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1.发明专利Turbofan engine, operation method of turbofan engine, and turbofan engine fan case 有权涡轮发动机，涡轮发动机的操作方法和涡轮发动机风扇
公开(公告)号：JP2013155735A
公开(公告)日：2013-08-15
申请号：JP2013012762
申请日：2013-01-28
Inventor： ROBERTSON JR THOMAS J , COSTA MARK W , SANTANA JOHAN R
CPC classification number: F01D11/18 , F01D11/125 , F01D25/26 , F05D2220/36 , F05D2230/68 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/50212 , F05D2300/603 , Y02T50/672 , Y10T29/49323 , Y10T156/10 , Y10T156/17
Abstract: PROBLEM TO BE SOLVED: To provide a turbofan engine formed by improving a reduction in engine efficiency due to a gap between a fan tip and a fan case.SOLUTION: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. The turbofan engine includes at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted on the composite structural member to permit differential thermal expansion proximate the blades.
Abstract translation: 要解决的问题：提供一种涡轮风扇发动机，其通过改善由于风扇尖端和风扇壳体之间的间隙而引起的发动机效率的降低而形成。解决方案：涡扇风扇发动机具有带有圆周阵列的风扇叶片的风扇。 风扇外壳包围风扇。 涡轮风扇发动机包括至少一个压缩机部分，燃烧器和至少一个涡轮部分。 风扇壳体包括复合结构构件和由复合结构构件包围的金属构件。 金属构件安装在复合结构构件上以允许在叶片附近的不同的热膨胀。
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2.发明专利Turbofan engine fan case cartridge, method and fixture of manufacturing the same 有权涡轮发动机风扇箱，其制造方法及其制造方法
公开(公告)号：JP2013155741A
公开(公告)日：2013-08-15
申请号：JP2013042483
申请日：2013-03-05
Inventor： ROBERTSON JR THOMAS J , COSTA MARK W , SANTANA JOHAN R
CPC classification number: F01D11/18 , F01D11/125 , F01D25/26 , F05D2220/36 , F05D2230/68 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/50212 , F05D2300/603 , Y02T50/672 , Y10T29/49323 , Y10T156/10 , Y10T156/17
Abstract: PROBLEM TO BE SOLVED: To provide a turbofan engine fan case cartridge, in which reduction of engine efficiency accompanying a gap between a distal end part of a fan and a fan case is improved.SOLUTION: A turbofan engine fan case cartridge comprising a metallic member is included. A first honeycomb has an inner diameter (ID) liner and is encircled by a front part of the metallic member. A second honeycomb is encircled by a metallic member at the back of the first honeycomb. A wear strip is encircled by the second honeycomb.
Abstract translation: 要解决的问题：提供一种涡轮风扇发动机风扇箱，其中伴随风扇的远端部分和风扇壳之间的间隙的发动机效率的降低得到改善。解决方案：一种涡轮风扇发动机风扇箱，包括金属构件 已经包括了。 第一蜂窝体具有内径（ID）衬里并且被金属构件的前部包围。 第二蜂窝体由第一蜂窝体后部的金属构件环绕。 磨损条被第二蜂窝包围。
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3.发明专利Turbine engine fan case assembly, turbine engine, and liner mounting mechanism for turbine engine fan case 有权涡轮发动机风箱组件，涡轮发动机和内燃机涡轮发动机风扇安装机构
公开(公告)号：JP2013155736A
公开(公告)日：2013-08-15
申请号：JP2013012763
申请日：2013-01-28
Inventor： ROBERTSON JR THOMAS J , WEBB SCOT A , CLARKSON STEVEN C
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。
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公开(公告)号：WO2015076882A3
公开(公告)日：2015-07-30
申请号：PCT/US2014051231
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLARKSON STEVEN C , ROBERTSON JR THOMAS J , PARKIN MICHAEL
CPC classification number: F01D25/005 , F01D11/08 , F01D21/045 , F01D25/243 , F02C7/20 , F02K3/06 , F05D2220/32 , F05D2240/12 , F05D2240/14 , F05D2300/43 , F05D2300/603 , F05D2300/614 , Y02T50/672
Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.
