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1. 发明授权

US08716623B2 Core runout ceiling for turbine components 有权
标题翻译：涡轮机组件的核心跳动天花板
公开(公告)号：US08716623B2
公开(公告)日：2014-05-06
申请号：US13020845
申请日：2011-02-04
申请人： Paul M. Lutjen , Kevin J. Ryan , Paul S. Bean , Paul C. McClay
发明人： Paul M. Lutjen , Kevin J. Ryan , Paul S. Bean , Paul C. McClay
IPC分类号： B23K26/00 , B23K26/20
CPC分类号： B23K31/02 , B23K15/0046 , B23K26/28 , B23K33/004 , B23K2101/001 , F01D11/24 , F01D25/12 , F05D2230/237 , F05D2230/80 , F05D2240/11 , Y10T29/49318
摘要： A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed.
摘要翻译：关闭涡轮机部件中的模具塞开口的方法包括将焊接部件插入待关闭的开口中的步骤，并且邻接从开口引出的通道内的颈缩部分。对焊接部件施加热量，使得与颈部接触的焊接部件的表面液化，焊接部件粘附到颈部，封闭开口部。选择焊接构件和施加热量使得焊接构件的整体不会液化，而是保持在开口中，而不会液化。还公开了通过该方法形成的涡轮机部件。

2. 发明申请

US20120201662A1 CORE RUNOUT CEILING FOR TURBINE COMPONENTS 有权
标题翻译：涡轮机组件的核心止回式天花板
公开(公告)号：US20120201662A1
公开(公告)日：2012-08-09
申请号：US13020845
申请日：2011-02-04
申请人： Paul M. Lutjen , Kevin J. Ryan , Paul S. Bean , Paul C. McClay
发明人： Paul M. Lutjen , Kevin J. Ryan , Paul S. Bean , Paul C. McClay
IPC分类号： F04D29/58 , B23K26/00 , B23K35/14
CPC分类号： B23K31/02 , B23K15/0046 , B23K26/28 , B23K33/004 , B23K2101/001 , F01D11/24 , F01D25/12 , F05D2230/237 , F05D2230/80 , F05D2240/11 , Y10T29/49318
摘要： A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed.
摘要翻译：关闭涡轮机部件中的模具塞开口的方法包括将焊接部件插入待关闭的开口中的步骤，并且邻接从开口引出的通道内的颈缩部分。对焊接部件施加热量，使得与颈部接触的焊接部件的表面液化，焊接部件粘附到颈部，封闭开口部。选择焊接构件和施加热量使得焊接构件的整体不会液化，而是保持在开口中，而不会液化。还公开了通过该方法形成的涡轮机部件。

3. 发明授权

US09103225B2 Blade outer air seal with cored passages 有权
标题翻译：叶片外密封带芯通道
公开(公告)号：US09103225B2
公开(公告)日：2015-08-11
申请号：US13487360
申请日：2012-06-04
申请人： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
发明人： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
摘要： A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
摘要翻译：用于燃气涡轮发动机的叶片外部空气密封件包括壁，前钩和后钩。该壁在前钩和后钩之间延伸，其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。壁包括沿壁的至少一部分延伸的芯通道。芯通道径向和轴向地延伸穿过后钩的一部分，以沿着后钩的后缘与一个或多个孔连通。

4. 发明申请

US20130113168A1 METAL GASKET FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于燃气涡轮发动机的金属垫片
公开(公告)号：US20130113168A1
公开(公告)日：2013-05-09
申请号：US13289101
申请日：2011-11-04
申请人： Paul M. Lutjen , Michael S. Stevens
发明人： Paul M. Lutjen , Michael S. Stevens
IPC分类号： F16J15/02 , B23P11/00
CPC分类号： F01D11/005 , F05D2240/55 , F05D2250/71 , F16J15/0887 , Y10T29/49826
摘要： A gasket assembly for a gas turbine engine includes a seal portion defining outer surfaces for providing sealing contact and a bias portion defining inner structures that are spaced apart from the seal portion for biasing the outer surfaces into sealing contact. The gasket further includes end portions disposed at ends of the seal portion that including a material thickness greater than a thickness of the bias portion.
摘要翻译：用于燃气涡轮发动机的垫圈组件包括限定用于提供密封接触的外表面的密封部分和限定与密封部分间隔开的内部结构的偏压部分，用于将外表面偏压成密封接触。垫圈还包括设置在密封部分的端部处的端部，其包括大于偏置部分的厚度的材料厚度。

