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公开(公告)号：US11454128B2
公开(公告)日：2022-09-27
申请号：US16055646
申请日：2018-08-06
Applicant: General Electric Company
Abstract: 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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公开(公告)号：US10801729B2
公开(公告)日：2020-10-13
申请号：US14791539
申请日：2015-07-06
Applicant: General Electric Company
Inventor： Nicholas John Bloom
Abstract: 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.
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公开(公告)号：US10168051B2
公开(公告)日：2019-01-01
申请号：US14842867
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
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公开(公告)号：US11859819B2
公开(公告)日：2024-01-02
申请号：US17451102
申请日：2021-10-15
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Shai Birmaher , Nicholas John Bloom , Daniel J. Kirtley , Gerardo Antonio Salazar Lois , Anquan Wang , Trevor James Hahm
CPC classification number: F23R3/002 , F02C3/04 , F23R3/007 , F23R3/60 , F05D2220/32 , F05D2240/35
Abstract: 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.
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公开(公告)号：US11149646B2
公开(公告)日：2021-10-19
申请号：US14842954
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20200040749A1
公开(公告)日：2020-02-06
申请号：US16055646
申请日：2018-08-06
Applicant: General Electric Company
Abstract: 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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公开(公告)号：US20170058778A1
公开(公告)日：2017-03-02
申请号：US14842954
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
Abstract translation: 提供一种燃气涡轮发动机，其具有燃烧部分，其具有在前端和后端之间延伸的衬套。 结构构件定位在燃烧部分的至少一部分中或周围。 此外，活塞环保持器在第一端处被附接到结构构件并且在第二端处靠近衬套的后端定位。 活塞环保持器是双金属构件，其包括由第一材料形成的第一部分和由第二材料形成的第二部分。 第一材料的热膨胀系数不同于第二材料的热膨胀系数。
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公开(公告)号：US12158087B2
公开(公告)日：2024-12-03
申请号：US17744973
申请日：2022-05-16
Applicant: General Electric Company
Abstract: 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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公开(公告)号：US20220333778A1
公开(公告)日：2022-10-20
申请号：US17855905
申请日：2022-07-01
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Nicholas John Bloom
Abstract: 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.
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公开(公告)号：US20190084894A1
公开(公告)日：2019-03-21
申请号：US15708203
申请日：2017-09-19
Applicant: General Electric Company
Inventor： Herbert Chidsey Roberts , Glenn Curtis Taxacher , Nicholas John Bloom , Patrick Wayne Hollingsworth
Abstract: 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.
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