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51. 发明授权

US08691333B2 Methods for manufacturing engine components with structural bridge devices 有权
标题翻译：用结构桥梁装置制造发动机部件的方法
公开(公告)号：US08691333B2
公开(公告)日：2014-04-08
申请号：US13171218
申请日：2011-06-28
申请人： Donald G. Godfrey , Daniel Ryan , Mark C. Morris , Vincent Chung
发明人： Donald G. Godfrey , Daniel Ryan , Mark C. Morris , Vincent Chung
IPC分类号： B05D3/00
CPC分类号： B23P15/02 , B22F3/1055 , B22F5/04 , B23K26/32 , B23K26/342 , B23K35/0244 , B23K35/30 , B23K35/3033 , B23K35/3046 , B23K35/3053 , B23K2101/001 , B23K2103/05 , B23K2103/26 , B33Y10/00 , B33Y30/00 , B33Y80/00 , Y02P10/295 , Y10T29/49229
摘要： A method is provided for manufacturing an engine component. The method includes providing a structural bridge device on a base block; forming a component portion on the structural bridge device with an additive manufacturing technique; removing the component portion from the base block and the structural bridge device; and finishing the component portion to form the engine component.
摘要翻译：提供了一种用于制造发动机部件的方法。该方法包括在基座块上提供结构桥接装置; 用添加剂制造技术在结构桥式装置上形成部件; 从所述基块和所述结构桥接装置中移除所述组件部分; 并整理组件部分以形成发动机部件。

52. 发明授权

US08668442B2 Turbine nozzles and methods of manufacturing the same 失效
标题翻译：涡轮喷嘴及其制造方法
公开(公告)号：US08668442B2
公开(公告)日：2014-03-11
申请号：US12827702
申请日：2010-06-30
申请人： Mark C. Morris , Daniel Ryan , Donald G. Godfrey , Jason Smoke
发明人： Mark C. Morris , Daniel Ryan , Donald G. Godfrey , Jason Smoke
IPC分类号： F01D9/02
CPC分类号： B23P15/04 , B33Y80/00 , F01D9/041 , F01D25/28 , F05D2260/94 , F05D2260/941 , Y02T50/67 , Y10T29/4932
摘要： A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.
摘要翻译：提供涡轮喷嘴并且包括具有第一微结构的第一环，从第一环延伸的叶片，第一环和叶片之间的第一多孔区，其比第一微结构多孔，以减弱第一微结构之间的热机械疲劳裂纹叶片和第一个环。还提供了制造涡轮喷嘴的方法。

53. 发明申请

US20130243606A1 TURBINE BLADE TIP COOLING 有权
标题翻译：涡轮叶片冷却
公开(公告)号：US20130243606A1
公开(公告)日：2013-09-19
申请号：US13419729
申请日：2012-03-14
申请人： Daniel Cregg Crites , Mark C. Morris , Steve Halfmann
发明人： Daniel Cregg Crites , Mark C. Morris , Steve Halfmann
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/20 , F05D2240/304 , F05D2240/307 , Y02T50/676
摘要： A turbine blade includes a blade portion, the blade portion comprising a tip outer wall and a trailing edge, an internal cooling circuit, the internal cooling circuit being configured for directing cooling air within the blade portion, and a tip trailing edge slot positioned adjacent to the tip outer wall and the trailing edge, the tip trailing edge slot being fluidly connected to the internal cooling circuit. The tip outer wall is recessed at the tip trailing edge slot such that the tip outer wall is not provided over the trailing edge slot, thereby allowing cooling air to flow from the cooling circuit, into the trailing edge slot, and radially over the tip outer wall.
摘要翻译：涡轮机叶片包括叶片部分，叶片部分包括尖端外壁和后缘，内部冷却回路，内部冷却回路构造成用于引导叶片部分内的冷却空气，以及尖端后缘槽，尖端外壁和后缘，尖端后缘槽流体地连接到内部冷却回路。尖端外壁在尖端后缘槽处凹陷，使得末端外壁不设置在后缘狭槽上，从而允许冷却空气从冷却回路流入后缘槽，并且径向地超过顶端外部壁。

