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1. 发明授权

US07377746B2 Airfoil cooling circuits and method 有权
标题翻译：翼型冷却回路及方法
公开(公告)号：US07377746B2
公开(公告)日：2008-05-27
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F03D11/02
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译：公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。每个电路由单独的铸造芯形成。还公开了形成轴向堆叠的芯和翼型的方法。

2. 发明申请

US20080080979A1 AIRFOIL COOLING CIRCUITS AND METHOD 有权
标题翻译：空气冷却电路和方法
公开(公告)号：US20080080979A1
公开(公告)日：2008-04-03
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译：公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。每个电路由单独的铸造芯形成。还公开了形成轴向堆叠的芯和翼型的方法。

3. 发明申请

US20130156550A1 MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD 有权
标题翻译：低密度涡轮机安装装置
公开(公告)号：US20130156550A1
公开(公告)日：2013-06-20
申请号：US13327349
申请日：2011-12-15
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty
IPC分类号： F04D29/40
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2260/38 , Y02T50/672
摘要： A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
摘要翻译：用于燃气涡轮发动机的护罩装置包括：环形金属吊架; 设置在所述衣架内的护罩区段，包括低延展性材料并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁在相对的第一和第二端面之间延伸，壁定义了弧形内流道表面; 以及保持器，其机械地联接到所述衣架，其接合所述护罩区段，以将所述护罩区段保持在所述衣架上，同时允许所述护罩区段在径向方向上移动。

4. 发明授权

US09175579B2 Low-ductility turbine shroud 有权
标题翻译：低延性涡轮罩
公开(公告)号：US09175579B2
公开(公告)日：2015-11-03
申请号：US13402616
申请日：2012-02-22
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
IPC分类号： F01D11/08 , F01D25/24 , F01D5/28 , F01D11/24
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2250/61 , F05D2250/712 , F05D2260/38 , F05D2300/6033
摘要： A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.
摘要翻译：一种用于燃气涡轮发动机的护罩段，所述护罩段由复合材料构成，所述复合材料包括嵌入基质中的增强纤维，并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁延伸在相对的第一和第二端面之间，其中所述内壁限定弓形的内部流路表面; 并且其中复合圆角设置在第一和第二壁之间的接合处，所述复合圆角包括第一和第二部分，所述第二部分具有延伸到所述第一壁中的凹曲率。

5. 发明授权

US06554563B2 Tangential flow baffle 有权
公开(公告)号：US06554563B2
公开(公告)日：2003-04-29
申请号：US09928763
申请日：2001-08-13
申请人： Mark Eugene Noe , Toby George Darkins, Jr. , Roger Lee Doughty
发明人： Mark Eugene Noe , Toby George Darkins, Jr. , Roger Lee Doughty
IPC分类号： F01D906
CPC分类号： F01D5/189 , F05D2240/10 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.

6. 发明授权

US08777583B2 Turbine airfoil components containing ceramic-based materials and processes therefor 有权
标题翻译：含有陶瓷基材料的涡轮机翼部件及其工艺
公开(公告)号：US08777583B2
公开(公告)日：2014-07-15
申请号：US12978679
申请日：2010-12-27
申请人： Toby George Darkins, Jr. , Joshua Brian Jamison , John Peter Heyward , Chad Daniel Kleinow , Roger Lee Doughty
发明人： Toby George Darkins, Jr. , Joshua Brian Jamison , John Peter Heyward , Chad Daniel Kleinow , Roger Lee Doughty
IPC分类号： F01D5/22 , F01D5/28 , F01D9/04
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , F01D9/04 , F01D9/044 , F05D2230/21 , F05D2240/125 , F05D2300/224 , F05D2300/603 , F05D2300/6033 , F05D2300/611 , Y02T50/672
摘要： A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.
摘要翻译：包含陶瓷材料的混合涡轮机翼型部件，其中部件的详细特征由不同于陶瓷材料的材料形成，但是导致部件的陶瓷部件和非陶瓷部件的牢固的机械附接。该部件包括由陶瓷基材料形成的第一副部件和由金属材料形成的第二副部件。第一副部件具有翼型部分和零件，并且第二副部件被分开地形成并且通过将金属材料铸造在第一副部件的凸点周围而附接到第一副部件。第二子部件包括具有至少一个离轴几何特征的叶片尖端护罩部分，其导致第二子部件具有比第一子部件更复杂的几何形状。

