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1. 发明授权

US08893382B2 Combustion system and method of assembling the same 有权
标题翻译：燃烧系统及其组装方法
公开(公告)号：US08893382B2
公开(公告)日：2014-11-25
申请号：US13249868
申请日：2011-09-30
申请人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
发明人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
IPC分类号： B23P17/00 , F23R3/50 , F23R3/00 , F23R3/60
CPC分类号： F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
摘要： A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
摘要翻译：一种组装燃气涡轮发动机的燃烧系统的方法包括提供燃烧室框架，内壳结构和外壳结构。该方法还包括将燃烧室框架安装在内壳结构和外壳结构之间，使得燃烧室框架联接到内壳结构和外壳结构。

2. 发明申请

US20130081270A1 COMBUSTION SYSTEM AND METHOD OF ASSEMBLING THE SAME 有权
标题翻译：燃烧系统及其组装方法
公开(公告)号：US20130081270A1
公开(公告)日：2013-04-04
申请号：US13249868
申请日：2011-09-30
申请人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe
发明人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe
IPC分类号： B23P17/00 , F02C3/14
CPC分类号： F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
摘要： A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
摘要翻译：一种组装燃气涡轮发动机的燃烧系统的方法包括提供燃烧室框架，内壳结构和外壳结构。该方法还包括将燃烧室框架安装在内壳结构和外壳结构之间，使得燃烧室框架联接到内壳结构和外壳结构。

3. 发明授权

US06568079B2 Methods for replacing combustor liner panels 有权
公开(公告)号：US06568079B2
公开(公告)日：2003-05-27
申请号：US09878848
申请日：2001-06-11
申请人： Gilbert Farmer , David Bruce Patterson , Steven Allen Stiverson , James Michael Caldwell , Edward John Emilianowicz , Jeffrey Michael Martini
发明人： Gilbert Farmer , David Bruce Patterson , Steven Allen Stiverson , James Michael Caldwell , Edward John Emilianowicz , Jeffrey Michael Martini
IPC分类号： B23P1500
CPC分类号： B23P6/005 , B23P2700/13 , F23R3/002 , F23R3/08 , F23R2900/00005 , F23R2900/00016 , Y02T50/67 , Y02T50/675 , Y10T29/49318 , Y10T29/49346 , Y10T29/49721 , Y10T29/4973 , Y10T29/49737
摘要： A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor.

4. 发明授权

US06345441B1 Method of repairing combustion chamber liners 失效
标题翻译：修理燃烧室衬套的方法
公开(公告)号：US06345441B1
公开(公告)日：2002-02-12
申请号：US09618379
申请日：2000-07-18
申请人： Gilbert Farmer , James Michael Caldwell , Steven Allen Stiverson , David Bruce Patterson , Edward John Emilianowicz
发明人： Gilbert Farmer , James Michael Caldwell , Steven Allen Stiverson , David Bruce Patterson , Edward John Emilianowicz
IPC分类号： B23P1500
CPC分类号： B23P6/005 , B23P2700/13 , F23R3/002 , F23R2900/00019 , Y10T29/49318 , Y10T29/4932 , Y10T29/49737
摘要： A method of repairing an annular transpiration cooled liner for a combustion chamber of a gas turbine engine. An annular portion of the liner including a damaged region is removed from between an upstream section and a downstream section of the liner. Sheet metal is formed into an annular replacement section having at least one axial seam extending between an upstream end and a downstream end of the replacement section. The replacement section is sized and shaped similarly to the removed annular portion of the liner. The upstream end of the formed annular section is joined to the upstream section of the liner and the downstream end of the formed annular section is joined to the downstream section of the liner.
摘要翻译：一种修复用于燃气涡轮发动机的燃烧室的环形蒸发冷却衬套的方法。包括受损区域的衬垫的环形部分从衬套的上游部分和下游部分之间移除。钣金形成为具有在更换部分的上游端和下游端之间延伸的至少一个轴向接缝的环形更换部分。替换部分的尺寸和形状类似于衬垫的移除的环形部分。形成的环形部分的上游端连接到衬套的上游部分，并且所形成的环形部分的下游端连接到衬套的下游部分。

