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1. 发明授权

US09021812B2 Combustor dome and heat-shield assembly 有权
标题翻译：燃烧器穹顶和隔热罩组件
公开(公告)号：US09021812B2
公开(公告)日：2015-05-05
申请号：US13560876
申请日：2012-07-27
申请人： Ronald B. Pardington , Paul Yankowich , Nagaraja S. Rudrapatna , Thomas Frank Johnson
发明人： Ronald B. Pardington , Paul Yankowich , Nagaraja S. Rudrapatna , Thomas Frank Johnson
IPC分类号： F02C1/00 , F02G3/00 , F02C7/20 , F23R3/14 , F23R3/60
CPC分类号： F23R3/14 , F23R3/60 , Y02T50/675 , Y10T29/49323
摘要： A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
摘要翻译：燃烧器穹顶和隔热罩组件包括具有穿过其中的第一开口的隔热罩。旋流器延伸穿过第一开口并捕获隔热罩。具有通过其的第二开口并具有上游侧和下游侧的圆顶。旋流器从下游侧延伸到第二开口到上游侧，以在下游侧捕获隔热罩，并且保持夹与旋流器接合以将旋流器和隔热罩固定在圆顶上。

2. 发明申请

US20140026580A1 COMBUSTOR DOME AND HEAT-SHIELD ASSEMBLY 有权
标题翻译： COMBUSTOR DOME AND HEI-SHIELD ASSEMBLY
公开(公告)号：US20140026580A1
公开(公告)日：2014-01-30
申请号：US13560876
申请日：2012-07-27
申请人： Ronald B. Pardington , Paul Yankowich , Nagaraja S. Rudrapatna , Thomas Frank Johnson
发明人： Ronald B. Pardington , Paul Yankowich , Nagaraja S. Rudrapatna , Thomas Frank Johnson
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23R3/60 , Y02T50/675 , Y10T29/49323
摘要： A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
摘要翻译：燃烧器穹顶和隔热罩组件包括具有穿过其中的第一开口的隔热罩。旋流器延伸穿过第一开口并捕获隔热罩。具有第二开口的圆顶具有上游侧和下游侧。旋流器从下游侧延伸到第二开口到上游侧，以在下游侧捕获隔热罩，并且保持夹与旋流器接合以将旋流器和隔热罩固定在圆顶上。

3. 发明申请

US20090293486A1 COMBUSTORS WITH IGNITERS HAVING PROTRUSIONS 审中-公开
标题翻译：具有突发事件的燃烧员
公开(公告)号：US20090293486A1
公开(公告)日：2009-12-03
申请号：US11925347
申请日：2007-10-26
申请人： Amy T. Hanson , Ronald B. Pardington
发明人： Amy T. Hanson , Ronald B. Pardington
IPC分类号： F02C1/00 , F02C7/264
CPC分类号： F23R3/60 , F23R3/50 , F23R2900/00012
摘要： A combustor for a gas turbine engine is provided, and includes an inner case; an outer case circumscribing the inner case and forming an annular pressure vessel therebetween; an inner liner positioned within the annular pressure vessel; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; and an igniter coupled to the outer case and extending to the outer liner such that the igniter is positioned to ignite an air and fuel mixture in the combustion chamber. The igniter includes a protrusion for coupling the igniter to the outer liner.
摘要翻译：提供一种用于燃气涡轮发动机的燃烧器，并且包括内壳体; 外壳围绕内壳并在其间形成环形压力容器; 位于所述环形压力容器内的内衬; 外衬套限定内衬，并形成具有内衬的燃烧室; 以及联接到外壳并且延伸到外衬套的点火器，使得点火器被定位成点燃燃烧室中的空气和燃料混合物。点火器包括用于将点火器耦合到外衬套的突起。