54. 发明授权

US08506836B2 Methods for manufacturing components from articles formed by additive-manufacturing processes 有权
标题翻译：通过添加剂制造工艺形成的制品的制造方法
公开(公告)号：US08506836B2
公开(公告)日：2013-08-13
申请号：US13235210
申请日：2011-09-16
申请人： Andy Szuromi , Daniel Ryan , Donald G. Godfrey , Mark C. Morris
发明人： Andy Szuromi , Daniel Ryan , Donald G. Godfrey , Mark C. Morris
IPC分类号： C23F1/00 , C03C15/00 , C03C25/68 , C25F3/00
CPC分类号： C23C26/00 , B22F3/1055 , B22F3/15 , B22F3/24 , B22F5/04 , B22F7/06 , B29C64/00 , B29C67/0051 , B33Y30/00 , B33Y40/00 , B33Y70/00 , B33Y80/00 , C23C10/60 , F05D2230/31 , Y02P10/295
摘要： A method is provided for manufacturing a component. The method includes forming a diffusion coating on a first intermediate article formed by an additive manufacturing process. The diffusion coating is removed from the first intermediate article forming a second intermediate article having at least one enhanced surface. The diffusion coating is formed by applying a layer of coating material on at least one surface of the first intermediate article and diffusion heat treating the first intermediate article and the layer. The diffusion coating comprises a surface additive layer and a diffusion layer below the surface additive layer. The formation of the diffusion coating and removal thereof may be repeated at least once.
摘要翻译：提供了用于制造部件的方法。该方法包括在通过添加剂制造工艺形成的第一中间制品上形成扩散涂层。扩散涂层从形成具有至少一个增强表面的第二中间制品的第一中间制品中除去。通过在第一中间制品的至少一个表面上涂覆一层涂料并对第一中间制品和该层进行扩散热处理来形成扩散涂层。扩散涂层包括表面添加层和在表面添加层下面的扩散层。扩散涂层的形成和其去除可以重复至少一次。

55. 发明授权

US08444387B2 Seal plates for directing airflow through a turbine section of an engine and turbine sections 有权
标题翻译：用于引导气流通过发动机和涡轮机部分的涡轮部分的密封板
公开(公告)号：US08444387B2
公开(公告)日：2013-05-21
申请号：US12622837
申请日：2009-11-20
申请人： Mark C. Morris , Larry Barr , Paul Couey , Stuart Andrew Harman , Douglas L. Ramerth , Luis A. Tapia
发明人： Mark C. Morris , Larry Barr , Paul Couey , Stuart Andrew Harman , Douglas L. Ramerth , Luis A. Tapia
IPC分类号： B63H1/14
CPC分类号： F01D5/3015 , F01D5/082 , F05D2240/126 , Y02T50/676
摘要： A seal plate for directing an airflow includes a hub, main pumping vanes, and splitter vanes. The hub has a tubular section and an annular flange section flared outwardly relative to the tubular section to define a flow surface. The main pumping vanes are disposed circumferentially on the flow surface around the annular flange section and each has a canted section located radially inward relative to a straight section and aligned with a flow direction of the airflow. The straight section extends along a first plane including a centerline of the seal plate. The splitter vanes are disposed circumferentially on the flow surface around the annular flange section such that at least one splitter vane is disposed between the straight sections of two adjacent main pumping vanes. Each splitter vane has a length that is less than a length of each of the two adjacent main pumping vanes.
摘要翻译：用于引导气流的密封板包括轮毂，主泵叶片和分流叶片。轮毂具有管状部分和环形凸缘部分，其相对于管状部分向外张开以限定流动表面。主泵叶片周向设置在环形凸缘部分周围的流动表面上，并且每个具有相对于直线部分径向向内定位并与气流的流动方向对准的倾斜部分。直线部分沿着包括密封板的中心线的第一平面延伸。分流叶片周向设置在环形凸缘部分周围的流动表面上，使得至少一个分流叶片设置在两个相邻的主泵叶片的直线部分之间。每个分流叶片的长度小于两个相邻主泵叶片中的每一个的长度。

56. 发明申请

US20130058768A1 GAS TURBINE ENGINES WITH ABRADABLE TURBINE SEAL ASSEMBLIES 有权
标题翻译：具有可拆卸涡轮密封组件的气体涡轮发动机
公开(公告)号：US20130058768A1
公开(公告)日：2013-03-07
申请号：US13224035
申请日：2011-09-01
申请人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
发明人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
IPC分类号： F01D11/00 , B21D53/84
CPC分类号： F01D11/122 , F01D11/006 , F05D2230/313 , F05D2240/55 , F05D2300/123 , Y10T29/49297
摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.
摘要翻译：燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。

57. 发明申请

US20100008760A1 GAS TURBINE ENGINE ASSEMBLIES WITH RECIRCULATED HOT GAS INGESTION 有权
标题翻译：燃气涡轮发动机组件与循环热气体吸收
公开(公告)号：US20100008760A1
公开(公告)日：2010-01-14
申请号：US12171000
申请日：2008-07-10
申请人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
发明人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
IPC分类号： F01D1/02
CPC分类号： F01D11/001 , F01D5/143 , F01D5/145 , F01D11/02 , F01D11/04 , Y02T50/673
摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.
摘要翻译：燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片路径。定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。

