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公开(公告)号：US09869473B2
公开(公告)日：2018-01-16
申请号：US14750543
申请日：2015-06-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ahmed Mostafa Elkady , Allen Michael Danis , Eric Matthew Roberson , Mark Anthony Mueller , George Moertle , Shui-chi Li
CPC classification number: F23R3/005 , F23R3/002 , F23R3/50 , F23R2900/03041 , F23R2900/03042
Abstract: A gas turbine engine combustor conical-flat heat shield includes an annular conical section extending upstream from and being integral with a flat section with a flat downstream facing surface which may be generally perpendicular to or canted with respect to a centerline. The flat section includes radially outer and inner edges at least one of which is circular and circumscribed about a centerline and circumferentially spaced apart clockwise and counter-clockwise radial edges having an origin on the centerline. A gas turbine engine combustor includes conical-flat heat shields in one or more circular rows arranged in a non-symmetrical or asymmetrical pattern. Two or more groups (A, B, C) of the conical-flat heat shields in the circular rows may be mounted on a domeplate and one or more of the conical-flat heat shields is different in one or more of the groups (A, B, C).
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Patent Agency Ranking
公开(公告)号：US20170067635A1
公开(公告)日：2017-03-09
申请号：US14849552
申请日：2015-09-09
Applicant: General Electric Company
Inventor： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
CPC classification number: F23R3/002 , F04D29/542 , F23R3/04 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F23R3/50 , F23R3/54 , Y02T50/675
Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.
Abstract translation: 一种包括环形燃烧器的系统，其具有围绕轴线周向设置的第一衬套壁，围绕第一衬里壁周向设置的燃烧室和围绕燃烧室周向设置的第二衬套壁。 环形燃烧器被配置成将下游方向的燃烧气体流引导通过燃烧室远离头端朝向涡轮机。 该系统还包括供应通道，其构造成将来自压缩机的流体流供应到燃烧室。 供给通道具有流路结构，其具有将流体流从压缩机排出方向转动到与燃烧气体流动的下游方向大致相反的上游侧的转向部。
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公开(公告)号：US20160298847A1
公开(公告)日：2016-10-13
申请号：US14680995
申请日：2015-04-07
Applicant: General Electric Company
Inventor： Quoc Hoai Nguyen , Kwanwoo Kim , Whitney Epperson , Patrick Edward Pastecki , Mark Anthony Mueller
IPC: F23R3/28
CPC classification number: F23R3/28 , F01N1/02 , F23M20/005 , F23R3/002 , F23R2900/00013 , F23R2900/00014
Abstract: A system includes a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber. The system also includes a resonator configured to receive at least a portion of the fluid flow. The resonator comprises a frequency adjuster configured to change an attenuation frequency of the resonator.
Abstract translation: 一种系统包括具有燃烧室和燃烧器供给通道的燃烧器，燃烧器供应通道构造成将流体流供应到燃烧室中。 该系统还包括构造成接收流体流的至少一部分的谐振器。 谐振器包括被配置为改变谐振器的衰减频率的频率调节器。
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公开(公告)号：US10088165B2
公开(公告)日：2018-10-02
申请号：US14680995
申请日：2015-04-07
Applicant: General Electric Company
Inventor： Quoc Hoai Nguyen , Kwanwoo Kim , Whitney Epperson , Patrick Edward Pastecki , Mark Anthony Mueller
Abstract: A system includes a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber. The system also includes a resonator configured to receive at least a portion of the fluid flow. The resonator comprises a frequency adjuster configured to change an attenuation frequency of the resonator.
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公开(公告)号：US20170067639A1
公开(公告)日：2017-03-09
申请号：US14849564
申请日：2015-09-09
Applicant: General Electric Company
Inventor： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
CPC classification number: F02C3/14 , F02C7/22 , F05D2260/30 , F23R3/04 , F23R3/283 , F23R3/50 , Y02T50/675
Abstract: A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a rotational axis of a gas turbine engine, and an axis of the combustion chamber is acutely angled relative to the rotational axis. The system also includes a holder coupled to the housing and extending through the head end chamber in an axial direction relative to the axis of the combustion chamber. The holder includes a first receptacle configured to hold a first fuel nozzle, and the holder comprises a first fuel passage extending to the first receptacle.
Abstract translation: 系统包括环形燃烧器，其具有围绕燃烧室上游的头端室设置的壳体。 环形燃烧器被构造成围绕燃气涡轮发动机的旋转轴线周向延伸，并且燃烧室的轴线相对于旋转轴线成锐角。 该系统还包括联接到壳体并且相对于燃烧室的轴线在轴向方向上延伸穿过头端室的保持器。 保持器包括构造成保持第一燃料喷嘴的第一容器，并且保持器包括延伸到第一容器的第一燃料通道。
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公开(公告)号：US10465907B2
公开(公告)日：2019-11-05
申请号：US14849552
申请日：2015-09-09
Applicant: General Electric Company
Inventor： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
IPC: F23R3/04 , F23R3/00 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F04D29/54 , F23R3/50 , F23R3/54
Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.
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