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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
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）。
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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.
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公开(公告)号：EP3084178A4
公开(公告)日：2016-12-28
申请号：EP14871637
申请日：2014-12-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN , BERGETHON RICHARD B
IPC: F02C7/05
CPC classification number: F04D29/526 , F01D21/045 , F02C7/045 , F02C7/05 , F02K3/06 , F04D29/325 , F04D29/38 , F05D2220/32 , F05D2220/36 , F05D2250/283 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.
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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
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.
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