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公开(公告)号：US20190137101A1
公开(公告)日：2019-05-09
申请号：US16231103
申请日：2018-12-21
发明人： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
摘要： A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
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公开(公告)号：US20210063016A1
公开(公告)日：2021-03-04
申请号：US16654571
申请日：2019-10-16
发明人： Michael Alan Stieg , Darrell Glenn Senile , Gregory Scott Phelps , Jeffrey Douglas Johnson , Chad Holden Sutton , Robert Andrew Stowers
摘要： A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
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公开(公告)号：US10197278B2
公开(公告)日：2019-02-05
申请号：US14842883
申请日：2015-09-02
发明人： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
摘要： A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
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公开(公告)号：US20170059160A1
公开(公告)日：2017-03-02
申请号：US14842883
申请日：2015-09-02
发明人： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
IPC分类号： F23R3/00
CPC分类号： F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00012
摘要： A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括至少部分地限定燃烧室并且在后端大致沿轴向方向的前端之间延伸的衬套。 燃烧器组件还包括环形圆顶，其包括限定用于接收衬套的前端的槽的封闭表面。 盖子定位在衬套的前端并且至少部分地定位在由环形圆顶的封闭表面限定的槽内。 盖包括被配置为接触环形圆顶的封闭表面和衬垫的前端中的至少一个的表面。 这种构造可以在衬套的前端和环形圆顶之间形成基本上气密的密封，尽管组件之间相对热膨胀。
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公开(公告)号：US20180356095A1
公开(公告)日：2018-12-13
申请号：US15450308
申请日：2017-03-06
摘要： A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an opening. The combustion section also includes a fuel nozzle extending at least partially into the opening, the fuel nozzle defining a fuel nozzle axis and a radial direction relative to the fuel nozzle axis. The fuel nozzle defines an aft end, the aft end of the fuel nozzle positioned forward of the aft surface of the heat shield along the fuel nozzle axis such that the aft end of the fuel nozzle defines a minimum separation from the aft surface of the heat shield along the fuel nozzle axis of at least about 0.15 inches.
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公开(公告)号：US10041676B2
公开(公告)日：2018-08-07
申请号：US14794016
申请日：2015-07-08
发明人： Nayan Vinodbhai Patel , Kwanwoo Kim , Chad Holden Sutton , Duane Douglas Thomsen , Craig Alan Gonyou , Harris Daniel Abramson , James A. Russo , Robert Andrew Stowers , Shanwu Wang , Anquan Wang
摘要： A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
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公开(公告)号：US20180051880A1
公开(公告)日：2018-02-22
申请号：US15239888
申请日：2016-08-18
发明人： Michael Alan Stieg , Darrell Glenn Senile , Gregory Scott Phelps , Jeffrey Douglas Johnson , Chad Holden Sutton , Robert Andrew Stowers
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/007 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018
摘要： A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
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公开(公告)号：US20170009986A1
公开(公告)日：2017-01-12
申请号：US14794016
申请日：2015-07-08
发明人： Nayan Vinodbhai Patel , Kwanwoo Kim , Chad Holden Sutton , Duane Douglas Thomsen , Craig Alan Gonyou , Harris Daniel Abramson , James A. Russo , Robert Andrews Stowers , Shanwu Wang , Anquan Wang
CPC分类号： F23R3/002 , F02C3/04 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
摘要翻译： 提供了一种用于限定轴向方向的燃气涡轮发动机的燃烧器组件。 燃烧器组件通常包括衬套，环形圆顶和偏转板。 衬垫至少部分地限定燃烧室。 环形拱顶限定第一腔并且具有多个冲击孔，并且偏转板限定锥形表面和平坦表面，其中多个冷却孔限定穿过偏转板。 环形圆顶和偏转板被定位在一起以限定通过多个冲击孔与第一空腔流体连通的第二腔。 此外，第二空腔通过多个冷却孔与燃烧室流体连通。
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