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91. 发明申请

US20160089722A1 METHOD OF MANUFACTURING GAS TURBINE ENGINE COMPONENT FROM A MOLYBDENUM-RICH ALLOY 审中-公开
标题翻译：从多金属合金制造气体涡轮发动机部件的方法
公开(公告)号：US20160089722A1
公开(公告)日：2016-03-31
申请号：US14849644
申请日：2015-09-10
申请人： United Technologies Corporation
发明人： John P. Rizzo, JR.
IPC分类号： B22F3/20 , B23K20/10 , B23K26/00 , B23H7/00 , C22C27/04 , B22F9/16
CPC分类号： B22F3/20 , B21J5/002 , B22F1/0096 , B22F3/17 , B22F9/16 , B22F2998/10 , B23H7/00 , B23K20/10 , B23K26/352 , C22C1/045 , C22C27/04 , C22C32/0005 , C22F1/18 , F01D5/28 , F01D25/005 , F05D2230/22 , F05D2300/131 , F23R2900/00018 , B22F3/02 , B22F2003/247
摘要： A method for manufacturing a gas turbine engine component from a molybdenum-rich alloy. The method includes the steps of providing a molybdenum powder of at least 50% molybdenum by weight, extruding the molybdenum powder to provide a first shape, forming the first shape to a second shape and forging the second shape to provide a third shape.
摘要翻译：一种从富钼合金制造燃气涡轮发动机部件的方法。该方法包括以下步骤：提供至少50重量％钼的钼粉末，挤出钼粉末以提供第一形状，将第一形状形成为第二形状并锻造第二形状以提供第三形状。

92. 发明申请

US20160032732A1 GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS 审中-公开
标题翻译：气体涡轮发动机空气动力学几何和制造过程的方法
公开(公告)号：US20160032732A1
公开(公告)日：2016-02-04
申请号：US14841324
申请日：2015-08-31
申请人： United Technologies Corporation
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
IPC分类号： F01D5/18 , B22C9/10 , B22C9/24 , B22F3/105
CPC分类号： F01D5/187 , B22C9/10 , B22C9/101 , B22C9/24 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y80/00 , C22C28/00 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2260/20 , F05D2300/131 , Y02P10/292 , Y02P10/295
摘要： An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).
摘要翻译：用于燃气涡轮发动机的翼型包括具有通过间隔开的压力和吸力侧连接的前缘和后缘的主体，以提供由周壁限定的外部翼面。内壁布置在周边壁的内部和附近，以在其间提供冷却通道。具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。第一厚度大于第二厚度。第二厚度小于0.060英寸（1.52毫米）。

93. 发明申请

US20160010183A1 METHOD OF MAKING A Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING SAME 审中-公开
标题翻译：制造镍基单晶超级合金的方法和包含其的涡轮叶片
公开(公告)号：US20160010183A1
公开(公告)日：2016-01-14
申请号：US14858421
申请日：2015-09-18
申请人： IHI Corporation
发明人： Yasuhiro Aoki , Akihiro Sato
IPC分类号： C22C19/05 , C22F1/10 , F01D5/28
CPC分类号： C22C19/057 , C22C19/056 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/28 , F05D2220/30 , F05D2230/40 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/175 , F05D2300/177 , F05D2300/607
摘要： The present invention provides a Ni-based single crystal superalloy which has the following composition by weight: 0.1 wt % or more and 9.9 wt % or less of Co, 5.1 wt % or more and 10.0 wt % or less of Cr, 1.0 wt % or more and 4.0 wt % or less of Mo, 8.1 wt % or more and 11.0 wt % or less of W, 4.0 wt % or more and 9.0 wt % or less of Ta, 5.2 wt % or more and 7.0 wt % or less of Al, 0.1 wt % or more and 2.0 wt % or less of Ti, 0.05 wt % or more and 0.3 wt % or less of Hf, 1.0 wt % or less of Nb and less than 3.0 wt % of Re with the remainder including Ni and unavoidable impurities. This Ni-based single crystal superalloy has a low Re content and also has excellent high-temperature strength, mainly creep strength.
摘要翻译：本发明提供一种Ni基单晶超耐热合金，其具有以下重量组成：0.1重量％以上且9.9重量％以下的Co，5.1重量％以上10.0重量％以下的Cr，1.0重量％以上，4.0重量％以下，W：8.1重量％以上，11.0重量％以下，W：4.0重量％以上9.0重量％以下，Ta：5.2重量％以上7.0重量％以下的Al，0.1重量％以上且2.0重量％以下的Ti，0.05重量％以上且0.3重量％以下的Hf，1.0重量％以下的Nb和小于3.0重量％的Re，余量包括 Ni和不可避免的杂质。这种Ni基单晶超合金具有低的Re含量，并且具有优异的高温强度，主要是蠕变强度。

