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1. 发明申请

US20050229600A1 Methods and apparatus for fabricating gas turbine engine combustors 审中-公开
标题翻译：制造燃气轮机发动机燃烧器的方法和装置
公开(公告)号：US20050229600A1
公开(公告)日：2005-10-20
申请号：US10826432
申请日：2004-04-16
申请人： David Kastrup , Jeffrey Martini , Douglas Fortuna , Timothy Held , Shaun De Vane , James Cooper
发明人： David Kastrup , Jeffrey Martini , Douglas Fortuna , Timothy Held , Shaun De Vane , James Cooper
IPC分类号： F23R3/14 , F23R3/22
CPC分类号： F23R3/14 , F23D2211/00
摘要： A method facilitates fabricating a gas turbine engine combustor. The method comprises coupling a venturi to a primary swirler, and coupling the venturi to a secondary swirler such that a gap is defined between a portion of the venturi and a portion of one of the primary swirler and the secondary swirler.
摘要翻译：一种方法有助于制造燃气涡轮发动机燃烧器。该方法包括将文丘里管连接到初级旋流器，以及将文丘里管连接到次级旋流器，使得在文丘里管的一部分与初级旋流器和次级旋流器之一的部分之间限定间隙。

2. 发明申请

US20060042253A1 Methods and apparatus for reducing gas turbine engine emissions 有权
公开(公告)号：US20060042253A1
公开(公告)日：2006-03-02
申请号：US10931550
申请日：2004-09-01
申请人： Douglas Fortuna , Timothy Held , David Kastrup
发明人： Douglas Fortuna , Timothy Held , David Kastrup
IPC分类号： F02C7/22
CPC分类号： F23L7/002 , F23D11/24 , F23D17/002 , F23R3/36
摘要： A method enables a gas turbine engine to be assembled. The method comprises coupling a fuel nozzle within the engine to inject fuel into the engine, wherein the fuel nozzle includes three independent injection circuits arranged such that the second injection circuit is between the first and third injection circuits, coupling a liquid fuel source to a first injection circuit defined within the nozzle and including an annular discharge opening, and coupling a water source to one of the second injection circuit and the third injection circuits such that the water source is coupled in flow communication to an annular discharge opening.

3. 发明申请

US20070095071A1 APPARATUS FOR ASSEMBLING GAS TURBINE ENGINE COMBUSTORS 审中-公开
标题翻译：装配燃气轮机发动机的装置
公开(公告)号：US20070095071A1
公开(公告)日：2007-05-03
申请号：US11564099
申请日：2006-11-28
申请人： David Kastrup , Stephen Furbish
发明人： David Kastrup , Stephen Furbish
IPC分类号： F23R3/14
CPC分类号： F23R3/283 , F23R3/60 , F23R2900/00017
摘要： A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture to at least one swirler, coupling the assembly fixture to the spectacle plate such that the swirler is maintained in alignment with respect to the spectacle plate during assembly of the combustor, and attaching the swirler to the spectacle plate.
摘要翻译：用于组装燃气涡轮发动机燃烧器的方法有助于减少组装所需的成本和时间。燃烧器包括眼镜板，多个旋流器和多个偏转板。该方法包括将组装夹具连接到至少一个旋流器，将组装夹具耦合到眼镜板，使得在组装燃烧器期间旋流器相对于眼镜板保持对准，并将旋流器附接到眼镜板。

4. 发明申请

US20050191516A1 Method for applying or repairing thermal barrier coatings 审中-公开
标题翻译：涂覆或修复热障涂层的方法
公开(公告)号：US20050191516A1
公开(公告)日：2005-09-01
申请号：US11113197
申请日：2005-04-25
申请人： Bangalore Nagaraj , Eva Lanman , Deborah Schorr , Thomas Tomlinson , Raymond Heidorn , David Kastrup , Craig Young
发明人： Bangalore Nagaraj , Eva Lanman , Deborah Schorr , Thomas Tomlinson , Raymond Heidorn , David Kastrup , Craig Young
IPC分类号： C23C4/10 , C23C4/00 , C23C4/02 , C23C28/00 , B32B15/10
CPC分类号： C23C4/00 , C23C4/02 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , F01D5/005 , F01D5/288 , F05D2230/312 , Y10T29/49318 , Y10T428/12618 , Y10T428/12736
摘要： A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.
摘要翻译：将热障涂层施加到金属基底上的方法，或者将先前通过物理气相沉积施加的热障涂层修复到覆盖金属基底的下面的铝化物扩散涂层。处理铝化物扩散涂层以使其更容易接受等离子体喷涂覆盖合金粘合涂层的粘附。然后将覆盖合金粘合涂层材料等离子体喷涂在经处理的铝化物扩散涂层上以形成覆盖合金粘合涂层。将陶瓷热障涂层材料等离子体喷涂在覆盖合金粘合涂层上以形成热障涂层。在该方法的修复实施例中，首先从下面的铝化物扩散涂层去除物理气相沉积涂覆的热障涂层。

