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公开(公告)号：US10816201B2
公开(公告)日：2020-10-27
申请号：US14913165
申请日：2014-07-11
Applicant: United Technologies Corporation
Inventor： Christopher Drake
Abstract: A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity. A method of cooling a wall assembly within a combustor for of a gas turbine engine includes directing air through a support shell and a liner panel to form a pressure drop across the support shell that is less than about 80% of a pressure drop across the combustor and to also form a pressure drop across the liner panel greater than about 20% of the pressure drop across the combustor.
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公开(公告)号：US10190425B2
公开(公告)日：2019-01-29
申请号：US14916291
申请日：2014-09-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake , Christopher B Lyons
Abstract: A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.
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公开(公告)号：US20160245518A1
公开(公告)日：2016-08-25
申请号：US15024589
申请日：2014-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake
CPC classification number: F23R3/007 , F02C7/24 , F23M5/04 , F23R3/002 , F23R3/60 , F23R2900/00017 , Y02T50/671
Abstract: A liner panel for a combustor of a gas turbine engine is provided that includes a first attachment and a second attachment that extends from a cold side of the liner panel. The first attachment is different than the second attachment. A combustor of a gas turbine engine is provided that includes an inner combustor wall assembly with an inner support shell and a multiple of inner liner panels. At least one of the multiple of inner liner panels includes a first inner attachment to the inner support shell and a second inner attachment to the inner support shell. The first inner attachment is different than, and upstream of, the second inner attachment. An outer combustor wall assembly is spaced from the inner combustor wall assembly to define an annular combustion cavity therebetween.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器的衬板，其包括从衬板的冷侧延伸的第一附接件和第二附接件。 第一附件与第二附件不同。 提供了一种燃气涡轮发动机的燃烧器，其包括具有内支撑壳体和多个内衬板的内燃机壁组件。 所述多个内衬板中的至少一个包括到所述内支撑壳体的第一内附件和所述内支撑壳体的第二内附件。 第一内附件不同于第二内附件的上游。 外部燃烧器壁组件与内部燃烧器壁组件间隔开以在它们之间限定环形燃烧腔。
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公开(公告)号：US09777634B2
公开(公告)日：2017-10-03
申请号：US14479566
申请日：2014-09-08
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Christopher B. Lyons
Abstract: A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing.
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公开(公告)号：US10598381B2
公开(公告)日：2020-03-24
申请号：US14904872
申请日：2014-05-15
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Seth A. Max , Meggan Harris
Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.
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Patent Agency Ranking
公开(公告)号：US10508808B2
公开(公告)日：2019-12-17
申请号：US14893781
申请日：2014-06-12
Applicant: United Technologies Corporation
Inventor： Christopher Drake
Abstract: A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.
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公开(公告)号：US10337354B2
公开(公告)日：2019-07-02
申请号：US14915755
申请日：2014-09-03
Applicant: United Technologies Corporation
Inventor： Christopher Drake
Abstract: A gas turbine engine includes a vane and a combustor housing that are supported relative to an engine static structure. A retaining assembly clamps the combustor housing and the vane to one another in an axial direction. A circumferential load transfer assembly circumferentially affixes the vane relative to the engine static structure. The retaining assembly is secured to the circumferential load transfer assembly.
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公开(公告)号：US20160201914A1
公开(公告)日：2016-07-14
申请号：US14913165
申请日：2014-07-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake
Abstract: A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity. A method of cooling a wall assembly within a combustor for of a gas turbine engine includes directing air through a support shell and a liner panel to form a pressure drop across the support shell that is less than about 80% of a pressure drop across the combustor and to also form a pressure drop across the liner panel greater than about 20% of the pressure drop across the combustor.
Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括至少部分地限定冲击腔的轨道。 导轨包括朝向冲击腔的凹口。 冷却用于燃气涡轮发动机的燃烧器内的壁组件的方法包括将空气引导通过支撑壳体和衬套板，以形成横跨支撑壳体的压降，其小于穿过燃烧器的压降的约80％ 并且还在衬板上形成超过燃烧器上的压降的约20％的压降。
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公开(公告)号：US20160194981A1
公开(公告)日：2016-07-07
申请号：US14915755
申请日：2014-09-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake
CPC classification number: F01D25/28 , F01D9/023 , F01D9/041 , F01D11/003 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/35 , F05D2260/30 , F05D2260/36 , F23R3/002
Abstract: A gas turbine engine includes a vane and a combustor housing that are supported relative to an engine static structure. A retaining assembly clamps the combustor housing and the vane to one another in an axial direction. A circumferential load transfer assembly circumferentially affixes the vane relative to the engine static structure. The retaining assembly is secured to the circumferential load transfer assembly.
Abstract translation: 燃气涡轮发动机包括相对于发动机静态结构支撑的叶片和燃烧器壳体。 保持组件将燃烧器壳体和叶片沿轴向方向彼此夹紧。 圆周载荷传递组件周向地相对于发动机静态结构固定叶片。 保持组件固定到周向负载传递组件。
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10.发明申请VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开VENA CONTRACTA发动机燃油涡轮增压通道公开(公告)号：US20160201908A1
公开(公告)日：2016-07-14
申请号：US14910856
申请日：2014-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake , Frank J. Cunha , Stanislav Kostka, JR. , Jonathan M. Jause , Russell B. Hanson
CPC classification number: F23R3/06 , F02C7/18 , F23R3/002 , F23R3/005 , F23R3/04 , F23R3/045 , F23R3/26 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.
Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，其包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。
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