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131. 发明授权

US08425836B1 Chromium alloy 有权
标题翻译：铬合金
公开(公告)号：US08425836B1
公开(公告)日：2013-04-23
申请号：US13297560
申请日：2011-11-16
申请人： Ayan Bhowmik , Howard J. Stone , Ian M. Edmonds
发明人： Ayan Bhowmik , Howard J. Stone , Ian M. Edmonds
IPC分类号： C22C27/06
CPC分类号： C22C27/06 , F05D2200/30 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/17
摘要： A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminum, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.
摘要翻译：一种过共晶铬合金，其由9至12at％的钽，4至15at％的硅，0至7at％的钼，0至7at％的铝，0至7at％的钛，0至5at％的铼，0至 2％银，0至2at％铪，0至2at％镧，0至2at％铈，0至2at％钇，余量为铬和附带杂质。过共晶铬合金具有良好的抗氧化性和良好的断裂韧性。铬合金可用于制造燃气涡轮发动机涡轮机叶片，涡轮叶片，涡轮密封件，燃烧室瓦片，排气喷嘴段或汽轮机部件。

132. 发明申请

US20120082551A1 GAS TURBINE BLADE AND METHOD OF PROTECTING SAME 有权
标题翻译：气体涡轮叶片及其保护方法
公开(公告)号：US20120082551A1
公开(公告)日：2012-04-05
申请号：US13189043
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
IPC分类号： F01D5/30
CPC分类号： F01D5/3092 , F01D5/005 , F01D5/28 , F05B2230/90 , F05D2220/32 , F05D2230/80 , F05D2230/90 , F05D2260/94 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/134 , F05D2300/143 , F05D2300/16 , F05D2300/1614 , F05D2300/1616 , F05D2300/609
摘要： An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
摘要翻译：燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。

133. 发明授权

US08097303B2 Methods for producing multilayered, oxidation-resistant structures on substrates 有权
标题翻译：在基材上生产多层抗氧化结构的方法
公开(公告)号：US08097303B2
公开(公告)日：2012-01-17
申请号：US12474977
申请日：2009-05-29
申请人： John H. Perepezko , Joon S. Park , Ridwan Sakidja
发明人： John H. Perepezko , Joon S. Park , Ridwan Sakidja
IPC分类号： C23C16/40
CPC分类号： C23C26/00 , F01D5/288 , F05D2230/90 , F05D2300/131 , F05D2300/222 , F05D2300/611
摘要： Methods for producing multilayered, oxidation-resistant structures on substrates are provided. The methods comprise depositing silicon dioxide on a substrate comprising molybdenum and boron and annealing the silicon dioxide at a temperature and for a time sufficient to form a coating comprising a borosilicate scale on the substrate.
摘要翻译：提供了在基片上生产多层抗氧化结构的方法。所述方法包括在包含钼和硼的衬底上沉积二氧化硅，并在足以在衬底上形成包含硼硅酸盐垢的涂层的温度和时间下退火二氧化硅。

134. 发明授权

US08070450B1 High temperature turbine rotor blade 有权
标题翻译：高温涡轮转子叶片
公开(公告)号：US08070450B1
公开(公告)日：2011-12-06
申请号：US12426343
申请日：2009-04-20
申请人： John E Ryznic , Wesley D Brown
发明人： John E Ryznic , Wesley D Brown
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F05D2300/13 , F05D2300/131
摘要： A turbine rotor blade made from the spar and shell construction in which the shell formed from a plurality of shell segments each being a thin wall shell segment made from a high temperature resistant material that is formed by a wire EDM process, and where the shell segments are each secured to the spar separately using a retainer that is poured into retainer occupying spaces formed in the shell segments and the spar, and then hardened to form a rigid retainer to secure each shell segment to the spar individually. The spar includes a number of radial extending projections each with a row of cavities that form the retainer occupying spaces in order to spread the loads around. The retainer can be a bicast material, a transient liquid phase bonding material, or a sintered metal. An old shell can be easily removed and replaced with a new shell by removing parts of the retainer and re-pouring a new retainer with a new shell in place.
摘要翻译：一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体由多个壳段形成，每个壳段均由由电线EDM工艺形成的耐高温材料制成的薄壁壳段，并且其中壳段各自使用保持器分别固定到翼梁上，该保持器被注入到形成在壳段和翼梁中的保持器占据空间中，然后硬化以形成刚性保持器，以将每个壳段单独地固定到翼梁。翼梁包括多个径向延伸的突起，每个具有一排空腔，形成保持器占据空间，以便使负载周围扩展。保持器可以是组播材料，瞬态液相粘合材料或烧结金属。可以通过移除保持器的部件并将新的保持器重新装入新的壳体中，可以容易地移除旧壳体并用新的壳体代替。