5. 发明申请

US20080010992A1 Method and apparatus to facilitate reducing NOx emissions in turbine engines 有权
标题翻译：有助于减少涡轮发动机中NOx排放的方法和装置
公开(公告)号：US20080010992A1
公开(公告)日：2008-01-17
申请号：US11590178
申请日：2006-10-31
申请人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
发明人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
IPC分类号： F02C1/00
CPC分类号： F23R3/06 , Y02T50/675
摘要： A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.
摘要翻译：提供一种用于制造燃气轮机的燃烧器衬套的方法。该方法包括提供包括多个周向延伸的面板的环形壳体，其中多个周向延伸的面板包括位于壳体的上游端的第一面板和位于第一面板的下游和邻近第一面板的第二面板。所述方法还包括在所述第一面板中形成多个初级稀释孔并在所述第二面板中形成多个次级稀释孔，其中所述初级和次级稀释孔构造成将稀释空气排放到所述壳体中。

6. 发明授权

US06427435B1 Retainer segment for swirler assembly 有权
标题翻译：旋流器组件保持器段
公开(公告)号：US06427435B1
公开(公告)日：2002-08-06
申请号：US09575415
申请日：2000-05-20
申请人： David Bruce Patterson , Thomas Anthony Leen
发明人： David Bruce Patterson , Thomas Anthony Leen
IPC分类号： F23R314
CPC分类号： F23R3/14 , F23C7/004 , Y02T50/675
摘要： A retainer segment is provided for a swirler assembly having first and second members, such as a primary and secondary swirler or a swirler body and floating ferrule, disposed in sliding engagement with each other. The two members are maintained in sliding engagement by two of the retainer segments which are joined to the second member and engage the first member. Each retainer segment is an arcuate member defining inner and outer curved edges and first and second ends. Each end has a concave cutout formed therein to reduce weld joint and bending stresses that occur from the forced vibration of the retainer segments.
摘要翻译：为具有第一和第二构件的旋转器组件提供保持器段，所述第一和第二构件例如初级和次级旋流器或旋流器本体和浮动套圈彼此滑动配合设置。两个构件通过两个保持器段保持滑动接合，该保持器段连接到第二构件并与第一构件接合。每个保持器段是限定内弯曲边缘和外弯曲边缘以及第一和第二端部的弧形构件。每个端部具有形成在其中的凹形切口以减少由保持器节段的强制振动发生的焊接接头和弯曲应力。

7. 发明授权

US07900457B2 Method and apparatus to facilitate reducing NOx emissions in turbine engines 有权
标题翻译：有助于减少涡轮发动机中NOx排放的方法和装置
公开(公告)号：US07900457B2
公开(公告)日：2011-03-08
申请号：US11590178
申请日：2006-10-31
申请人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
发明人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/06 , Y02T50/675
摘要： A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.
摘要翻译：提供一种用于制造燃气轮机的燃烧器衬套的方法。该方法包括提供包括多个周向延伸的面板的环形壳体，其中多个周向延伸的面板包括位于壳体的上游端的第一面板和位于第一面板的下游和邻近第一面板的第二面板。所述方法还包括在所述第一面板中形成多个初级稀释孔并在所述第二面板中形成多个次级稀释孔，其中所述初级和次级稀释孔构造成将稀释空气排放到所述壳体中。

8. 发明授权

US07775050B2 Method and apparatus for reducing stresses induced to combustor assemblies 有权
标题翻译：用于减少引起燃烧器组件的应力的方法和装置
公开(公告)号：US07775050B2
公开(公告)日：2010-08-17
申请号：US11590234
申请日：2006-10-31
申请人： David Bruce Patterson , Kelley Parker Brown , Robert Paul Czachor , Grzegorz Mlynski
发明人： David Bruce Patterson , Kelley Parker Brown , Robert Paul Czachor , Grzegorz Mlynski
IPC分类号： F02C7/20
CPC分类号： F02K3/06 , F01D9/023 , F02C3/14
摘要： A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.
摘要翻译：提供一种组装用于涡轮发动机的燃烧器的方法。该方法包括提供至少一个支撑腿，在支撑腿中形成至少一个开口，其中至少一个开口具有仅由多个非线性段限定的周界，并且将支撑腿联接到燃烧器。