94. 发明申请

US20150377069A1 COATING FOR ISOLATING METALLIC COMPONENTS FROM COMPOSITE COMPONENTS 有权
标题翻译：用于分离复合组分的金属组分的涂料
公开(公告)号：US20150377069A1
公开(公告)日：2015-12-31
申请号：US14749296
申请日：2015-06-24
申请人： Rolls-Royce Corporation
发明人： Sean E. Landwehr , Sungbo Shim , Adam L. Chamberlain , Ann Bolcavage
IPC分类号： F01D25/28
CPC分类号： F01D25/28 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2230/40 , F05D2230/60 , F05D2230/90 , F05D2240/11 , F05D2240/80 , F05D2240/90 , F05D2300/13 , F05D2300/131 , F05D2300/2112 , F05D2300/222 , F05D2300/611 , F05D2300/701
摘要： A barrier coating for isolating a metallic support component from a composite component in a gas turbine engine is provided. The barrier coating may be applied to the metallic support component so that when the ceramic component is mounted on the metallic support component the barrier coating is engaged.
摘要翻译：提供了用于将燃料涡轮发动机中的金属支撑部件与复合部件隔离的阻隔涂层。可以将阻挡涂层施加到金属支撑部件，使得当陶瓷部件安装在金属支撑部件上时，阻挡涂层被接合。

95. 发明申请

US20150321249A1 Hybrid Turbine Blade for Improved Engine Performance or Architecture 审中-公开
标题翻译：用于改善发动机性能或结构的混合涡轮叶片
公开(公告)号：US20150321249A1
公开(公告)日：2015-11-12
申请号：US14651911
申请日：2013-12-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Dilip M. Shah , Alan D. Cetel
IPC分类号： B22D25/02 , B22D21/06 , C22C19/05 , F01D5/28
CPC分类号： B22D25/02 , B22D19/16 , B22D21/025 , B22D21/06 , B22D27/045 , C22C19/057 , F01D5/14 , F01D5/147 , F01D5/28 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/17 , F05D2300/606 , F05D2300/609 , Y10T403/478
摘要： A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.
摘要翻译：提供了一种用于铸造诸如具有附接根部和翼型的叶片的制品的方法，所述翼型件具有近端和远端。该方法包括将熔融合金引入模具中; 并且在引入期间改变引入的合金的组成以产生组成变化。

96. 发明申请

US20130280081A1 GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS 审中-公开
标题翻译：气体涡轮发动机空气动力学几何和制造过程的方法
公开(公告)号：US20130280081A1
公开(公告)日：2013-10-24
申请号：US13454221
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
IPC分类号： F03B3/12 , B22F3/02
CPC分类号： F01D5/187 , B22C9/10 , B22C9/101 , B22C9/24 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y80/00 , C22C28/00 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2260/20 , F05D2300/131 , Y02P10/292 , Y02P10/295
摘要： A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of a refractory metal core, and producing the core having a variable thickness.
摘要翻译：用于翼型的芯部包括具有可变厚度的难熔金属结构。翼型件包括主体，其具有通过间隔开的压力和吸力侧连接的前缘和后缘，以提供由周边壁限定的外部翼型表面。内壁布置在周边壁的内部和附近，以在其间提供冷却通道。具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。第一厚度大于第二厚度，第二厚度小于0.060英寸（1.52mm）。制造难熔金属芯的方法包括将多层粉末状金属彼此沉积，参照与难熔金属芯的特定横截面相关的CAD数据将层彼此接合，并且制造具有可变的厚度。

