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公开(公告)号：US20190293291A1
公开(公告)日：2019-09-26
申请号：US16304497
申请日：2016-07-25
摘要： A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.
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公开(公告)号：US20180258778A1
公开(公告)日：2018-09-13
申请号：US15571139
申请日：2015-08-28
CPC分类号： F01D9/023 , F02C3/14 , F05D2240/35 , F05D2250/73
摘要： A gas turbine engine has a non-axially symmetric main duct portion (113). The non-axially symmetric main duct portion (113) may provide improved aerodynamics, heat load, structural strength and engine compactness.
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3.发明申请公开(公告)号：US20180179905A1
公开(公告)日：2018-06-28
申请号：US15736162
申请日：2015-08-06
CPC分类号： F01D9/023 , F01D25/12 , F05D2220/32 , F05D2230/23 , F05D2240/35 , F05D2250/132 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion bonded to the raised ribs and including an impingement hole (72) for each pocket of the array of pockets. The raised ribs include a thickness (104) that is less than half of a smallest dimension (96) of the pocket. The component is configured to receive combustion gases from a combustor and accelerate and deliver the combustion gases onto a first row of turbine blades without a turning vane.
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公开(公告)号：US20170227220A1
公开(公告)日：2017-08-10
申请号：US15502016
申请日：2014-08-26
发明人： Reinhard Schilp , Timothy A. Fox
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/00014 , F23R2900/03044
摘要： The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38) of the gas turbine combustor liner (34). The film cooling holes (44) extend circumferentially around the gas turbine combustor liner (34) and comprise a first set of holes (56) having a first axial row spacing X and a second set of holes (58) having a second axial row spacing X′. The second set of holes (58) is formed in the gas turbine combustor liner (34) in a downstream direction relative to the first set of holes (56). The second axial row spacing X′ is greater than the first axial row spacing X.
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公开(公告)号：US20190301738A1
公开(公告)日：2019-10-03
申请号：US16316495
申请日：2016-08-26
摘要： A combustion system in a combustion turbine engine is provided. The system may include a combustor wall fluidly coupled to receive a cross-flow of combustion products. The combustor wall may include a plurality of cooling air conduits. An injector assembly may be in fluid communication with the cooling fluid conduits to receive cooling fluid that passes through the cooling fluid conduits. Injector assembly includes means for injecting a flow of the cooling fluid into the combustion stage. The flow of the cooling fluid may be arranged to condition interaction of a flow of reactants injected to admix with the cross-flow of combustion products.
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公开(公告)号：US20180039254A1
公开(公告)日：2018-02-08
申请号：US15248386
申请日：2016-08-26
IPC分类号： G05B19/4099 , B33Y50/02 , G06F17/50 , B29C67/00 , F23R3/26 , F23R3/28 , B33Y10/00 , B33Y80/00
CPC分类号： G05B19/4099 , B29C67/0088 , B29L2031/7504 , B33Y10/00 , B33Y50/00 , B33Y50/02 , B33Y80/00 , F23R3/005 , F23R3/06 , F23R2900/00018 , G05B2219/49019 , G06F17/50 , G06F2217/12
摘要： Method and computer-readable model for additively manufacturing a ducting arrangement (20) in a combustion stage are provided. The ducting arrangement may include a combustor wall (40) in a combustion stage fluidly coupled to receive a cross-flow of combustion products (21). An injector assembly (12) may be in fluid communication with cooling fluid conduits (46) in the combustor wall to receive cooling fluid that passes through the cooling fluid conduits. The injector assembly may include means for injecting (24, 25, 26) a flow of the cooling fluid (22) arranged to condition interaction of a flow of reactants (19) injected with the cross-flow of combustion products. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.
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公开(公告)号：US11092338B2
公开(公告)日：2021-08-17
申请号：US16609336
申请日：2018-06-28
摘要： Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110. The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.
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8.发明申请公开(公告)号：US20200063962A1
公开(公告)日：2020-02-27
申请号：US16609336
申请日：2018-06-28
摘要： Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110. The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.
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公开(公告)号：US10443855B2
公开(公告)日：2019-10-15
申请号：US15515294
申请日：2014-10-23
摘要： A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.
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公开(公告)号：US20150047361A1
公开(公告)日：2015-02-19
申请号：US14164791
申请日：2014-01-27
发明人： Steven Williams , Timothy A. Fox , Reinhard Schilp
CPC分类号： F23R3/343 , F02C7/266 , F23D3/22 , F23D11/38 , F23D11/42 , F23D14/22 , F23D14/24 , F23D2207/00 , F23R3/36 , F23R3/38
摘要： A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body
摘要翻译： 用于燃烧器的先导燃料喷嘴包括形成沿着喷嘴的纵向中心延伸的中心体的点火器。 喷嘴尖端包括多个周向间隔开的燃料通道和多个周向隔开的空气通道，其延伸到喷嘴尖端的外侧。 中心体延伸穿过喷嘴尖端的中心，用于产生火花以点燃与喷嘴尖端相邻的燃料/空气混合物。 多个燃料管沿着中心体延伸，每个燃料管具有接合在喷嘴尖端上的出口端，用于将燃料从喷嘴尖端输送到燃烧室的燃烧室中。外套管包围燃料管并限定一个 环形空间与外套筒和中心体之间的喷嘴尖端的空气通道流体连通
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