9. 发明申请

US20090142548A1 AIR COOLED GAS TURBINE COMPONENTS AND METHODS OF MANUFACTURING AND REPAIRING THE SAME 审中-公开
标题翻译：空气冷却气体涡轮机组件及其制造和修理方法
公开(公告)号：US20090142548A1
公开(公告)日：2009-06-04
申请号：US11926986
申请日：2007-10-29
申请人： David Bruce Patterson , John Starkweather , Thomas Holland , Thomas Tomlinson
发明人： David Bruce Patterson , John Starkweather , Thomas Holland , Thomas Tomlinson
IPC分类号： B32B3/10 , B05D3/12 , B32B43/00
CPC分类号： F01D25/12 , C23C4/01 , C23C4/02 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/005 , F01D5/288 , F01D9/023 , F23M2900/05004 , F23R3/007 , F23R3/06 , Y02T50/67 , Y02T50/675 , Y02T50/6765 , Y10T428/24322
摘要： A component suitable for use in a gas turbine engine. The component includes a substrate defining a surface of the component and has a first surface and a second surface. At least one aperture extends through the substrate from the first surface to the second surface, and has a first open area. The component has a first coating on at least one of the first surface and the second surface adjacent to the at least one aperture. The component also has a second coating overlying the first coating adjacent to the at least one aperture, such that at least a portion of the first coating is exposed adjacent to the at least one aperture. The first coating defines a second open area which is smaller than the first open area. In another aspect, a method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area. In a further aspect, a method of repairing a component suitable for use in a gas turbine engine, the method comprising the steps of removing coatings from the component, repairing any defects in the substrate of the component, and applying coatings as described herein.
摘要翻译：适用于燃气涡轮发动机的部件。该部件包括限定部件的表面并具有第一表面和第二表面的基板。至少一个孔从第一表面延伸穿过基底到第二表面，并且具有第一开口区域。所述部件在与所述至少一个孔相邻的所述第一表面和所述第二表面中的至少一个上具有第一涂层。所述部件还具有覆盖邻近所述至少一个孔的所述第一涂层的第二涂层，使得所述第一涂层的至少一部分暴露于所述至少一个孔附近。第一涂层限定比第一开口区域小的第二开口区域。在另一方面，一种制造适用于燃气涡轮发动机的部件的方法，包括以下步骤：从具有第一表面和第二表面的基底形成所述部件，从所述第一表面形成穿过所述基板的至少一个孔到具有第一开放区域的第二表面，向邻近所述至少一个孔的所述第一表面和所述第二表面中的至少一个施加第一涂层，所述孔至少部分地被所述第一涂层阻挡，施加第二涂层至少邻近于所述至少一个孔的所述第一涂层，所述孔至少部分地被所述第二涂层阻挡，并且从所述孔移除所述第二涂层，使所述第一涂层的大部分或全部限定为较小的第二开口区域比第一个开放区域。在另一方面，一种修复适用于燃气涡轮发动机的部件的方法，所述方法包括以下步骤：从组件去除涂层，修复部件的基底中的任何缺陷，以及如本文所述的涂覆涂层。

10. 发明申请

US20080098739A1 Method and apparatus for reducing stresses induced to combustor assemblies 有权
标题翻译：用于减少引起燃烧器组件的应力的方法和装置
公开(公告)号：US20080098739A1
公开(公告)日：2008-05-01
申请号：US11590234
申请日：2006-10-31
申请人： David Bruce Patterson , Kelley Parker Brown , Robert Paul Czachor , Grzegorz Mlynski
发明人： David Bruce Patterson , Kelley Parker Brown , Robert Paul Czachor , Grzegorz Mlynski
IPC分类号： F02C1/00
CPC分类号： F02K3/06 , F01D9/023 , F02C3/14
摘要： A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.
摘要翻译：提供一种组装用于涡轮发动机的燃烧器的方法。该方法包括提供至少一个支撑腿，在支撑腿中形成至少一个开口，其中至少一个开口具有仅由多个非线性段限定的周界，并且将支撑腿联接到燃烧器。

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