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1. 发明授权

US08484978B2 Fuel nozzle assembly that exhibits a frequency different from a natural operating frequency of a gas turbine engine and method of assembling the same 有权
标题翻译：表现出与燃气涡轮发动机的自然工作频率不同的频率的燃料喷嘴组件及其组装方法
公开(公告)号：US08484978B2
公开(公告)日：2013-07-16
申请号：US12617085
申请日：2009-11-12
申请人： Donald Mark Bailey , Scott Robert Simmons , Marcus Byron Huffman
发明人： Donald Mark Bailey , Scott Robert Simmons , Marcus Byron Huffman
IPC分类号： F02C1/00
CPC分类号： F01D25/28 , F02C7/222 , F05D2230/60 , F05D2240/128 , F23R3/286 , F23R2900/00014 , F23R2900/00018 , Y10T29/49229
摘要： A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.
摘要翻译：组装具有自然工作频率的燃气涡轮发动机的燃料喷嘴组件的方法包括提供凸缘并提供预混管。凸缘由第一合金制成，使得凸缘被配置为呈现与燃气涡轮发动机的自然工作频率不同的第一频率。预混管由第二合金制成，使得预混合管被配置为展现不同于燃气涡轮发动机的自然工作频率的第二频率。预混管连接到凸缘。

2. 发明申请

US20110107764A1 FUEL NOZZLE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME 有权
标题翻译：用于气体涡轮发动机的燃料喷嘴组件及其组装方法
公开(公告)号：US20110107764A1
公开(公告)日：2011-05-12
申请号：US12617085
申请日：2009-11-12
申请人： Donald Mark Bailey , Scott Robert Simmons , Marcus Byron Huffman
发明人： Donald Mark Bailey , Scott Robert Simmons , Marcus Byron Huffman
IPC分类号： F02C7/22 , B23P17/00
CPC分类号： F01D25/28 , F02C7/222 , F05D2230/60 , F05D2240/128 , F23R3/286 , F23R2900/00014 , F23R2900/00018 , Y10T29/49229
摘要： A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.
摘要翻译：组装具有自然工作频率的燃气涡轮发动机的燃料喷嘴组件的方法包括提供凸缘并提供预混管。凸缘由第一合金制成，使得凸缘被配置为呈现与燃气涡轮发动机的自然工作频率不同的第一频率。预混管由第二合金制成，使得预混合管被配置为展现不同于燃气涡轮发动机的自然工作频率的第二频率。预混管连接到凸缘。

3. 发明申请

US20120060504A1 APPARATUS AND METHOD FOR COOLING A COMBUSTOR 有权
标题翻译：用于冷却燃烧器的装置和方法
公开(公告)号：US20120060504A1
公开(公告)日：2012-03-15
申请号：US12880446
申请日：2010-09-13
申请人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
发明人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
IPC分类号： F02C1/00
CPC分类号： F23R3/54 , F23R3/002 , F23R3/04 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for preferentially directing fluid flow across a predetermined position of the turbulators. A method for cooling a combustion chamber includes locating a plurality of turbulators to an exterior surface of the combustion chamber and preferentially directing fluid flow across a predetermined position of the plurality of turbulators.
摘要翻译：燃烧器包括燃烧室和周向围绕燃烧室的至少一部分并限定外表面的内壁。多个紊流器位于外表面上。燃烧器还包括用于优先引导流体流过湍流器的预定位置的装置。一种用于冷却燃烧室的方法包括将多个湍流器定位到燃烧室的外表面，并且优先地引导流体流过多个湍流器中的预定位置。

4. 发明申请

US20120247120A1 APPARATUS AND METHOD FOR COOLING A COMBUSTOR 有权
公开(公告)号：US20120247120A1
公开(公告)日：2012-10-04
申请号：US13494297
申请日：2012-06-12
申请人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
发明人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
IPC分类号： F02C7/18 , F02C6/08
CPC分类号： F23R3/54 , F23R3/002 , F23R3/04 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for preferentially directing fluid flow across a predetermined position of the turbulators. A method for cooling a combustion chamber includes locating a plurality of turbulators to an exterior surface of the combustion chamber and preferentially directing fluid flow across a predetermined position of the plurality of turbulators.