Abstract translation: 涡轮发动机风扇壳体（48）包括围绕轴线（500）并具有环形安装部分（310,410）的复合主体部件（300），沿着环形部分的分段聚合物部件（320,330,420,440） 安装部分，并与其一体化。
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公开(公告)号：WO2014197053A3
公开(公告)日：2015-02-19
申请号：PCT/US2014024618
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON JR THOMAS J , COSTA MARK W , WELCH DAVID A
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F01D11/125 , F05D2250/283 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/5021 , Y02T50/671
Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.
Abstract translation: 用于燃气涡轮发动机的风扇壳体的盒包括与热适应衬套部分一体化的入口声学衬垫部分。
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Patent Agency Ranking6.发明申请
公开(公告)号：WO2015147964A3
公开(公告)日：2015-11-05
申请号：PCT/US2015010717
申请日：2015-01-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON JR THOMAS J
CPC classification number: F01D25/005 , B22F3/1055 , B22F5/04 , B22F7/08 , B22F2999/00 , B29C45/14819 , B29C70/68 , B29K2705/00 , B29L2031/082 , B33Y10/00 , B33Y30/00 , B33Y80/00 , F01D5/147 , F01D9/041 , F01D17/162 , F05D2220/32 , F05D2240/12 , F05D2250/11 , F05D2250/75 , F05D2300/43 , F05D2300/436 , F05D2300/44 , F05D2300/603 , Y02P10/295
Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的部件包括由塑料形成的翼型体。 加强部分具有由金属材料形成并且延伸到翼型中的腹板。 还公开了一种燃气涡轮发动机，以及形成用于燃气轮机的部件的方法。
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公开(公告)号：SG11201404102PA
公开(公告)日：2014-10-30
申请号：SG11201404102P
申请日：2013-02-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUSSIER DARIN S , VOLETI SREENIVASA R , ROBERTSON JR THOMAS J , QUINN CHRISTOPHER M
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8.发明公开THERMALLY CONFORMING ACOUSTIC LINER CARTRIDGE FOR A GAS TURBINE ENGINE 审中-公开热门ANPASSUNG EINER SCHALLAUSKLEIDUNGSKARTUSCHEFÜREINEN GASTURBINENMOTOR
公开(公告)号：EP2971660A4
公开(公告)日：2016-03-09
申请号：EP14807640
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON JR THOMAS J , COSTA MARK W , WELCH DAVID A
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F01D11/125 , F05D2250/283 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/5021 , Y02T50/671
Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.
Abstract translation: 用于燃气涡轮发动机的风扇壳体的盒包括与热适应衬套部分一体化的入口声学衬垫部分。
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公开(公告)号：EP2971606A4
公开(公告)日：2016-12-28
申请号：EP14767427
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： VOLETI SREENIVASA R , ROBERTSON JR THOMAS J , LUSSIER DARIN S
CPC classification number: F01D25/24 , B32B27/38 , B32B2260/021 , B32B2260/046 , F01D21/045 , F01D25/28 , F02C7/32 , F05D2220/32 , F05D2220/36 , F05D2300/43 , F05D2300/501 , F05D2300/603 , F05D2300/614 , Y02T50/672
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10.发明公开TURBINE AIRFOIL WITH ADDITIVE MANUFACTURED REINFORCEMENT OF THERMOPLASTIC BODY 审中-公开含添加剂装配式涡轮刀片加强热塑性BODY
公开(公告)号：EP3099900A4
公开(公告)日：2017-03-22
申请号：EP15770220
申请日：2015-01-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERTSON JR THOMAS J
CPC classification number: F01D25/005 , B22F3/1055 , B22F5/04 , B22F7/08 , B22F2999/00 , B29C45/14819 , B29C70/68 , B29K2705/00 , B29L2031/082 , B33Y10/00 , B33Y30/00 , B33Y80/00 , F01D5/147 , F01D9/041 , F01D17/162 , F05D2220/32 , F05D2240/12 , F05D2250/11 , F05D2250/75 , F05D2300/43 , F05D2300/436 , F05D2300/44 , F05D2300/603 , Y02P10/295
Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.
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