97. 发明授权

US08511999B1 Multiple piece turbine rotor blade 有权
标题翻译：多片涡轮转子叶片
公开(公告)号：US08511999B1
公开(公告)日：2013-08-20
申请号：US12731928
申请日：2010-03-25
申请人： Keith D Kimmel , Jack W. Wilson , Russell B Jones
发明人： Keith D Kimmel , Jack W. Wilson , Russell B Jones
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/20 , F01D5/30 , F05D2300/13 , F05D2300/131
摘要： A turbine rotor blade of the spar and shell construction, the spar including a tip end with a dovetail shaped groove extending from the top, and a tip cap includes a dovetail shaped slot that engages with the spar groove to retain the tip cap in place. A shell made from a high temperature resistant material is secured in place between the platform and the tip cap. The platform includes a core extending into a hollow space formed by the shell and discharges impingement cooling air against the backside wall of the shell. The spar and the platform include fir tree configurations so that an assembled blade can be inserted into a slot of a rotor disk.
摘要翻译：翼梁和壳体结构的涡轮机转子叶片，翼梁包括具有从顶部延伸的燕尾形槽的末端，并且尖端帽包括与翼梁槽接合以将顶盖保持在适当位置的燕尾形槽。由耐高温材料制成的外壳固定在平台和顶盖之间的适当位置。平台包括延伸到由壳体形成的中空空间中的芯体，并将冲击冷却空气排放到壳体的后壁上。翼梁和平台包括枞树构造，使得组装的叶片可以插入转子盘的槽中。

98. 发明授权

US08241560B2 Nickel base superalloy and single crystal castings 有权
标题翻译：镍基超级合金和单晶铸件
公开(公告)号：US08241560B2
公开(公告)日：2012-08-14
申请号：US10424589
申请日：2003-04-28
申请人： John Corrigan , Michael G. Launsbach , John R. Mihalisin
发明人： John Corrigan , Michael G. Launsbach , John R. Mihalisin
IPC分类号： C22C19/05
CPC分类号： C22C19/057 , F01D5/28 , F05C2201/0466 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/1723
摘要： A single crystal nickel base superalloy consists essentially of, in weight %, about 6.4% to about 6.8% Cr, about 9.3% to about 10.0% Co, above 6.7% to about 8.5% Ta, about 5.45% to about 5.75% Al, about 6.2% to about 6.6% W, about 0.5% to about 0.7% Mo, about 0.8% to about 1.2% Ti, about 2.8% to about 3.2% Re, up to about 0.12% Hf, about 0.01% to about 0.08% by weight C, up to about 0.10% B, and balance Ni and incidental impurities. The superalloy provides improved alloy cleanliness and castability while providing improved high temperature mechanical properties such as stress rupture life.
摘要翻译：单晶镍基超级合金基本上由重量％，约6.4％至约6.8％的Cr，约9.3％至约10.0％的Co，高于6.7％至约8.5％的Ta，约5.45％至约5.75％的Al，约6.2％至约6.6％的W，约0.5％至约0.7％的Mo，约0.8％至约1.2％的Ti，约2.8％至约3.2％的Re，至多约0.12％的Hf，约0.01％至约0.08％的C，高达约0.10％的B，并且平衡Ni和附带的杂质。超耐热合金提供改善的合金清洁度和铸造性，同时提供改善的高温机械性能，如应力断裂寿命。