5. 发明申请

US20070028620A1 Free floating mixer assembly for combustor of a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的燃烧器的自由浮动混合器组件
公开(公告)号：US20070028620A1
公开(公告)日：2007-02-08
申请号：US11188482
申请日：2005-07-25
申请人： Marie McMasters , David Kastrup
发明人： Marie McMasters , David Kastrup
IPC分类号： F23R3/14
CPC分类号： F23R3/343 , F23R3/286 , F23R3/60
摘要： A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; and, a mixer assembly located upstream of and in substantial alignment with each of the openings in the dome plate, with the mixer assembly including a forward portion and an aft portion. Each mixer assembly is retained in a manner so as to be movable in a radial and axial direction without obstructing the radial sections of the dome plate. A first pair of tabs are positioned on the forward surface of the dome plate adjacent each opening and a second pair of tabs are positioned on the aft portion of each mixer assembly, wherein the dome plate tabs interface with the mixer assembly tabs to prevent rotation of each mixer assembly.
摘要翻译：一种用于燃气涡轮发动机的燃烧器圆顶组件，其具有延伸穿过其中的纵向中心线轴线，包括：环形圆顶板，其具有形成在其中的内部部分，外部部分，前表面和多个周向间隔开的开口，定义在每个相邻的开口之间; 以及混合器组件，其位于圆顶板中的每个开口的上游并与其基本对齐，其中混合器组件包括前部和后部。每个混合器组件被保持为能够在径向和轴向方向上移动，而不会妨碍圆顶板的径向部分。第一对突片位于邻近每个开口的圆顶板的前表面上，并且第二对突片定位在每个混合器组件的后部上，其中圆顶板突片与混合器组件接片接合以防止每个混合器组件。

6. 发明申请

US20050015984A1 Apparatus for assembling gas turbine engine combustors 失效
标题翻译：用于组装燃气涡轮发动机燃烧器的装置
公开(公告)号：US20050015984A1
公开(公告)日：2005-01-27
申请号：US10673875
申请日：2003-09-29
申请人： David Kastrup , Stephen Furbish
发明人： David Kastrup , Stephen Furbish
IPC分类号： F23C5/02 , F23R3/00 , B21D53/00
CPC分类号： F23R3/00 , F23C5/02 , F23R2900/00017 , Y10T29/4932 , Y10T29/49346 , Y10T29/49885 , Y10T29/49895 , Y10T29/49998
摘要： A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture to at least one swirler, coupling the assembly fixture to the spectacle plate such that the swirler is maintained in alignment with respect to the spectacle plate during assembly of the combustor, and attaching the swirler to the spectacle plate.
摘要翻译：用于组装燃气涡轮发动机燃烧器的方法有助于减少组装所需的成本和时间。燃烧器包括眼镜板，多个旋流器和多个偏转板。该方法包括将组装夹具连接到至少一个旋流器，将组装夹具耦合到眼镜板，使得在组装燃烧器期间旋流器相对于眼镜板保持对准，并将旋流器附接到眼镜板。

7. 发明申请

US20070141375A1 Braze cladding for direct metal laser sintered materials 审中-公开
标题翻译：钎焊包层直接金属激光烧结材料
公开(公告)号：US20070141375A1
公开(公告)日：2007-06-21
申请号：US11312731
申请日：2005-12-20
申请人： David Budinger , Ronald Galley , Ashwin Raghavan , David Kastrup
发明人： David Budinger , Ronald Galley , Ashwin Raghavan , David Kastrup
IPC分类号： B22F7/02
CPC分类号： B22F7/08 , B22F2998/10 , B23K1/0056 , B23K26/32 , B23K26/34 , B23K35/004 , B23K35/007 , B23K2101/001 , B23K2103/04 , B23K2103/08 , B23K2103/18 , B23K2103/26 , B23K2103/50 , B33Y40/00 , C23C24/10 , Y02P10/295 , Y10T428/12028 , Y10T428/12042 , Y10T428/12063 , Y10T428/12576 , Y10T428/12944 , Y10T428/12965 , B22F3/1055
摘要： A direct metal laser sintered material including a substrate formed from a laser sintering process, the substrate having at least one surface, and a cladding material brazed onto at least a portion of the surface.
摘要翻译：一种直接金属激光烧结材料，其包括由激光烧结工艺形成的衬底，所述衬底具有至少一个表面，以及钎焊到所述表面的至少一部分上的覆层材料。

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