7. 发明申请

US20130156556A1 LOW-DUCTILITY TURBINE SHROUD 有权
标题翻译：低密度涡轮SHROUD
公开(公告)号：US20130156556A1
公开(公告)日：2013-06-20
申请号：US13402616
申请日：2012-02-22
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
IPC分类号： F04D29/42
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2250/61 , F05D2250/712 , F05D2260/38 , F05D2300/6033
摘要： A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.
摘要翻译：一种用于燃气涡轮发动机的护罩段，所述护罩段由复合材料构成，所述复合材料包括嵌入基质中的增强纤维，并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁延伸在相对的第一和第二端面之间，其中所述内壁限定弓形的内部流路表面; 并且其中复合圆角设置在第一和第二壁之间的接合处，所述复合圆角包括第一和第二部分，所述第二部分具有延伸到所述第一壁中的凹曲率。

8. 发明申请

US20110189009A1 MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD 有权
标题翻译：低密度涡轮机安装装置
公开(公告)号：US20110189009A1
公开(公告)日：2011-08-04
申请号：US12696566
申请日：2010-01-29
申请人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
发明人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
IPC分类号： F02C7/20 , F01D9/04
CPC分类号： F01D25/246 , F01D11/12
摘要： A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.
摘要翻译：为具有中心轴线的燃气涡轮发动机提供涡轮机护罩装置。该装置包括：（a）环形支撑构件; （b）设置在所述支撑构件中的涡轮机罩，所述护罩是包括低延性材料并具有相对的流路和后表面以及相对的前后端的连续环; 和（c）弹簧，其安装在所述支撑构件和所述护罩之间并且布置成将所述护罩弹性地推动到所述结构构件内的同心位置。

9. 发明授权

US06340285B1 End rail cooling for combined high and low pressure turbine shroud 有权
标题翻译：用于组合的高低压涡轮机护罩的末端导轨冷却
公开(公告)号：US06340285B1
公开(公告)日：2002-01-22
申请号：US09590590
申请日：2000-06-08
申请人： Craig Alan Gonyou , Roger Lee Doughty , Monty Lee Shelton
发明人： Craig Alan Gonyou , Roger Lee Doughty , Monty Lee Shelton
IPC分类号： F04D3100
CPC分类号： F01D11/005 , F01D25/246 , F02C7/28 , F05D2240/11 , F05D2260/20 , F05D2260/202
摘要： A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.
摘要翻译：分段涡轮机冷却部件，例如用于燃气涡轮发动机的高压和低压涡轮机部分的护罩段，其可用于通过组合供应到中间体中的冷却空气向涡轮机部件的侧轨或侧板提供优先冷却沮丧者和初级密封件之间的压力空腔，然后通过下部砸痕器密封槽的底壁中的凹槽，其将空气撞击在挡板密封件下方的侧板部分。涡轮机部件的侧板具有上主要密封槽和下部盘片密封槽，其底壁具有沿着其长度的多个交替的平台和凹部，以及多个冷却空气通道，其具有出口到上述下槽中土地子组件可以由多个这样的涡轮机部件形成，其中相邻侧板的下部罢工槽的平台和凹槽的间隔交错，使得一个相邻面板的下槽的平台与另一个相邻侧面板的下槽。该子组件还具有由相应的上部和下部狭槽接收的主要和沮丧的密封件，该密封件定位在相邻面板之间的间隙中，在相邻面板之间的间隙中限定了中间压力空腔，并且在捣实器密封件下方的沟槽被消耗的冷却空气从凹部下槽。

10. 发明授权

US09726043B2 Mounting apparatus for low-ductility turbine shroud 有权
公开(公告)号：US09726043B2
公开(公告)日：2017-08-08
申请号：US13327349
申请日：2011-12-15
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty
IPC分类号： F01D11/08 , F01D25/24 , F01D11/12 , F01D11/24 , F01D5/28
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2260/38 , Y02T50/672
摘要： A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.

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