公开(公告)号：EP3058179A4

公开(公告)日：2017-07-05

申请号：EP14853033

申请日：2014-09-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE ,  GRAVES WILLIAM R

IPC: F01D5/30 ,  F01D5/32 ,  F01D21/04

CPC classification number: F01D5/323 ,  F01D5/3007 ,  F01D21/045 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2300/506

Abstract: A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness. A second layer of a second material is mechanically attached to the first layer. The second material has a second stiffness different from the first stiffness.

Abstract translation: 一种用于燃气涡轮发动机的轮毂和叶片组件的隔离件，该隔离件包括形成具有细长形状的隔离件主体的第一材料的第一层。 第一种材料具有第一硬度。 第二材料的第二层机械附着到第一层。 第二材料具有不同于第一硬度的第二硬度。

公开(公告)号：EP2935795A4

公开(公告)日：2015-12-23

申请号：EP13865899

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DROZDENKO LEE ,  GRAVES WILLIAM R

IPC: F01D5/30 ,  F01D21/04 ,  F02C7/00

CPC classification number: F01D5/3007 ,  F01D5/3092 ,  F01D21/045

公开(公告)号：EP2867473A4

公开(公告)日：2015-08-19

申请号：EP13886385

申请日：2013-06-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DEAL JAMES L ,  SCHIRRA JOHN J ,  DROZDENKO LEE ,  GRAVES WILLIAM R ,  HANSEN JAMES O ,  WEISSE MICHAEL A ,  WATSON THOMAS J

IPC: F01D5/14 ,  B23P15/04 ,  F01D5/28 ,  F04D29/38

CPC classification number: F01D5/288 ,  F01D5/147 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/124 ,  F05D2300/174 ,  Y02T50/672

Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt% and about 3.0 wt% of lithium.