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1. 发明申请

US20050247065A1 Rich quick mix combustion system 有权
标题翻译：丰富的快速混合燃烧系统
公开(公告)号：US20050247065A1
公开(公告)日：2005-11-10
申请号：US10839116
申请日：2004-05-04
申请人： Rodolphe Dudebout , Terrel Kuhn , Paul Yankowich , Frank Zupanc
发明人： Rodolphe Dudebout , Terrel Kuhn , Paul Yankowich , Frank Zupanc
IPC分类号： F23R3/14 , F23R3/28 , F23R3/30 , F23R3/42 , F23R3/50 , F23R3/58
CPC分类号： F23R3/286 , F23R3/30 , F23R3/50
摘要： A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.
摘要翻译：用于燃气涡轮发动机的燃烧器的预混合室包括具有预混室壁的圆柱形腔室，该圆柱形腔室具有沿着中心轴线从室出口端纵向分离的室入口端，与预混合物连通的室入口板腔室入口板具有设置在腔室入口板上的燃料喷嘴入口孔，腔室入口板还包括多个设置在腔室入口板上的旋流器通道，腔室出口端开口。还公开了一种生产涡轮机气体的方法。

2. 发明申请

US20070113557A1 System for coupling flow from a centrifugal compressor to an axial combustor for gas turbines 有权
标题翻译：用于将来自离心压缩机的流动耦合到用于燃气轮机的轴向燃烧器的系统
公开(公告)号：US20070113557A1
公开(公告)日：2007-05-24
申请号：US11286102
申请日：2005-11-22
申请人： Jurgen Schumacher , Frank Zupanc , Paul Yankowich , Rodolphe Dudebout , Michael Barton
发明人： Jurgen Schumacher , Frank Zupanc , Paul Yankowich , Rodolphe Dudebout , Michael Barton
IPC分类号： F02C7/00
CPC分类号： F23R3/04 , F23R3/50
摘要： A system is provided for aerodynamically coupling air flow from a centrifugal compressor to an axial combustor. The system includes a diffuser, a deswirl assembly, combustor inner and outer annular liners, a combustor dome, and a curved annular plate. The diffuser has an inlet that communicates with the centrifugal compressor, an outlet, and a flow path that extends radially outward. The deswirl assembly has an inlet that communicates with the diffuser outlet to receive air flowing in a radially outward direction, an outlet, and a flow path configured to redirect the air in a radially inward and axial direction through the deswirl assembly outlet at an angle toward a longitudinal axis. The curved annular plate is coupled to combustor inner and outer annular liner upstream ends to form a combustor subplenum therebetween and has a first opening and a second opening formed therein, the first opening aligned with the deswirl assembly outlet to receive air discharged therefrom.
摘要翻译：提供了一种用于将来自离心式压缩机的空气动力耦合到轴向燃烧器的系统。该系统包括扩散器，去沫组件，燃烧器内部和外部环形衬垫，燃烧器圆顶和弯曲的环形板。扩散器具有与离心式压缩机，出口和径向向外延伸的流路连通的入口。洗涤组件具有与扩散器出口连通的入口，以接收沿径向向外的方向流动的空气，出口和流路，其配置成沿着径向向内和轴向方向将空气以一定的角度朝向脱水组件出口纵轴。弯曲的环形板联接到燃烧器的内部和外部环形衬套上游端，以在它们之间形成燃烧器子板，并且具有形成在其中的第一开口和第二开口，第一开口与脱水组件出口对准以接收从其排出的空气。

3. 发明申请

US20070169484A1 Segmented effusion cooled gas turbine engine combustor 有权
标题翻译：分段喷射冷却燃气轮机发动机燃烧器
公开(公告)号：US20070169484A1
公开(公告)日：2007-07-26
申请号：US11339439
申请日：2006-01-24
申请人： Jurgen Schumacher , Frank Zupanc , Rodolphe Dudebout
发明人： Jurgen Schumacher , Frank Zupanc , Rodolphe Dudebout
IPC分类号： F23R3/04
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03041 , Y02T50/675
摘要： A combustor includes two or more sets of effusion cooling holes that extend through the inner and outer liners. Each set of effusion cooling holes includes one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows. Each effusion cooling hole is disposed at a tangential angle relative to an axial line. The tangential angle of the effusion cooling holes in each set of effusion cooling holes gradually transitions from a substantially transverse tangential angle in each initial row to a substantially axial tangential angle in each final row.
摘要翻译：燃烧器包括两组或多组延伸穿过内衬和外衬的积液冷却孔。每套排出冷却孔包括一排或多排初始排出的冷却孔，设置在一个或多个初始行下游的一排或多排排出的冷却孔，以及设置在初始和最后一行。每个排出冷却孔相对于轴线设置成切线角。每组排出冷却孔中的排出冷却孔的切向角逐渐从每个初始行中的基本上横向的切向角逐渐转变到每个最后一行的基本轴向的切向角。

4. 发明申请

US20060272335A1 Advanced effusion cooling schemes for combustor domes 失效
公开(公告)号：US20060272335A1
公开(公告)日：2006-12-07
申请号：US11146595
申请日：2005-06-07
申请人： Jurgen Schumacher , Frank Zupanc , Rodolphe Dudebout
发明人： Jurgen Schumacher , Frank Zupanc , Rodolphe Dudebout
IPC分类号： F23R3/04
CPC分类号： F23R3/50 , F23R3/12 , Y02T50/675
摘要： A cooling scheme for a dome comprises an effusion array drilled directly through a single walled dome. In one embodiment, the layout of the holes comprises two regions, a region close to the fuel injector where the holes follow a tangential path around the injector, and a second region where the direction of the holes is radially outward from the injector axis. A film of cooling air may be applied on the interior side of the combustor dome via an air swirler, which projects air radially outward from the injector axis. The first series of cooling holes supplement this air supply so that cooling efficacy is extended along the dome surface and is directed in a counter-rotating manner with respect to the main air swirler. The second series of dome cooling holes infuse further cooling flux that reduces the temperature in the corner regions between fuel injectors.