5. 发明授权

US08177492B2 Passage obstruction for improved inlet coolant filling 有权
标题翻译：通道堵塞以改善入口冷却液填充
公开(公告)号：US08177492B2
公开(公告)日：2012-05-15
申请号：US12074501
申请日：2008-03-04
申请人： James N. Knapp , Paul M. Lutjen
发明人： James N. Knapp , Paul M. Lutjen
IPC分类号： F01D5/20 , F01D11/08 , F04D29/08 , F04D29/18
CPC分类号： F01D5/18 , F01D11/08 , F05D2240/81 , Y02T50/676
摘要： A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage.
摘要翻译：冷却的燃气涡轮发动机部件包括冷却通道，与冷却剂供应源和冷却通道的第一端流动连通的一个或多个冷却入口孔以及冷却通道内的冷却剂流阻塞，该冷却通道在一个或多个冷却入口孔之间以及冷却通道的第二端，并且构造成将来自所述一个或多个冷却入口孔的冷却剂的一部分引向冷却通道的第一端。

6. 发明授权

US08128366B2 Counter-vortex film cooling hole design 有权
标题翻译：逆流膜冷却孔设计
公开(公告)号：US08128366B2
公开(公告)日：2012-03-06
申请号：US12157117
申请日：2008-06-06
申请人： Christopher W. Strock , Paul M. Lutjen
发明人： Christopher W. Strock , Paul M. Lutjen
IPC分类号： F01D5/18
CPC分类号： F23R3/002 , F01D5/186 , F05D2250/11 , F05D2250/12 , F05D2250/141 , F05D2260/2212 , F23R3/04 , F23R2900/03042
摘要： An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-generating structures. The first film cooling passage defines a first interior surface region and a second interior surface region. The first row of vortex-generating structures is located along the first interior surface region, and the second row of vortex-generating structures is located along the second interior surface region. The first and second rows of vortex-generating structures are configured to inducing a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet.
摘要翻译：用于燃气涡轮发动机的装置包括限定外表面的壁，沿着壁的外表面延伸穿过壁到第一出口的第一膜冷却通道，用于提供膜冷却，以及第一和第二排涡流发生器，生成结构。第一膜冷却通道限定第一内表面区域和第二内表面区域。涡流产生结构的第一排沿着第一内表面区域定位，第二排涡流产生结构沿着第二内表面区域定位。涡流产生结构的第一排和第二排构造成在到达第一出口之前在通过第一冷却通道的冷却流体中基本上相反的第一和第二旋转方向引起一对涡流。

7. 发明申请

US20110203286A1 3D NON-AXISYMMETRIC COMBUSTOR LINER 有权
标题翻译： 3D非轴对称配线架
公开(公告)号：US20110203286A1
公开(公告)日：2011-08-25
申请号：US12709951
申请日：2010-02-22
申请人： Joel H. Wagner , Paul M. Lutjen
发明人： Joel H. Wagner , Paul M. Lutjen
IPC分类号： F23R3/42
CPC分类号： F23R3/16 , F23C3/00 , F23R3/002 , F23R3/50
摘要： A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.
摘要翻译：具有输入端和输出端的燃烧器衬套包括环形内壁和环形外壁。内壁和外壁中的至少一个是三维轮廓。内壁和外壁形成燃烧室，其轮廓在室内形成交替的膨胀和收缩区域，使得燃烧气体在周向和轴向上流动。