58. 发明授权

US06931859B2 Variable turbine cooling flow system 失效
标题翻译：可变涡轮冷却流系统
公开(公告)号：US06931859B2
公开(公告)日：2005-08-23
申请号：US10739754
申请日：2003-12-17
申请人： Peter L. Morgan , William J. Howe , Mark C. Morris , Adrian R. Allan , Donald L. Palmer
发明人： Peter L. Morgan , William J. Howe , Mark C. Morris , Adrian R. Allan , Donald L. Palmer
IPC分类号： F01D17/14 , F02C7/18 , F02C9/20 , F02C7/12
CPC分类号： F02C9/20 , F01D17/141 , F02C7/18 , F05D2240/55 , F05D2240/57 , F05D2250/61 , Y10T137/7781
摘要： Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.
摘要翻译：可以调节到燃气轮机的叶片和盘的冷却空气以提供可变的涡轮机冷却流。通过向波纹管的内部提供高压压缩机排出流，可以延伸波纹管。当波纹管内部与环境压力空气相通时，波纹管可能被压缩。波纹管的延伸/压缩将臂移动到冷却空气流动路径中的孔口上。波纹管内部的压力被计量以将臂移动至少一个孔口，从而在发动机以低功率运行时限制冷却气流。波纹管内部的压力被计量以移动臂以露出所有的槽，以在发动机以高功率运行时提供最大的冷却流量。所产生的可变冷却流系统导致在低功率下对冷却空气的需求较少，从而降低发动机燃料消耗。

59. 发明授权

US06554562B2 Combustor hot streak alignment for gas turbine engine 失效
标题翻译：燃气涡轮发动机的燃烧器热条对准
公开(公告)号：US06554562B2
公开(公告)日：2003-04-29
申请号：US09882518
申请日：2001-06-15
申请人： Rodolphe Dudebout , Mark C. Morris , Douglas P. Freiberg , Craig W. McKeever , Richard J. Musiol , Ardeshir Riahi , William J. Howe
发明人： Rodolphe Dudebout , Mark C. Morris , Douglas P. Freiberg , Craig W. McKeever , Richard J. Musiol , Ardeshir Riahi , William J. Howe
IPC分类号： F01D904
CPC分类号： F01D5/142 , F01D9/04 , Y02T50/673
摘要： A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.
摘要翻译：描述了一种降低燃气涡轮发动机的热段中的喷嘴的平均温度和最高温度的方法和装置。该方法涉及燃气涡轮发动机中的燃料喷嘴和下游涡轮喷嘴的圆周对准。这使得从每个燃料喷嘴出现的热条之间位于相同数量的涡轮喷嘴翼型之间。用于降低喷嘴翼型的耐用性的最严苛的操作条件是产生热操作温度条件的操作条件。通过识别通过下游喷嘴翼型件的温度曲线，静态阶段的翼型件可以围绕附接到燃气涡轮发动机的壳体的环的圆周选择性间隔开，以避免高温暴露于翼型件。该方法和装置通过允许热气体区域穿过两个相邻翼型之间的路径来减轻翼型件中最差的氧化和热机械疲劳损伤。

60. 发明授权

US09085980B2 Methods for repairing turbine components 有权
标题翻译：修理涡轮机组件的方法
公开(公告)号：US09085980B2
公开(公告)日：2015-07-21
申请号：US13041113
申请日：2011-03-04
申请人： Don Mittendorf , Daniel Ryan , Donald G. Godfrey , Mark C. Morris , Harry Kington
发明人： Don Mittendorf , Daniel Ryan , Donald G. Godfrey , Mark C. Morris , Harry Kington
IPC分类号： F01D5/00 , F01D5/20 , B22F3/105 , B23P6/00 , B22F7/06
CPC分类号： B23P6/00 , B22F3/1055 , B22F2003/1057 , B22F2007/068 , B23P6/007 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y50/00 , B33Y80/00 , F01D5/005 , F01D5/20 , F05D2230/31 , F05D2240/304 , F05D2240/307 , Y02P10/295 , Y02T50/67 , Y02T50/673 , Y10T29/49318
摘要： A method is provided for repairing a turbine component with a distressed portion. The method includes machining the turbine component into a first intermediate turbine article such that the distressed portion is removed; and rebuilding the first intermediate turbine article into the turbine component with an additive manufacturing process.
摘要翻译：提供了一种用于修复具有凹陷部分的涡轮机部件的方法。所述方法包括将所述涡轮机部件加工成第一中间涡轮机制品，使得所述受压部分被移除; 并且通过添加剂制造方法将第一中间涡轮机物品重建成涡轮机部件。

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