/28 ,  F01D5/282 ,  F01D5/286 ,  F01D5/288 ,  F04D29/023 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/6012

Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

Abstract translation: 叶片包括从后缘延伸到前缘的翼型件。 翼型件包括由含铝材料形成的主体。 护套位于前缘，由含钛材料形成。 三明治位于护套和翼型体之间，夹层包括邻近护套的外部粘合剂层，中间织物层和邻近身体的内部粘合剂层。 还公开了一种燃气涡轮发动机。

公开(公告)号：US20160348689A1

公开(公告)日：2016-12-01

申请号：US15075705

申请日：2016-03-21

Applicant: United Technologies Corporation

Inventor： Lee Drozdenko ,  William R. Graves ,  Michael Ll ,  Maria C. Kirejczyk

IPC: F04D29/34 ,  F02K3/06 ,  F02C3/04 ,  F04D29/38

CPC classification number: F04D29/34 ,  F01D5/30 ,  F01D5/3007 ,  F01D21/045 ,  F02C3/04 ,  F02K3/06 ,  F04D29/322 ,  F04D29/38 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/10 ,  F05D2240/35 ,  F05D2250/241 ,  F05D2250/291 ,  F05D2250/294 ,  F05D2260/941

Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

Abstract translation: 提供了一种风扇叶片，其包括前缘，在前缘的后方延伸的附着根和形成在附接根部的表面中的沟槽。 还提供附件根。 附接根部包括前缘，在前缘的后方延伸的燕尾榫和形成在燕尾榫的表面中的沟槽。 还提供燃气涡轮发动机。 燃气涡轮发动机包括被构造成围绕轴线旋转的压缩机部分，压缩机部分的燃烧器后部和压缩机部分的涡轮部分并被构造成围绕轴线旋转。 风扇可以设置在涡轮部分的前方并且包括叶片。 叶片可以具有形成在附接根部中的沟槽。