135. 发明授权

US07861510B1 Ceramic regenerator for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的陶瓷再生器
公开(公告)号：US07861510B1
公开(公告)日：2011-01-04
申请号：US12276322
申请日：2008-11-22
申请人： Jack W. Wilson, Jr. , John E. Ryznic
发明人： Jack W. Wilson, Jr. , John E. Ryznic
IPC分类号： F02C7/00 , F02G1/00
CPC分类号： F02C7/10 , F05D2300/131 , F05D2300/21 , F05D2300/611
摘要： A high temperature heat exchanger for use with a small gas turbine engine to produce a combined cycle power plant, where the heat exchanger includes ceramic heat exchange tubes of SiC that are tightly fitted to the heat exchanger so that no welds or brazing is used and prevent any thermal stresses between the tubes and the heat exchanger end plates or baffle plates. The heat exchanger includes an inner casing and an outer casing with the heat exchange tubes extending through the heat exchanger between the two casings, and the gas turbine engine operating in the space within the inner casing. The tubes are tightly fitted in holes within the end plates and baffle plates, and a molybdenum disulfide coating is used to form a seal.
摘要翻译：一种用于小型燃气涡轮发动机以生产联合循环发电厂的高温热交换器，其中热交换器包括紧密地装配到热交换器的SiC的陶瓷热交换管，使得不使用焊接或钎焊，并且防止管和热交换器端板或挡板之间的任何热应力。热交换器包括内壳和外壳，其中热交换管延伸穿过两壳体之间的热交换器，并且燃气涡轮发动机在内壳体内的空间中工作。管紧紧地装配在端板和挡板中的孔中，并且使用二硫化钼涂层形成密封。

136. 发明授权

US07824150B1 Multiple piece turbine airfoil 有权
标题翻译：多件涡轮机翼型
公开(公告)号：US07824150B1
公开(公告)日：2010-11-02
申请号：US12467009
申请日：2009-05-15
申请人： Keith D Kimmel , Jack W. Wilson, Jr.
发明人： Keith D Kimmel , Jack W. Wilson, Jr.
IPC分类号： F01D9/06 , F01D5/18
CPC分类号： F01D5/189 , F01D5/147 , F05D2230/642 , F05D2300/13 , F05D2300/131 , F05D2300/50212 , Y02T50/672 , Y02T50/676
摘要： A turbine airfoil, such as a rotor blade or a stator vane, for a gas turbine engine, the airfoil formed as a shell and spar construction with a plurality of dog bone struts each mounted within openings formed within the shell and spar to allow for relative motion between the spar and shell in the airfoil chordwise direction while also forming a seal between adjacent cooling channels. The struts provide the seal as well as prevent bulging of the shell from the spar due to the cooling air pressure.
摘要翻译：用于燃气涡轮发动机的诸如转子叶片或定子叶片的涡轮机翼片，形成为壳体的翼型件和具有多个狗骨架的翼梁结构，每个支架安装在形成在壳体和翼梁内的开口内，以允许相对叶片和翼壳在翼型方向上的运动，同时在相邻的冷却通道之间形成密封。由于冷却空气压力，支柱提供密封以及防止壳体从翼梁膨胀。

