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公开(公告)号：US07341427B2
公开(公告)日：2008-03-11
申请号：US11306221
申请日：2005-12-20
申请人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
发明人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
IPC分类号： F04D9/02
CPC分类号： F01D5/288 , F01D9/041 , F05D2220/31 , F05D2230/21 , F05D2230/31 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611
摘要： A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.
摘要翻译： 一种燃气涡轮发动机喷嘴段和用于生产这种喷嘴段的工艺，以显示出改善的耐久性和空气动力性能。 该过程产生具有在一对平台之间并互连的至少一个叶片的喷嘴段。 喷嘴段由伽马强化镍基超级合金铸造，其表面被热喷涂为由MCrAlX型涂层材料形成的环境涂层。 然后对环境涂层的表面进行加工，使涂层的表面光洁度小于2.0微米。 然后在喷嘴段中钻出冷却孔，然后在喷嘴段的平滑表面上施加耐氧化涂层，以便保持表面光洁度小于2.0微米Ra的喷嘴段上的最外表面。
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公开(公告)号：US07140835B2
公开(公告)日：2006-11-28
申请号：US10956299
申请日：2004-10-01
IPC分类号： F01D9/02
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.
摘要翻译： 涡轮喷嘴包括连接到相对的内部和外部带的中空叶片。 内带包括在叶片的前缘下方的前唇，在叶片的后缘下方的后唇，以及间隔开的安装凸缘。 冲击孔从安装凸缘的底部在内带的角部向后缘倾斜地向后延伸，用于冲击冷却。
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3.发明授权Thermal barrier coating protected by tantalum oxide and method for preparing same 失效由氧化钽保护的热障涂层及其制备方法公开(公告)号：US06933066B2
公开(公告)日：2005-08-23
申请号：US10317731
申请日：2002-12-12
申请人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
发明人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
CPC分类号： C23C28/00 , C23C30/00 , F01D5/288 , F05D2240/11 , F05D2300/21 , Y10T428/24917 , Y10T428/24926 , Y10T428/265
摘要： A thermal barrier coating for an underlying metal substrate of articles that operate at, or are exposed to, high temperatures, as well as being exposed to environmental contaminant compositions. This coating includes an inner layer nearest to the underlying metal substrate comprising a ceramic thermal barrier coating material, as well as an outer layer having an exposed surface and comprising tantalum oxide in an amount sufficient to protect the thermal barrier coating at least partially against environmental contaminants that become deposited on the exposed surface and optionally an intermediate layer between the inner and outer layers comprising alumina. This coating can be used to provide a thermally protected article having a metal substrate and optionally a bond coat layer adjacent to and overlaying the metal substrate. The thermal barrier coating can be prepared by forming the inner layer comprising the ceramic thermal barrier material, optionally forming the intermediate layer comprising the alumina over the inner layer, and then forming the outer layer comprising the tantalum oxide over the intermediate (inner) layer.
摘要翻译： 用于在高温下操作或暴露于高温以及暴露于环境污染物组合物的制品的基础金属基底的热障涂层。 该涂层包括最接近底层金属基底的内层，其包含陶瓷热障涂层材料，以及具有暴露表面的外层，并且包含足以保护热障涂层的氧化钽至少部分地防止环境污染物 其沉积在暴露的表面上，并且任选地沉积在包含氧化铝的内层和外层之间的中间层。 该涂层可用于提供具有金属基底和任选的与金属基底相邻并覆盖金属基底的粘合涂层的热保护制品。 可以通过形成包含陶瓷热障材料的内层，任选地在内层上形成包含氧化铝的中间层，然后在中间（内）层上形成包含氧化钽的外层来制备热障涂层。
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公开(公告)号：US06582834B2
公开(公告)日：2003-06-24
申请号：US09879691
申请日：2001-06-12
IPC分类号： B32B1504
CPC分类号： C23C16/045 , C23C16/40 , C23C28/00 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y10T428/12458 , Y10T428/12611 , Y10T428/12618 , Y10T428/12736 , Y10T428/12944 , Y10T428/24975 , Y10T428/265
摘要： An anti-stick coating that inhibits the adhesion of contaminants that form deposits on the internal cooling passages of gas turbine engine components. The anti-stick coating is formed as an outer coating of the internal cooling passages, and preferably overlies an environmental coating such as a diffusion aluminide coating formed on the passage surfaces. The outer coating has a thickness of not greater than three micrometers, and is resistant to adhesion by dirt contaminants as a result of comprising at least one layer of tantala, titania, hafnia, niobium oxide, yttria, silica and/or alumina. The outer coating is preferably deposited directly on the environmental coating by chemical vapor deposition.
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公开(公告)号：US07371046B2
公开(公告)日：2008-05-13
申请号：US11160010
申请日：2005-06-06
IPC分类号： F04D29/54
CPC分类号： F01D5/143 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/80 , Y02T50/673
摘要： A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading and trailing edges. A compound fillet is disposed between the airfoil body and at least one of the platforms. The compound fillet includes a concave first fillet having a first radius, and a concave second fillet having a second, greater radius. The second fillet extends from the leading edge downstream along the suction sidewall and terminates at a point upstream of the trailing edge. The second fillet may also extend downstream from the leading edge along the pressure sidewall.
