公开(公告)号：US20070071996A1

公开(公告)日：2007-03-29

申请号：US11162839

申请日：2005-09-26

申请人： Brian Hazel ,  Ramgopal Darolia ,  Brett Boutwell ,  David Wortman

发明人： Brian Hazel ,  Ramgopal Darolia ,  Brett Boutwell ,  David Wortman

IPC分类号： F03B3/12 ,  B32B15/01 ,  B23K35/00

CPC分类号： C23C30/00 ,  Y10T428/12458 ,  Y10T428/12736 ,  Y10T428/1275 ,  Y10T428/12875 ,  Y10T428/12937 ,  Y10T428/12944

摘要： An intermetallic composition suitable for use as an environmentally-protective coating on surfaces of components used in hostile thermal environments, including the turbine, combustor and augmentor sections of a gas turbine engine. The coating contains the gamma-prime (Ni3Al) nickel aluminide intermetallic phase and either the beta (NiAl) nickel aluminide intermetallic phase or the gamma solid solution phase. The coating has an average aluminum content of 14 to 30 atomic percent and an average platinum-group metal content of at least 1 to less than 10 atomic percent, the balance of the coating being nickel, one or more of chromium, silicon, tantalum, and cobalt, optionally one or more of hafnium, yttrium, zirconium, lanthanum, and cerium, and incidental impurities.

摘要翻译： 适用于在敌对热环境中使用的组件的表面上用作环境保护涂层的金属间组合物，包括燃气涡轮发动机的涡轮机，燃烧器和增压器部分。 该涂层含有γ-prime（Ni 3 Al 3）铝铝化物金属间相和β（NiAl）镍铝化物金属间相或γ固溶体相。 该涂层的平均铝含量为14〜30原子％，平均铂族金属含量为1〜10原子％以下，镀层为镍，铬，硅，钽， 和钴，任选地一种或多种铪，钇，锆，镧和铈以及附带的杂质。

公开(公告)号：US20060057406A1

公开(公告)日：2006-03-16

申请号：US10711364

申请日：2004-09-14

申请人： Ramgopal Darolia ,  Brett Boutwell ,  Brian Hazel ,  Bangalore Nagaraj ,  Joseph Rigney ,  Roger Wustman

发明人： Ramgopal Darolia ,  Brett Boutwell ,  Brian Hazel ,  Bangalore Nagaraj ,  Joseph Rigney ,  Roger Wustman

IPC分类号： B32B15/04 ,  B32B9/00 ,  C23C16/00

CPC分类号： C23C14/226 ,  C23C14/22 ,  C23C14/505 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/611 ,  Y10T428/24355 ,  Y10T428/24413

摘要： Thermal barrier coating (TBC) and a method of depositing a TBC having a modulated columnar microstructure that exhibits increased impact resistance. The TBC is deposited to have a columnar microstructure in which columns extend from a substrate surface. The columns having inner regions contacting the surface, outer regions near an outermost surface of the TBC, and interior regions therebetween. The inner regions of the columns are substantially normal to the substrate surface and at least one of the interior and outer regions of the columns are nonaligned with its respective inner regions, so that the columns of the columnar microstructure are continuous but modulated between the inner and outer regions to reduce tensile stresses within the columns resulting from particle impact.

摘要翻译： 热屏蔽涂层（TBC）和沉积具有显示出增加的耐冲击性的调制柱状微结构的TBC的方法。 沉积TBC以具有柱状微结构，其中柱从衬底表面延伸。 具有接触表面的内部区域，靠近TBC的最外表面的外部区域以及它们之间的内部区域的列。 柱的内部区域基本上垂直于基底表面，并且柱的内部和外部区域中的至少一个与其相应的内部区域不对齐，使得柱状微结构的列是连续的但是在内部和/ 外部区域以减少由于颗粒撞击引起的柱内的拉伸应力。

公开(公告)号：US20060204665A1

公开(公告)日：2006-09-14

申请号：US11075799

申请日：2005-03-10

申请人： Matthew Buczek ,  Andrew Skoog ,  Jane Murphy ,  Brian Hazel

发明人： Matthew Buczek ,  Andrew Skoog ,  Jane Murphy ,  Brian Hazel

IPC分类号： B05D1/04 ,  B05D5/00

CPC分类号： C04B28/34 ,  C03C1/008 ,  C03C8/14 ,  C03C2207/00 ,  C03C2207/04 ,  C04B28/24 ,  C04B2111/00525 ,  C04B2111/90 ,  C09D5/084 ,  C23C4/123 ,  C23C22/74 ,  C23C26/02 ,  C23C28/022 ,  C23C28/027 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  F01D5/288 ,  F05D2230/90 ,  C04B14/34

