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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.
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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
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。
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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
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。
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公开(公告)号：US20160273550A1
公开(公告)日：2016-09-22
申请号：US15037770
申请日：2014-12-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven Clarkson , Richard B. Bergethon
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.
Abstract translation: 一种用于燃气涡轮发动机衬套的衬套组件包括具有至少两个轴向相邻段的蜂窝芯，包括前段和后段。 抗冲击层抵靠蜂窝前进段的径向内侧设置。 在耐冲击层和后段的至少一部分上限定相对基本上不间断的流动路径的径向内部层向抗冲击层和蜂窝状后段两侧延伸并径向向内延伸。
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