99. 发明授权

US07866950B1 Turbine blade with spar and shell 有权
标题翻译：涡轮叶片与翼梁和壳
公开(公告)号：US07866950B1
公开(公告)日：2011-01-11
申请号：US12176622
申请日：2008-07-21
申请人： Jack W Wilson, Jr.
发明人： Jack W Wilson, Jr.
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/20 , F05D2230/50 , F05D2300/131 , F05D2300/506
摘要： A turbine blade for use in a gas turbine engine, where the turbine blade is made from a spar and shell construction in which a thin walled shell is held in place between the blade tip and the platform by only a mechanical fastener without using any bonding, welding or brazing. The spar is connected to an attachment by a tie bolt, and a separate platform is secured, over the attachment t in which the shell is held against. This provides for a thermally free platform and shell connection. With this arrangement, the shell is held under compression within the 2% yield stress range such that the turbine blade shell can have an infinite life. Also, the turbine blade is much lighter than prior art blades. As a result, the spar and shell blade produces less stress on the rotor disk during engine operation.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，其中涡轮机叶片由翼梁和壳体结构制成，其中薄壁壳体仅通过机械紧固件而保持在叶片尖端和平台之间的适当位置，而不使用任何接合，焊接或钎焊。翼梁通过连接螺栓连接到附件，并且单独的平台固定在附接件t上，壳体被固定在其上。这提供了一个无热平台和外壳连接。通过这种布置，壳体在2％屈服应力范围内保持压缩，使得涡轮机叶片壳体可以具有无限的寿命。此外，涡轮叶片比现有技术的叶片要轻得多。结果，在发动机运转时，翼梁和壳叶片在转子盘上产生较小的应力。

100. 发明申请

US20100059572A1 WELD REPAIR PROCESS AND ARTICLE REPAIRED THEREBY 审中-公开
标题翻译：焊接维修工艺及其修理
公开(公告)号：US20100059572A1
公开(公告)日：2010-03-11
申请号：US12206886
申请日：2008-09-09
申请人： John M. Sassatelli , John F. Nolan , Nicholas D. Porteous , Mark J. Passino, JR. , Gerald R. Crawmer , Carter S. Cook
发明人： John M. Sassatelli , John F. Nolan , Nicholas D. Porteous , Mark J. Passino, JR. , Gerald R. Crawmer , Carter S. Cook
IPC分类号： B23K31/02
CPC分类号： B23K9/044 , B23K2101/001 , B23K2103/04 , B23K2103/18 , B23K2103/26 , C21D9/50 , C22C19/00 , F01D5/005 , F05C2201/0463 , F05C2201/0466 , F05D2220/31 , F05D2230/232 , F05D2300/11 , F05D2300/131 , F05D2300/132
摘要： A method for repairing a steel alloy article, and an article repaired thereby, is provided and comprises the steps of depositing at least a first weld repair layer on a surface of the article so as to form a heat affected zone in the article beneath the surface. Locally heat treating the first weld repair layer and at least a portion of the heat affected zone adjacent the first weld repair layer at a temperature above the critical A1 temperature of the steel alloy article. Depositing at least one additional weld repair layer on the first weld repair layer without forming additional heat affected zone in the surface of the article. The first weld repair layer and the at least one additional weld repair layer are comprised of a material chosen from the group consisting of nickel chromium—iron alloys, cobalt base alloys, ERNiCr-3, ENiCrFe-3, ERNiCrMo-3, ERNiFeCr-2, ERCoCr-A, ERCoCr-E, CrMo alloys and CrMoV alloys. The article can be placed in service without a post-weld heat treatment of the additional weld repair layer following the step of depositing the additional weld repair layer.
摘要翻译：提供了修复钢合金制品的方法和由此修补的制品，并且包括以下步骤：在制品的表面上沉积至少第一焊接修复层，以便在制品下面形成热影响区。在高于钢合金制品的临界Al温度的温度下，局部热处理第一焊接修复层和与第一焊接修复层相邻的热影响区的至少一部分。在第一焊接修复层上沉积至少一个附加的焊接修复层，而不在制品的表面中形成额外的热影响区。第一焊接修复层和至少一个另外的焊接修复层由选自镍铬铁合金，钴基合金，ERNiCr-3，ENiCrFe-3，ERNiCrMo-3，ERNiFeCr-2的材料组成，ERCoCr-A，ERCoCr-E，CrMo合金和CrMoV合金。在附加的焊接修复层的沉积步骤之后，可以在不进行附加焊接修复层的焊后热处理的情况下使用该制品。

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