5. 发明授权

US08201412B2 Apparatus and method for cooling a combustor 有权
标题翻译：用于冷却燃烧器的设备和方法
公开(公告)号：US08201412B2
公开(公告)日：2012-06-19
申请号：US12880446
申请日：2010-09-13
申请人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
发明人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
IPC分类号： F02C1/00
CPC分类号： F23R3/54 , F23R3/002 , F23R3/04 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for preferentially directing fluid flow across a predetermined position of the turbulators. A method for cooling a combustion chamber includes locating a plurality of turbulators to an exterior surface of the combustion chamber and preferentially directing fluid flow across a predetermined position of the plurality of turbulators.
摘要翻译：燃烧器包括燃烧室和周向围绕燃烧室的至少一部分并限定外表面的内壁。多个紊流器位于外表面上。燃烧器还包括用于优先引导流体流过湍流器的预定位置的装置。一种用于冷却燃烧室的方法包括将多个湍流器定位到燃烧室的外表面，并且优先地引导流体流过多个湍流器中的预定位置。

6. 发明授权

US08453460B2 Apparatus and method for cooling a combustor 有权
标题翻译：用于冷却燃烧器的设备和方法
公开(公告)号：US08453460B2
公开(公告)日：2013-06-04
申请号：US13494297
申请日：2012-06-12
申请人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
发明人： Saurav Dugar , Matthew P. Berkebile , Dullal Ghosh , Joseph Vincent Pawlowski , Krishnakumar Pallikara Gopalan , Marcus Byron Huffman
IPC分类号： F02C1/00
CPC分类号： F23R3/54 , F23R3/002 , F23R3/04 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for preferentially directing fluid flow across a predetermined position of the turbulators. A method for cooling a combustion chamber includes locating a plurality of turbulators to an exterior surface of the combustion chamber and preferentially directing fluid flow across a predetermined position of the plurality of turbulators.
摘要翻译：燃烧器包括燃烧室和周向围绕燃烧室的至少一部分并限定外表面的内壁。多个紊流器位于外表面上。燃烧器还包括用于优先引导流体流过湍流器的预定位置的装置。一种用于冷却燃烧室的方法包括将多个湍流器定位到燃烧室的外表面，并且优先地引导流体流过多个湍流器中的预定位置。

7. 发明申请

US20090255267A1 COMUBSTOR SEAL HAVING MULTIPLE COOLING FLUID PATHWAYS 失效
标题翻译： COMUBSTOR密封有多个冷却流体路径
公开(公告)号：US20090255267A1
公开(公告)日：2009-10-15
申请号：US12100679
申请日：2008-04-10
申请人： Wei Chen , Marcus Byron Huffman , David James Taylor
发明人： Wei Chen , Marcus Byron Huffman , David James Taylor
IPC分类号： F01D5/08 , F02C3/14 , F02C7/28
CPC分类号： F23R3/002 , F01D9/023 , F23R2900/00012
摘要： A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway. A combustor seal is located between the first combustor component and the second combustor component. The combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component. A method for cooling a first combustor component and a second combustor component is also disclosed.
摘要翻译：燃气轮机的燃烧器包括第一燃烧器部件和第二燃烧器部件。第二燃烧器部件至少部分地可插入到第一燃烧器部件中，并且第一燃烧器部件和第二燃烧器部件限定燃烧流体通路。燃烧器密封件位于第一燃烧器部件和第二燃烧器部件之间。燃烧器密封件限定在燃烧器密封件和第二燃烧器部件之间的至少一个内部冷却通路以及燃烧器密封件和第一燃烧器部件之间的至少一个外部冷却通道，用于冷却第一燃烧器部件和第二燃烧器部件。还公开了一种用于冷却第一燃烧器部件和第二燃烧器部件的方法。

8. 发明授权

US07594401B1 Combustor seal having multiple cooling fluid pathways 失效
标题翻译：具有多个冷却流体通道的燃烧器密封件
公开(公告)号：US07594401B1
公开(公告)日：2009-09-29
申请号：US12100679
申请日：2008-04-10
申请人： Wei Chen , Marcus Byron Huffman , David James Taylor
发明人： Wei Chen , Marcus Byron Huffman , David James Taylor
IPC分类号： F02C7/20
CPC分类号： F23R3/002 , F01D9/023 , F23R2900/00012
摘要： A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway. A combustor seal is located between the first combustor component and the second combustor component. The combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component. A method for cooling a first combustor component and a second combustor component is also disclosed.
摘要翻译：燃气轮机的燃烧器包括第一燃烧器部件和第二燃烧器部件。第二燃烧器部件至少部分地可插入到第一燃烧器部件中，并且第一燃烧器部件和第二燃烧器部件限定燃烧流体通路。燃烧器密封件位于第一燃烧器部件和第二燃烧器部件之间。燃烧器密封件限定在燃烧器密封件和第二燃烧器部件之间的至少一个内部冷却通路以及燃烧器密封件和第一燃烧器部件之间的至少一个外部冷却通道，用于冷却第一燃烧器部件和第二燃烧器部件。还公开了一种用于冷却第一燃烧器部件和第二燃烧器部件的方法。

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