公开(公告)号：JP2013155736A

公开(公告)日：2013-08-15

申请号：JP2013012763

申请日：2013-01-28

Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

Inventor： ROBERTSON JR THOMAS J ,  WEBB SCOT A ,  CLARKSON STEVEN C

IPC: F02C7/00 ,  F01D25/00 ,  F02K3/06

CPC classification number: F01D11/16 ,  F01D11/122 ,  F01D11/127 ,  F01D21/045 ,  F02K3/06 ,  F05D2250/75 ,  Y02T50/672

Abstract: PROBLEM TO BE SOLVED: To provide a turbine engine fan case assembly.SOLUTION: A turbine engine fan case assembly includes a structural case and a liner assembly. A radially adapted mounting mechanism connects the liner assembly to the structural case. The mounting mechanism includes a circumferentially-distributed plurality of longitudinally elongated and radially outwardly open channels mounted to the liner assembly. The mounting mechanism further includes an associated plurality of inwardly-projecting projecting edge parts mounted to the structural case. Each of the projecting edge parts is accommodated in a corresponding channel, respectively.

Abstract translation: 要解决的问题：提供一种涡轮发动机风扇壳体组件。解决方案：涡轮发动机风扇壳体组件包括结构壳体和衬套组件。 径向适配的安装机构将衬套组件连接到结构壳体。 安装机构包括周向分布的多个纵向细长和径向向外开放的通道，其安装到衬套组件上。 安装机构还包括安装到结构壳体上的相关联的多个向内突出的突出边缘部分。 每个突出边缘部分分别容纳在相应的通道中。

公开(公告)号：WO2015069335A3

公开(公告)日：2015-07-23

申请号：PCT/US2014049576

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE M ,  HANSEN JAMES O ,  KIREJCZYK MARIA C ,  WEBB SCOT A ,  MEYER JESSE C ,  GATES BRANDON A ,  BERGETHON RICHARD B ,  MORDEN MICHAEL A

IPC: F01D5/14 ,  F02K3/06 ,  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: 翼型构件（100）包括沿着翼型构件的翼型（102）的至少一部分的基板（120）。 护套（122）具有接收基底的一部分（160）的通道（144）。 稀松布（200）位于基材和护套之间。 间隔件（220）位于护套和基底之间，并具有多个在间隔开的部分之间具有间隙的间隔开的部分（232,234）。

公开(公告)号：WO2014204546A3

公开(公告)日：2015-03-05

申请号：PCT/US2014032300

申请日：2014-03-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WARD THOMAS W ,  WEBB SCOT A

IPC: F02C7/047 ,  F01D25/02

CPC classification number: F02C7/047 ,  F01D25/02 ,  F05D2300/5024 ,  Y02T50/672

Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的除冰系统包括与前部组件相邻的前组件和后组件。 前组件和后组件中的一个可相对于另一组件旋转以在所述前组件和后组件之间产生一定量的空气摩擦。

公开(公告)号：EP3044419A4

公开(公告)日：2017-04-19

申请号：EP14843035

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE M ,  HANSEN JAMES O ,  MEYER JESSE C ,  MARCIN JR JOHN J ,  SHEMENSKI ROBERT M ,  WEBB SCOT A ,  GATES BRANDON A ,  MORDEN MICHAEL A

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12 ,  F04D29/38 ,  F04D29/58

CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F04D29/023 ,  F04D29/324 ,  F04D29/325 ,  F04D29/644 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/433 ,  F05D2300/614

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 plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.

Abstract translation: 包括沿翼型件的翼型件（102）的至少一部分具有基底（120）的翼型件（100）。 护套（122）具有容纳衬底的一部分（160）的通道（144）。 多个分离的间隔物（320; 380; 400）位于护套和衬底之间并且在间隔件之间具有多个间隙。

公开(公告)号：EP3090127A4

公开(公告)日：2017-10-25

申请号：EP14875792

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE ,  HANSEN JAMES O ,  MEYER JESSE C ,  KIREJCZYK MARIA C ,  WEBB SCOT A ,  GATES BRANDON A ,  BERGETHON RICHARD B

IPC: F01D5/12 ,  B32B5/02 ,  B32B7/12 ,  B32B15/14 ,  B32B15/20 ,  F01D5/14 ,  F01D5/22 ,  F01D5/28 ,  F02C7/00 ,  F04D29/02 ,  F04D29/32 ,  F04D29/38

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.

公开(公告)号：EP3060777A4

公开(公告)日：2017-06-21

申请号：EP14855237

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KLING COLIN J ,  WEBB SCOT A ,  MCPHAIL JAMES J

IPC: B64C11/14 ,  F01D5/06

CPC classification number: B64C11/14 ,  F01D5/066 ,  F02C3/04 ,  F05D2220/36 ,  F05D2230/23 ,  Y02T50/672

Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

Abstract translation: 公开了一种燃气涡轮发动机的风扇组件，用于制造用于燃气涡轮发动机的风扇组件的方法以及燃气涡轮发动机。 燃气涡轮发动机的风扇组件可以包括旋转器部分，旋转器部分的尾部的风扇轮毂部分以及它们之间的接头。 所述风扇组件还可包括用于内部支撑所述旋转器的支撑环，所述支撑环包括面向所述风扇轮毂的第一部分和在所述接头处连接至所述旋转器的第二部分，其中所述第二部分与所述接头之间的连接是 绑定连接。

公开(公告)号：EP3044417A4

公开(公告)日：2016-12-14

申请号：EP14860986

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE M ,  HANSEN JAMES O ,  KIREJCZYK MARIA C ,  WEBB SCOT A ,  MEYER JESSE C ,  GATES BRANDON A ,  BERGETHON RICHARD B ,  MORDEN MICHAEL A

IPC: F01D5/14 ,  F02K3/06 ,  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.

公开(公告)号：EP2971517A4

公开(公告)日：2016-11-09

申请号：EP13878508

申请日：2013-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WARD THOMAS W ,  WEBB SCOT A ,  HOGATE ISAAC JON

IPC: F01D15/10 ,  F01D25/02 ,  F02C7/047

CPC classification number: F02C7/047 ,  F01D15/10 ,  F01D25/02 ,  F02C7/32 ,  F05D2220/76 ,  H02K7/1823 ,  H05B3/0014 ,  H05B3/06