5. 发明申请

US20050076650A1 Auxiliary power unit having a rotary fuel slinger 有权
标题翻译：辅助动力装置具有旋转燃料抛油环
公开(公告)号：US20050076650A1
公开(公告)日：2005-04-14
申请号：US10837194
申请日：2004-04-30
申请人： Rodolphe Dudebout , David Edmonds , Frank Zupanc , Roger DeRudder , Mario Scaini , Victor Reyes
发明人： Rodolphe Dudebout , David Edmonds , Frank Zupanc , Roger DeRudder , Mario Scaini , Victor Reyes
IPC分类号： F23R3/38 , F23R3/52 , F23R3/54 , F02C7/00
CPC分类号： F23R3/38 , F05B2220/50 , F23R3/52 , F23R3/54
摘要： An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous “fuel sheet.” As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.
摘要翻译：辅助动力单元（APU）包括旋转燃料抛油环和单线轴两级涡轮机。旋转燃料抛油环接受来自涡轮机的旋转驱动力和来自燃料源的燃料供给。旋转燃料喷射器将燃料喷射到燃烧器中作为连续的“燃料板”。结果，燃烧器内的燃料混合和雾化得到改善，这减少了排放和模式因素，这反过来又增加了涡轮机寿命。

6. 发明申请

US20070214791A1 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：US20070214791A1
公开(公告)日：2007-09-20
申请号：US11367282
申请日：2006-03-02
申请人： Jurgen Schumacher , Frank Zupanc , Paul Yankowich , Ronald Pardington
发明人： Jurgen Schumacher , Frank Zupanc , Paul Yankowich , Ronald Pardington
IPC分类号： F02C1/00 , F02C7/20
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。

7. 发明申请

US20050257530A1 Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions 有权
标题翻译：用于减少燃气轮机燃烧器废气排放的燃料空气混合装置
公开(公告)号：US20050257530A1
公开(公告)日：2005-11-24
申请号：US10850871
申请日：2004-05-21
申请人： Frank Zupanc , Paul Yankowich
发明人： Frank Zupanc , Paul Yankowich
IPC分类号： F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23R3/286 , Y02T50/675
摘要： A fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream from the fuel injector and a second swirler wherein the second swirler is located downstream from the fuel injector. The plurality of discrete plain jet orifices are situated between the highly swirling airstreams generated by the two radial swirlers. The distributed injection of the fuel between two highly swirling airstreams results in rapid and effective mixing to the desired fuel-air ratio and prevents the formation of local hot spots in the combustor primary zone. A combustor and a gas turbine engine comprising the fuel-air mixer of the present invention are also provided as well as a method using the fuel-air mixer of the present invention.
摘要翻译：提供一种用于燃气轮机的燃烧室的燃料空气混合器。燃料空气混合装置包括具有多个离散的平面喷射孔的环形燃料喷射器，第一旋流器，其中第一旋流器位于燃料喷射器的上游，以及第二旋流器，其中第二旋流器位于燃料喷射器的下游。多个离散的平面喷射孔位于由两个径向旋流器产生的高旋涡气流之间。燃料在两个高旋涡气流之间的分布式喷射导致快速且有效地混合到所需的燃料空气比并防止在燃烧器主区域中形成局部热点。还提供了包括本发明的燃料 - 空气混合器的燃烧器和燃气涡轮发动机以及使用本发明的燃料 - 空气混合器的方法。

8. 发明申请

US20050132716A1 Reduced exhaust emissions gas turbine engine combustor 有权
标题翻译：减少废气排放燃气轮机发动机燃烧器
公开(公告)号：US20050132716A1
公开(公告)日：2005-06-23
申请号：US10746654
申请日：2003-12-23
申请人： Frank Zupanc , Paul Yankowich
发明人： Frank Zupanc , Paul Yankowich
IPC分类号： F23R3/28 , F23R3/34 , F23R3/14
CPC分类号： F23R3/343 , F23R3/286
摘要： A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas emissions during engine operation. The plurality of main fuel injector assemblies are arranged in a substantially circular pattern of a first radius, and each includes an outlet port having a first divergence angle. The plurality of pilot fuel injector assemblies are arranged in a substantially circular pattern of a second radius. Each pilot fuel injector assembly is disposed between at least two main fuel injector assemblies, and each includes an outlet port having a second divergence angle.
摘要翻译：燃气涡轮发动机燃烧器包括多个主燃料喷射器组件和多个引燃燃料喷射器组件，其布置和构造成在发动机运转期间减少废气排放。多个主燃料喷射器组件布置成具有第一半径的大致圆形图案，并且每个包括具有第一发散角的出口。多个先导燃料喷射器组件布置成第二半径的大致圆形图案。每个引燃燃料喷射器组件设置在至少两个主燃料喷射器组件之间，并且每个包括具有第二发散角的出口。

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