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1. 发明授权

US11454128B2 Fairing assembly 有权
公开(公告)号：US11454128B2
公开(公告)日：2022-09-27
申请号：US16055646
申请日：2018-08-06
申请人： General Electric Company
发明人： Mark Anthony Holleran , Matthew Mark Weaver , Darrell Glenn Senile , Nicholas John Bloom
IPC分类号： F01D9/04 , F01D25/24 , F01D25/28 , F01D11/00
摘要： Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

2. 发明授权

US10801729B2 Thermally coupled CMC combustor liner 有权
公开(公告)号：US10801729B2
公开(公告)日：2020-10-13
申请号：US14791539
申请日：2015-07-06
申请人： General Electric Company
发明人： Nicholas John Bloom
IPC分类号： F23R3/00 , F23R3/60
摘要： A combustor for a gas turbine engine is provided, which includes: a CMC liner having a forward end and an aft end; an annular dome comprising a metal and defining an annular slot within its end defined between an outer arm and an inner arm; a feather seal extending from an annularly exterior surface of the annular dome to an annularly exterior surface of the liner; and a plurality of pin members. The forward end of the liner defines a plurality of fingers and a plurality of axial slots, and is fitted between the outer arm and the inner arm within the annular slot. Each pin member extending through an aperture in the feather seal, through an aperture in the outer arm of the annular dome, through an opening defined by the liner, and through an aperture in the inner arm of the annular dome.

3. 发明授权

US10168051B2 Combustor assembly for a turbine engine 有权
公开(公告)号：US10168051B2
公开(公告)日：2019-01-01
申请号：US14842867
申请日：2015-09-02
申请人： General Electric Company
发明人： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
IPC分类号： F23R3/00 , F23R3/60 , F02C3/04 , F23R3/50 , F02C3/14 , F16C29/02
摘要： A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.

4. 发明申请

US20220333778A1 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE 有权
公开(公告)号：US20220333778A1
公开(公告)日：2022-10-20
申请号：US17855905
申请日：2022-07-01
申请人： General Electric Company
发明人： Michael Alan Stieg , Nicholas John Bloom
IPC分类号： F23R3/00 , F23R3/60
摘要： A combustor assembly for a gas turbine engine includes a dome defining 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 is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.

5. 发明申请

US20190084894A1 METHODS FOR REPAIRING COMPOSITE CYLINDERS 审中-公开
公开(公告)号：US20190084894A1
公开(公告)日：2019-03-21
申请号：US15708203
申请日：2017-09-19
申请人： General Electric Company
发明人： Herbert Chidsey Roberts , Glenn Curtis Taxacher , Nicholas John Bloom , Patrick Wayne Hollingsworth
IPC分类号： C04B37/02 , C04B37/00
摘要： Methods for repairing composite cylindrical components are provided. One exemplary method for repairing a cylindrical component defining an axial direction, a radial direction, and a circumferential direction includes removing a damaged region of the cylindrical component. A flange extending from a cylindrical body of the cylindrical component is included in the damaged region. One or more arc segments that extend along the circumferential direction are connected with the existing cylindrical component. At least one of the arc segments includes a prefabricated flange. One or more plies are laid up to connect the arc segments with the existing cylindrical component to repair the damaged region of the cylindrical body and the prefabricated flange formed integrally with one of the arc segments replaces the damaged portion of the flange. Repaired cylindrical components are also provided.

6. 发明授权

US10197278B2 Combustor assembly for a turbine engine 有权
公开(公告)号：US10197278B2
公开(公告)日：2019-02-05
申请号：US14842883
申请日：2015-09-02
申请人： General Electric Company
发明人： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
IPC分类号： F23R3/00 , F23R3/50 , F23R3/60
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.

7. 发明申请

US20170059160A1 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE 审中-公开
标题翻译：用于涡轮发动机的COMBUSTOR组件
公开(公告)号：US20170059160A1
公开(公告)日：2017-03-02
申请号：US14842883
申请日：2015-09-02
申请人： General Electric Company
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。

8. 发明授权

US11859819B2 Ceramic composite combustor dome and liners 有权
公开(公告)号：US11859819B2
公开(公告)日：2024-01-02
申请号：US17451102
申请日：2021-10-15
申请人： General Electric Company
发明人： Ryan Christopher Jones , Shai Birmaher , Nicholas John Bloom , Daniel J. Kirtley , Gerardo Antonio Salazar Lois , Anquan Wang , Trevor James Hahm
IPC分类号： F23R3/00 , F23R3/60 , F02C3/04
CPC分类号： F23R3/002 , F02C3/04 , F23R3/007 , F23R3/60 , F05D2220/32 , F05D2240/35
摘要： A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

9. 发明授权

US11149646B2 Piston ring assembly for a turbine engine 有权
公开(公告)号：US11149646B2
公开(公告)日：2021-10-19
申请号：US14842954
申请日：2015-09-02
申请人： General Electric Company
发明人： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
IPC分类号： F02C7/20 , F02C7/28 , F23R3/60 , F23R3/50 , F23R3/00
摘要： A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

10. 发明申请

US20200040749A1 Fairing Assembly 审中-公开
公开(公告)号：US20200040749A1
公开(公告)日：2020-02-06
申请号：US16055646
申请日：2018-08-06
申请人： General Electric Company
发明人： Mark Anthony Holleran , Matthew Mark Weaver , Darrell Glenn Senile , Nicholas John Bloom
IPC分类号： F01D9/04 , F01D25/24 , F01D25/28 , F01D11/00
摘要： Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

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