8. 发明申请

US20100226762A1 Structural members in a pedestal array 有权
标题翻译：基座阵列中的结构构件
公开(公告)号：US20100226762A1
公开(公告)日：2010-09-09
申请号：US11524541
申请日：2006-09-20
申请人： Paul M. Lutjen , Gary L. Grogg
发明人： Paul M. Lutjen , Gary L. Grogg
IPC分类号： F01D25/08
CPC分类号： F01D5/187 , F01D11/08 , F01D25/12 , F05D2250/70 , F05D2260/201 , F05D2260/202 , F05D2260/2214 , F23R3/005
摘要： A turbine engine component has a flow path wall and a support wall. The turbine engine component has at least one cooling compact heat exchanger. Each cooling compact heat exchanger has a pedestal array and at least one structural member within the pedestal array for preventing modal crossing in operation range, for preventing panel bulging, and/or for connecting the flow path wall to at least one outer diameter support structure.
摘要翻译：涡轮发动机部件具有流路壁和支撑壁。涡轮发动机部件具有至少一个冷却紧凑型热交换器。每个冷却紧凑型热交换器具有基座阵列和基座阵列内的至少一个结构构件，用于防止在操作范围内的模态交叉，用于防止面板凸出，和/或用于将流路壁连接到至少一个外径支撑结构。

9. 发明授权

US07621719B2 Multiple cooling schemes for turbine blade outer air seal 有权
标题翻译：涡轮叶片外部空气密封的多个冷却方案
公开(公告)号：US07621719B2
公开(公告)日：2009-11-24
申请号：US11240192
申请日：2005-09-30
申请人： Paul M. Lutjen , Gary Grogg , Christopher Joe
发明人： Paul M. Lutjen , Gary Grogg , Christopher Joe
IPC分类号： F01D11/08
CPC分类号： F01D9/06 , F05D2240/11 , F05D2260/20
摘要： A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.
摘要翻译：叶片外部空气密封件具有多个不同的冷却回路方案。优选地，使用紧凑的热交换器结构，并且可以沿着叶片外部空气密封件对特定位置单独地定制。作为示例，在燃烧产物和后缘处的冷却空气之间存在比在前缘处发现的更大的压力比。本发明通过利用在后缘具有比接近前缘使用的冷却方案具有更大压降的冷却方案来利用这种区别。

10. 发明授权

US09550230B2 Mold for casting a workpiece that includes one or more casting pins 有权
标题翻译：用于铸造包括一个或多个铸造销的工件的模具
公开(公告)号：US09550230B2
公开(公告)日：2017-01-24
申请号：US13234966
申请日：2011-09-16
申请人： Paul M. Lutjen , Christopher W. Strock
发明人： Paul M. Lutjen , Christopher W. Strock
IPC分类号： B22C9/04 , B22C9/10 , B22C9/24
CPC分类号： B22C9/04 , B22C9/108 , B22C9/24
摘要： A mold for casting a workpiece that includes a casting shell, a casting core and casting pin that supports the core within the shell. The casting shell includes an interior shell surface. The casting core is located within the shell, and includes a sidewall extending between a first core surface and a second core surface. The casting pin includes an intermediate segment connected between a first support segment and a second support segment. The intermediate segment contacts the sidewall. The first support segment extends from the first core surface to a first side of the interior shell surface. The second support segment extends from the second core surface to a second side of the interior shell surface that is opposite the first side.
摘要翻译：一种用于铸造工件的模具，其包括铸造壳体，铸造芯和铸造销，所述铸造支撑件在壳体内支撑芯部。铸造壳体包括内壳表面。铸造芯位于壳体内，并且包括在第一芯表面和第二芯表面之间延伸的侧壁。铸造销包括连接在第一支撑段和第二支撑段之间的中间段。中间部分接触侧壁。第一支撑段从第一芯表面延伸到内壳表面的第一侧。第二支撑段从第二芯表面延伸到内壳表面的与第一侧相对的第二侧。

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