137. 发明申请

US20090214345A1 LOW PRESSURE SECTION STEAM TURBINE BUCKET 审中-公开
标题翻译：低压部分蒸汽涡轮机
公开(公告)号：US20090214345A1
公开(公告)日：2009-08-27
申请号：US12037346
申请日：2008-02-26
申请人： Alan R. DeMania , Amir Mujezinovic
发明人： Alan R. DeMania , Amir Mujezinovic
IPC分类号： F01D5/14 , F01D5/22
CPC分类号： F01D5/14 , C22C14/00 , F01D5/22 , F01D5/28 , F05D2220/31 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/1614
摘要： A bucket for use in the low-pressure section of a steam turbine engine is provided. The bucket has a vane length of at least about 45 inches. The bucket is comprised of a dovetail section disposed near an inner radial position of the bucket, a tip shroud disposed near an outer radial position of the bucket and a part span shroud disposed at an intermediate radial position. The intermediate radial position is located between the inner and outer radial positions. The bucket is comprised of a titanium-based alloy having between about 2% and about 6.25% by weight aluminum, up to about 3.5% vanadium, up to about 2.25% tin, up to about 2.25% zirconium, between about 1.75% and about 5.0% molybdenum, up to about 2.25% chromium, up to about 0.7% silicon and up to about 2.3% iron, with the balance being titanium.
摘要翻译：提供了一种用于蒸汽涡轮发动机的低压部分的铲斗。铲斗具有至少约45英寸的叶片长度。铲斗由设置在铲斗的内部径向位置附近的燕尾部分组成，尖端护罩设置在铲斗的外部径向位置附近，并且设置在中间径向位置处的部分跨距护罩。中间径向位置位于内径和外径位置之间。该桶由具有约2％至约6.25重量％的铝，至多约3.5％的钒，至多约2.25％的锡，至多约2.25％的锆，约1.75％和约 5.0％的钼，至多约2.25％的铬，至多约0.7％的硅和至多约2.3％的铁，余量为钛。

138. 发明授权

US07331757B2 Turbine shaft and production of a turbine shaft 有权
标题翻译：涡轮轴和涡轮轴的生产
公开(公告)号：US07331757B2
公开(公告)日：2008-02-19
申请号：US10537237
申请日：2003-12-02
申请人： Wolfgang Janssen , Torsten-Ulf Kern , Heinz Klöckner
发明人： Wolfgang Janssen , Torsten-Ulf Kern , Heinz Klöckner
IPC分类号： F01D25/00
CPC分类号： F01D5/026 , F01D5/063 , F01D5/28 , F05C2201/0466 , F05D2230/232 , F05D2300/131 , F05D2300/132 , Y10T29/4932
摘要： The invention relates to a turbine shaft for a steam turbine, oriented in an axial direction and comprising a first and a second flow region. According to the invention, a first material is provided in the first flow region of the turbine shaft, and a second flow region is provided in the second flow region thereof, the first material having heat-resistant properties and the second material having cold-resistant properties. The inventive turbine shaft is produced by means of a construction weld seam without any previous buffer layer welding on one of the two materials.
摘要翻译：本发明涉及一种用于汽轮机的涡轮轴，其轴向定向并且包括第一和第二流动区域。根据本发明，在涡轮轴的第一流动区域中设置第一材料，并且在其第二流动区域中设置第二流动区域，第一材料具有耐热性能，第二材料具有耐寒性属性。本发明的涡轮轴通过施工焊缝生产，在两种材料之一上没有任何先前的缓冲层焊接。