摘要翻译： 涡轮机翼片可以是具有单个平台的旋转叶片或具有一对平台的固定喷嘴。 机翼本体具有在前缘和后缘之间延伸的压力和吸力侧壁。 在翼型件本体和至少一个平台之间设置复合内圆角。 复合圆角包括具有第一半径的凹入的第一圆角和具有第二较大半径的凹入的第二圆角。 第二圆角从前缘沿着吸力侧壁向下游延伸，并终止在后缘上游的一个点处。 第二圆角也可以沿着压力侧壁从前缘的下游延伸。
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公开(公告)号：US20080080968A1
公开(公告)日：2008-04-03
申请号：US11538273
申请日：2006-10-03
IPC分类号： F01D25/26
CPC分类号： F01D25/246 , F01D11/005 , F05D2240/57
摘要： A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.
摘要翻译： 提供一种用于组装燃气涡轮发动机的方法。 该方法包括提供包括外带和内带的涡轮喷嘴，其中每个带包括前缘，后缘和在其间延伸的本体。 外带和内带中的至少一个具有从其向外延伸的至少一个径向突片。 该方法还包括在从外带和内带延伸的至少一个径向突片和外带和内带的相应前缘之间联接至少一个密封件。 该方法还包括将至少一个非平面密封支撑件定位在密封件的至少一部分上。
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公开(公告)号：US20070134087A1
公开(公告)日：2007-06-14
申请号：US11297082
申请日：2005-12-08
申请人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles , Douglas Fortuna
发明人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles , Douglas Fortuna
IPC分类号： F01D9/00
CPC分类号： F01D9/023 , F01D9/042 , F01D25/246 , F05D2300/505 , Y02T50/673 , Y02T50/675
摘要： A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, coupling the turbine nozzle within the gas turbine engine, such that the turbine nozzle is downstream from a combustor, and coupling the turbine nozzle to the combustor using at least a first annular ring, wherein the first annular ring substantially seals a gap defined between the turbine nozzle and the combustor.
摘要翻译： 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，其包括内带，外带，以及在内带和外带之间延伸的至少一个叶片，将涡轮喷嘴连接在燃气涡轮发动机内，使得涡轮喷嘴在 燃烧器，并且使用至少第一环形环将涡轮喷嘴耦合到燃烧器，其中第一环形圈基本上密封限定在涡轮喷嘴和燃烧器之间的间隙。
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公开(公告)号：US07195454B2
公开(公告)日：2007-03-27
申请号：US11002570
申请日：2004-12-02
CPC分类号： F01D5/143 , F01D5/145 , F01D9/041 , F01D11/005 , F01D25/246 , F05D2250/19 , Y02T50/673
摘要： A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.
摘要翻译： 涡轮机翼型包括从流路表面跨越的相对的压力和吸力侧。 流路表面具有弦向相反的前后边缘，并且与翼型压力和吸力侧对应的横向相对的第一和第二端面。 流路表面将前端长嘴的前边缘处的第一端面连接起来，并且在后方长臂处的后边缘处连接第二端面，其中棱镜从相对边缘的半径变化。
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公开(公告)号：US20060062671A1
公开(公告)日：2006-03-23
申请号：US10898835
申请日：2004-07-26
申请人： Ching-Pang Lee , Wenfeng Lu
发明人： Ching-Pang Lee , Wenfeng Lu
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/081 , F01D5/187 , F05D2260/607 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls spaced apart between opposite leading and trailing edges and interconnected by a plurality of partitions to define first and second independent cooling circuits therein. The cooling circuits have corresponding inlets in a dovetail of the blade and extend through a platform of the blade and through the airfoil to its tip. A common discharge chamber is disposed below the airfoil tip and includes a plurality of outlet holes for discharging cooling air from the circuits.
摘要翻译： 涡轮机叶片包括具有在相对的前缘和后缘间隔开的压力和吸力侧壁的翼型件，并通过多个隔板互连以在其中限定第一和第二独立冷却回路。 冷却回路在叶片的燕尾形中具有相应的入口，并延伸穿过叶片的平台并且通过翼型件到其顶端。 公共排放室设置在翼型件末端的下方，并且包括用于从电路排出冷却空气的多个出口孔。
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公开(公告)号：US07976274B2
公开(公告)日：2011-07-12
申请号：US11297699
申请日：2005-12-08
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F01D9/02 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.
摘要翻译： 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，该涡轮喷嘴包括内带，外带，在内带和外带之间延伸的至少一个叶片，以及在至少一个叶片和至少一个叶片之间延伸的至少一个前缘圆角 内部和外部带，其中所述至少一个叶片的前缘在所述内部和外部带的前缘的下游，以及将所述涡轮喷嘴连接在所述燃气涡轮发动机内，使得所述前缘圆角被配置为有助于最小化涡旋 沿着与内带和外带中的至少一个相邻的叶片前缘的形成。
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