4. 发明申请

US20090090110A1 FACETED DOME ASSEMBLIES FOR GAS TURBINE ENGINE COMBUSTORS 审中-公开
标题翻译：用于气体涡轮发动机燃烧器的面对的组件
公开(公告)号：US20090090110A1
公开(公告)日：2009-04-09
申请号：US11867195
申请日：2007-10-04
申请人： Ronald B. Pardington , Jonathan N. Kettinger
发明人： Ronald B. Pardington , Jonathan N. Kettinger
IPC分类号： F23R3/42
CPC分类号： F23R3/10 , Y02T50/675
摘要： A dome assembly for a gas turbine engine includes a plurality of faceted segments and a plurality of openings. The plurality of faceted segments are coupled together to form a dome structure that is configured to be disposed between an inner liner and an outer liner that circumscribes the inner liner. The plurality of openings are each opening formed within a respective faceted segment, and are configured to at least partially house an atomizer therein. Each faceted segment is at least substantially flat.
摘要翻译：用于燃气涡轮发动机的圆顶组件包括多个小平面段和多个开口。所述多个刻面部分联接在一起以形成圆顶结构，所述圆顶结构被配置为设置在内衬和外衬上的外衬套之间。多个开口中的每一个开口形成在相应的分段内，并且构造成至少部分地将雾化器容纳在其中。每个刻面片段至少基本上平坦。

5. 发明申请

US20090084110A1 COMBUSTOR SYSTEMS WITH LINERS HAVING IMPROVED COOLING HOLE PATTERNS 有权
标题翻译：具有改进的冷却孔模式的衬管的COMBUSTOR系统
公开(公告)号：US20090084110A1
公开(公告)日：2009-04-02
申请号：US11863791
申请日：2007-09-28
申请人： Rodolphe Dudebout , Paul R. Yankowich , Frank J. Zupanc , Ronald B. Pardington
发明人： Rodolphe Dudebout , Paul R. Yankowich , Frank J. Zupanc , Ronald B. Pardington
IPC分类号： F23R3/06 , F02C3/00
CPC分类号： F23R3/06
摘要： A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction.
摘要翻译：燃烧器衬套组件包括衬套和形成在衬套中的第一组冷却孔，并且在下游方向具有增加的密度。

6. 发明授权

US07905094B2 Combustor systems with liners having improved cooling hole patterns 有权
标题翻译：具有衬垫的燃烧器系统具有改进的冷却孔模式
公开(公告)号：US07905094B2
公开(公告)日：2011-03-15
申请号：US11863791
申请日：2007-09-28
申请人： Rodolphe Dudebout , Paul R. Yankowich , Frank J. Zupanc , Ronald B. Pardington
发明人： Rodolphe Dudebout , Paul R. Yankowich , Frank J. Zupanc , Ronald B. Pardington
IPC分类号： F02C1/00
CPC分类号： F23R3/06
摘要： A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction. The first group of cooling holes include a generally circumferential first row of cooling holes, a generally circumferential second row of cooling holes immediately downstream from, consecutive to, and separated from the first row at a first distance, a generally circumferential third row of cooling holes immediately downstream from, consecutive to, and separated from the second row at a second distance, and a generally circumferential fourth row of cooling holes immediately downstream from, consecutive to, and separated from the third row at a third distance. The first distance is greater than the second distance and the third distance, and the second distance is greater than the third distance.
摘要翻译：燃烧器衬套组件包括衬套和形成在衬套中的第一组冷却孔，并且在下游方向具有增加的密度。第一组冷却孔包括大致圆周的第一排冷却孔，大致圆周的第二排冷却孔，紧邻第一排的第一排，第一排，第二排，紧邻第一排，第一排，第二排冷却孔，在第二距离处紧邻下游，连续到第二排并且与第二排分离，以及大致圆周的第四排冷却孔，紧邻第三排的第三排，连续地和从第三排分离。第一距离大于第二距离和第三距离，第二距离大于第三距离。