139. 发明申请

US20060118215A1 Precipitation hardened martensitic stainless steel, manufacturing method therefor, and turbine moving blade and steam turbine using the same 审中-公开
标题翻译：沉淀硬化马氏体不锈钢及其制造方法，以及使用其的涡轮机动叶片和蒸汽轮机
公开(公告)号：US20060118215A1
公开(公告)日：2006-06-08
申请号：US11135385
申请日：2005-05-24
申请人： Yuichi Hirakawa , Yoshikuni Kadoya , Hiroharu Ooyama , Tatsuya Furukawa , Naoto Tochitani
发明人： Yuichi Hirakawa , Yoshikuni Kadoya , Hiroharu Ooyama , Tatsuya Furukawa , Naoto Tochitani
IPC分类号： C22C38/44
CPC分类号： F01D5/286 , C21D6/004 , C21D6/005 , C21D6/008 , C21D6/02 , C21D9/0068 , C21D2211/008 , C22C38/001 , C22C38/02 , C22C38/04 , C22C38/06 , C22C38/44 , C22C38/48 , F01D5/02 , F01D5/12 , F05C2201/0466 , F05D2220/30 , F05D2220/31 , F05D2230/00 , F05D2230/411 , F05D2300/11 , F05D2300/121 , F05D2300/125 , F05D2300/131 , F05D2300/132 , F05D2300/171
摘要： The precipitation hardened martensitic stainless steel is characterized by containing, in percent by weight, 12.25 to 14.25% Cr, 7.5 to 8.5% Ni, 1.0 to 2.5% Mo, 0.05% or less C, 0.2% or less Si, 0.4% or less Mn, 0.03% or less P, 0.005% or less S, 0.008% or less N, 0.90 to 2.25% Al, the balance substantially being Fe, and the total content of Cr and Mo being 14.25 to 16.75%. A turbine moving blade and a steam turbine are manufactured by using this martensitic stainless steel.
摘要翻译：沉淀硬化马氏体不锈钢的特征在于，以重量％计含有12.25〜14.25％的Cr，7.5〜8.5％的Ni，1.0〜2.5％的Mo，0.05％以下的C，0.2％以下的Si，0.4％以下 Mn，0.03％以下的P，0.005％以下的S，0.008％以下的N，0.90〜2.25％的Al，余量实质上为Fe，Cr和Mo的总含量为14.25〜16.75％。通过使用该马氏体不锈钢制造涡轮机动叶片和汽轮机。

140. 发明申请

US20030217792A1 Hybrid single crystal-powder metallurgy turbine component 有权
标题翻译：混合单晶粉末冶金涡轮机组件
公开(公告)号：US20030217792A1
公开(公告)日：2003-11-27
申请号：US10155257
申请日：2002-05-24
申请人： Siemens Westinghouse Power Corporation
发明人： Allister James
IPC分类号： B32B015/01
CPC分类号： C22C19/03 , B22F5/04 , B22F7/08 , B22F2998/10 , B32B15/01 , C22C19/058 , F01D5/187 , F05C2201/0463 , F05C2201/0466 , F05D2230/00 , F05D2230/21 , F05D2300/11 , F05D2300/121 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/607 , Y10T428/12944 , B22F3/15 , B22F2202/01
摘要： A hybrid component (30) having a cast single crystal superalloy portion (32) and an attached powder metallurgy material portion (34). The component may be a blade (30) of a gas turbine engine having a single crystal airfoil section and a powder metallurgy material root section. The powder metallurgy material may extend to form a core (36) within the airfoil section and may include cooling passages 38. The single crystal portion has a relatively simple geometry so that casting yields are optimized. The powder metallurgical portion includes the lower stressed and more complicated geometry sections of the component. A method of forming such a component includes casting the single crystal superalloy portion, then using that portion to form part of the mold for forming the powder metallurgy material portion.
摘要翻译：具有铸造单晶超合金部分（32）和附着的粉末冶金材料部分（34）的混合部件（30）。该部件可以是具有单晶翼型部分和粉末冶金材料根部的燃气轮机的叶片（30）。粉末冶金材料可以延伸以在翼型部分内形成芯部（36）并且可以包括冷却通道38.单晶部分具有相对简单的几何形状，使得铸造产量被优化。粉末冶金部分包括部件的较低应力和更复杂的几何形状部分。形成这种组分的方法包括浇铸单晶超合金部分，然后使用该部分形成用于形成粉末冶金材料部分的模具的一部分。

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