摘要： A composition comprising a liquid mixture having: a corrosion resistant metal particulate component comprising aluminum-containing metal particulates, wherein the aluminum-containing metal particulates have a phosphate and/or silica-containing insulating layer; a glass-forming binder component; and a liquid carrier component. Also disclosed is a method comprising the following steps: (a) providing an article comprising a metal substrate; (b) imparting to the metal substrate an electrical charge; and (c) electrostatically applying a liquid coating composition to the electrically charged metal substrate, wherein the liquid coating composition comprises a liquid mixture having: a corrosion resistant metal particulate component comprising aluminum-containing metal particulates having a phosphate and/or silica-containing insulating layer; glass-forming binder component; and a liquid carrier component.

公开(公告)号：US20060115661A1

公开(公告)日：2006-06-01

申请号：US11001884

申请日：2004-12-01

申请人： Brian Hazel ,  Mark Gorman ,  Bangalore Nagaraj

发明人： Brian Hazel ,  Mark Gorman ,  Bangalore Nagaraj

IPC分类号： B32B15/04 ,  B32B9/00 ,  B32B19/00

CPC分类号： C23C26/00 ,  C23C28/3215 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/284 ,  F01D5/288 ,  F05D2230/31 ,  F05D2260/95 ,  Y02T50/67 ,  Y02T50/6765

摘要： According to an embodiment of the invention, an article of manufacture for use in a gas turbine engine is disclosed. The article comprises a part having a surface covered with a ceramic thermal barrier coating. The thermal barrier coating has an outer surface covered with a sacrificial phosphate coating, wherein the sacrificial phosphate coating reacts with contaminant compositions to prevent contaminant infiltration into the thermal barrier coating.

摘要翻译： 根据本发明的实施例，公开了一种用于燃气涡轮发动机的制品。 该制品包括具有覆盖有陶瓷热障涂层的表面的部分。 热障涂层具有被牺牲磷酸盐涂层覆盖的外表面，其中牺牲磷酸盐涂层与污染物组合物反应以防止污染物渗透到热障涂层中。

公开(公告)号：US20070141367A1

公开(公告)日：2007-06-21

申请号：US11306125

申请日：2005-12-16

申请人： Ramgopal Darolia ,  Brian Hazel

发明人： Ramgopal Darolia ,  Brian Hazel

IPC分类号： B32B15/04

CPC分类号： C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  Y10T428/12951

摘要： A thermal barrier coating (TBC) for a component intended for use in a hostile environment, such as a component of a gas turbine engine. The TBC exhibits improved impact and erosion resistance as a result of being a composite material consisting essentially of particles of a ceramic reinforcement material dispersed in a ceramic matrix material. The ceramic reinforcement material has a yield strength greater than the ceramic matrix material at about 1100° C., and the particles of the ceramic reinforcement material have an average maximum dimension of greater than five micrometers.

摘要翻译： 用于在敌对环境中使用的组件的热障涂层（TBC），例如燃气涡轮发动机的部件。 作为基本上由分散在陶瓷基体材料中的陶瓷增强材料的颗粒组成的复合材料，TBC显示出改善的耐冲击性和耐腐蚀性。 陶瓷增强材料在约1100℃下的屈服强度大于陶瓷基体材料，并且陶瓷增强材料的颗粒的平均最大尺寸大于5微米。

公开(公告)号：US20050053467A1

公开(公告)日：2005-03-10

申请号：US10655835

申请日：2003-09-05

申请人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  Robert Zimmerman ,  Bangalore Nagaraj ,  Brian Hazel ,  Nripendra Das

发明人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  Robert Zimmerman ,  Bangalore Nagaraj ,  Brian Hazel ,  Nripendra Das

IPC分类号： C23C10/02 ,  C23C16/16 ,  C23C16/20 ,  F01D5/28 ,  F01D5/14

CPC分类号： F01D5/288 ,  C23C10/02 ,  C23C16/16 ,  C23C16/20 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/67

摘要： A turbine engine rotor component, such as a compressor or turbine disk or seal element, is protected from corrosion by depositing an aluminum or chromium coating on the component. The deposition can be performed by a vapor deposition process, such as metal organic chemical vapor deposition (MOCVD), to a coating thickness of from about 0.2 to about 50 microns, typically from about 0.5 to about 3 microns. In one embodiment, the method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; and flowing a tri-alkyl aluminum or chromium carbonyl coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum or chromium coating on the surface of the component. The coated component is then heated in a nonoxidizing atmosphere to a specified temperature to form an aluminide or chromide coating on the surface. The coated component is typically then heated or maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the surface of the component.