7. 发明授权

US07617689B2 Combustor dome assembly including retaining ring 失效
标题翻译：燃烧器圆顶组件包括固定环
公开(公告)号：US07617689B2
公开(公告)日：2009-11-17
申请号：US11367282
申请日：2006-03-02
申请人： Jurgen C. Schumacher , Frank J. Zupanc , Paul R. Yankowich , Ronald B. Pardington
发明人： Jurgen C. Schumacher , Frank J. Zupanc , Paul R. Yankowich , Ronald B. Pardington
IPC分类号： F02C7/20 , F23R3/14
CPC分类号： F02C7/20
摘要： A retaining ring is provided for use in conjunction with a carburetor assembly having a flow passage therethrough for conducting a fuel-air mixture into a combustion chamber, the carburetor assembly comprising an air flow modifier and a fuel injector receiving element adjacent thereto. The retaining ring comprises a collar configured to engage the fuel injector receiving element so as to maintain its position adjacent the air flow modifier, and a retaining portion coupled to the collar and configured to engage the air flow modifier to secure the airflow modifier to the combustion chamber. The retaining portion cooperates with the collar to form an aperture through the retaining ring for receiving the carburetor assembly.
摘要翻译：提供一个保持环，用于与具有通过其的流动通道的化油器组件一起使用，以将燃料 - 空气混合物传导到燃烧室中，化油器组件包括气流调节器和与其相邻的燃料喷射器接收元件。保持环包括被配置为接合燃料喷射器接收元件以便保持其邻近空气流量调节器的位置的轴环，以及联接到轴环并被配置为接合气流调节器以将气流调节器固定到燃烧的保持部分房间。保持部分与套环协作以形成穿过保持环的孔，用于容纳化油器组件。

8. 发明授权

US6101806A Tri-mode combustion system 有权
标题翻译：三模燃烧系统
公开(公告)号：US6101806A
公开(公告)日：2000-08-15
申请号：US143588
申请日：1998-08-31
申请人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
发明人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
IPC分类号： F02C3/13 , F02C6/16 , F02C7/268
CPC分类号： F02C6/16 , F02C3/13 , F05D2220/50 , Y02E60/15
摘要： A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet. During emergency/starting operation, the combustion chamber and turbine section receive compressed air from a stored air accumulator through a stored air inlet. During normal air breathing operation, the combustion chamber and turbine section receive compressed air from a compressor through an air breathing inlet. During bypass bleed operation, the combustion chamber and turbine section receive compressed air from the aircraft main engine through a bypass bleed air inlet. The tri-mode operation is made possible by a unique two-way bypass ring having a plurality of axial passages communicating the stored air inlet and air breathing inlet with the upstream combustor inlet and a plurality of radial passages communicating the bypass bleed inlet with the downstream combustor inlet. A valving system selectively admits compressed air into the combustor and turbine section from the stored air inlet, air breathing inlet or bypass bleed inlet depending on the mode of operation.
摘要翻译：公开了一种涡轮发动机，其能够在紧急动力模式，空气呼吸辅助动力模式和旁路出血环境控制模式下操作。在本发明的优选实施例中，发动机包括工作流体流动的压缩空气压缩机，燃烧室和动力涡轮机，用于从加热和/或压缩空气中提取机械作业。压缩机和涡轮机分别由轴连接，轴也耦合到用于提供电力的发电机和用于向飞机机舱和航空电子设备供应冷却空气的冷却涡轮机。燃烧室具有上游燃烧器入口和下游燃烧器入口，每个入口可以允许压缩空气与燃料混合以便燃烧，或者直接通到可操作地连接到动力涡轮机部分入口的燃烧室出口。在紧急/启动操作期间，燃烧室和涡轮部分通过储存的空气入口从储存的空气储存器接收压缩空气。在正常的呼吸呼吸操作期间，燃烧室和涡轮部分通过空气吸入口从压缩机接收压缩空气。在旁路泄放操作期间，燃烧室和涡轮部分通过旁路放气入口接收来自飞机主机的压缩空气。通过具有多个轴向通道的独特的双向旁路环来实现三模式操作，所述多个轴向通道将存储的空气入口和空气呼吸入口与上游燃烧器入口连通，以及多个径向通道将旁路出气口与下游燃烧器入口。阀门系统根据操作模式，从储存的空气入口，空气呼吸入口或旁路渗流入口选择性地将压缩空气进入燃烧器和涡轮机部分。

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