公开(公告)号：US20070128447A1

公开(公告)日：2007-06-07

申请号：US11293448

申请日：2005-12-02

申请人： Brian Hazel ,  Lawrence Kool

发明人： Brian Hazel ,  Lawrence Kool

IPC分类号： B05D3/02 ,  B05D1/02

CPC分类号： C23C26/00 ,  C23C28/027 ,  C23C28/028 ,  Y02T50/67 ,  Y02T50/6765

摘要： A corrosion resistant coating for engine components such as turbine disks, turbine seal elements and turbine shafts. This coating may also find application to other turbine components that are subjected to high temperatures and corrosive environments, such as turbine components located within or on the boundary of the gas fluid flow path, including for example turbine blades, turbine vanes, liners and exhaust flaps. The corrosion resistant coating of the present invention in service on a gas turbine component includes a glassy ceramic matrix wherein the glassy matrix is silica-based and particles selected from the group consisting of refractory oxide particles, MCrAlX particles and combinations of these particles, substantially uniformly distributed within the matrix. The refractory oxide and/or the MCrAlX provides the coating with corrosion resistance. Importantly the coating of the present invention has a coefficient of thermal expansion (CTE) greater than alumina. The CTE of the coating is sufficiently close to the substrate material, that is, the component to which it is applied, such that the coating does not spall after frequent engine cycling at elevated temperature

摘要翻译： 发动机部件如涡轮盘，涡轮密封元件和涡轮轴的耐腐蚀涂层。 该涂层还可以应用于经受高温和腐蚀性环境的其它涡轮机部件，例如位于气体流体流路的边界内或其上的涡轮机部件，包括例如涡轮机叶片，涡轮叶片，衬管和排气翼 。 在燃气轮机部件上使用的本发明的耐腐蚀涂层包括玻璃质陶瓷基体，其中玻璃质基质是基于二氧化硅的，并且选自由耐火氧化物颗粒，MCrAlX颗粒和这些颗粒的组合组成的组的颗粒，基本均匀 分布在矩阵内。 难熔氧化物和/或MCrAlX为涂层提供耐腐蚀性。 重要的是，本发明的涂层具有比氧化铝大的热膨胀系数（CTE）。 涂层的CTE足够接近基材，即其所施加的组分，使得涂层在高温下经常发动机循环后不会分散

公开(公告)号：US20050255329A1

公开(公告)日：2005-11-17

申请号：US10843966

申请日：2004-05-12

申请人： Brian Hazel

发明人： Brian Hazel

IPC分类号： B32B15/04 ,  C23C4/10 ,  C23C14/06 ,  C23C14/32 ,  C23C16/00 ,  C23C30/00 ,  F01D5/28

CPC分类号： F01D5/288 ,  C23C14/0021 ,  C23C14/0617 ,  C23C14/325 ,  F05D2230/90 ,  Y02T50/67

摘要： According to an embodiment of the invention, a turbine engine rotor component comprises a base metal substrate; and an oxidation and corrosion resistant metal nitride or metal carbide overlay coating applied directly on the base metal substrate of the turbine engine rotor component.

摘要翻译： 根据本发明的实施例，涡轮发动机转子部件包括基底金属基板; 以及直接施加在涡轮发动机转子部件的基底金属基底上的抗氧化和腐蚀的金属氮化物或金属碳化物覆盖涂层。

公开(公告)号：US20050138805A1

公开(公告)日：2005-06-30

申请号：US10747458

申请日：2003-12-29

申请人： Brian Hazel ,  Eva Lanman ,  Joseph Heaney ,  Michael Weimer

发明人： Brian Hazel ,  Eva Lanman ,  Joseph Heaney ,  Michael Weimer

IPC分类号： C09D1/00 ,  C09D1/02 ,  C09D4/00 ,  C09D5/18 ,  F01D5/28 ,  F01D25/00 ,  B23P6/00 ,  B23K9/04

CPC分类号： F01D5/286 ,  C09D1/00 ,  C09D1/02 ,  C09D5/18 ,  F01D5/288 ,  F01D25/007 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/611 ,  Y02T50/67 ,  Y10T29/49318 ,  Y10T29/49746 ,  Y10T29/49885

摘要： The present invention is a process for applying oxide paint as a touch-up paint for an oxide-based corrosion inhibiting coating with at least one imperfection region. Such oxide-based corrosion inhibiting coatings are applied on superalloy components used for moderately high temperature applications, such as the superalloy components found in the high-pressure turbine (HPT) section of a gas turbine engine, including turbine disks and seals. However, during the application of oxide-based corrosion inhibiting coatings, imperfection regions sometimes occur, exposing the superalloy substrate beneath the oxide-based corrosion inhibiting coating. Such imperfection regions can include a spalled region, a scratched region, a chipped region, an uncoated region, or combinations thereof. The process of the present invention is useful where aircraft engine components have been treated with a corrosion inhibiting three-layer paint oxide system comprising chromia and alumina, but where a small imperfection region or regions within the layer oxide system are present after initial manufacture, refurbishment, or repair of the component.

摘要翻译： 本发明是一种将氧化物涂料用作具有至少一个不完美区域的氧化物基腐蚀抑制涂层的上涂料的方法。 这种基于氧化物的腐蚀抑制涂层被应用于用于适度高温应用的超级合金部件上，例如在包括涡轮盘和密封件的燃气涡轮发动机的高压涡轮机（HPT）部分中发现的超级合金部件。 然而，在施加氧化物基腐蚀抑制涂层期间，有时会出现缺陷区域，使超合金基底暴露于氧化物基腐蚀抑制涂层之下。 这样的缺陷区域可以包括剥落区域，划痕区域，切屑区域，未涂覆区域或其组合。 本发明的方法在飞机发动机部件已经被包括氧化铬和氧化铝的腐蚀抑制三层涂料氧化物体系处理但在初始制造，翻新之后存在于氧化层系中的小缺陷区域或区域的情况下是有用的 ，或修理组件。

公开(公告)号：US20060222884A1

公开(公告)日：2006-10-05

申请号：US11094351

申请日：2005-03-31

申请人： Bangalore Nagaraj ,  Brian Hazel ,  Jeffrey Pfaendtner

发明人： Bangalore Nagaraj ,  Brian Hazel ,  Jeffrey Pfaendtner

IPC分类号： B32B19/00 ,  B32B9/00

CPC分类号： C23C18/1283 ,  C23C18/1208 ,  C23C18/1225 ,  C23C18/1241 ,  C23C18/1254 ,  C23C26/00 ,  C23C28/042 ,  C23C28/322 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/28 ,  F01D5/286 ,  F01D5/288 ,  F01D25/007 ,  F05D2230/314 ,  F05D2230/90 ,  F05D2260/95 ,  F05D2300/21 ,  F05D2300/2118 ,  F05D2300/611 ,  Y02T50/67

摘要： An article comprising a turbine component other than an airfoil having a metal substrate and a ceramic corrosion resistant coating overlaying the metal substrate. This coating has a thickness up to about 5 mils (127 microns) and comprises a ceramic metal oxide selected from the group consisting of zirconia, hafnia and mixtures thereof. This coating can be formed by a method comprising the following steps: (a) providing a turbine component other than an airfoil comprising the metal substrate; (b) providing a gel-forming solution comprising a ceramic metal oxide precursor; (c) heating the gel-forming solution to a first preselected temperature for a first preselected time to form a gel; (d) depositing the gel on the metal substrate; and (e) firing the gel at a second preselected temperature above the first preselected temperature to form the ceramic corrosion resistant coating comprising the ceramic metal oxide. This coating can also be formed by alternative methods wherein a ceramic composition comprising the ceramic metal oxide is deposited by physical vapor deposition on the metal substrate to provide a strain-tolerant columnar structure, or is thermal sprayed on the metal substrate.

摘要翻译： 一种制品，其包括除了具有金属基底的翼型以外的涡轮机部件和覆盖所述金属基底的陶瓷耐腐蚀涂层。 该涂层具有高达约5密耳（127微米）的厚度，并且包含选自氧化锆，铪和其混合物的陶瓷金属氧化物。 该涂层可以通过包括以下步骤的方法形成：（a）提供除了包括金属基底的翼型之外的涡轮机部件; （b）提供包含陶瓷金属氧化物前体的凝胶形成溶液; （c）将凝胶形成溶液加热至第一预选温度，以第一预选时间形成凝胶; （d）将凝胶沉积在金属基底上; 和（e）在高于第一预选温度的第二预选温度下烧制凝胶以形成包含陶瓷金属氧化物的陶瓷耐腐蚀涂层。 该涂层也可以通过替代方法形成，其中通过物理气相沉积将包含陶瓷金属氧化物的陶瓷组合物沉积在金属基底上以提供耐应变柱状结构，或者热喷涂在金属基底上。