-
公开(公告)号：US20160153660A1
公开(公告)日：2016-06-02
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.
Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括围绕旋流器中心纵向轴线限定的旋流器螺纹部分的旋流器外部主体。 用于燃气涡轮发动机的燃烧器的隔板支撑壳包括旋流器凸台，其具有围绕旋流器中心纵向轴线限定的凸起螺纹部分。 燃气涡轮发动机的燃烧器包括具有旋流器凸台的隔板支撑壳体。 燃烧器还包括旋流器，其可以围绕旋流器中心纵向轴线限定的螺纹接口安装到旋流器凸台。
-
公开(公告)号：US20160123592A1
公开(公告)日：2016-05-05
申请号：US14897725
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake , Frank J Cunha , Stanislav Kostka
CPC classification number: F23R3/002 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
Abstract translation: 为燃气涡轮发动机的燃烧器提供衬套面板。 衬板包括多个传热增强器。 多个传热增强器中的至少一个包括凹陷，其中凹陷包括穿过衬垫板的至少一个通道的入口。
-
13.发明申请公开(公告)号：US20150068210A1
公开(公告)日：2015-03-12
申请号：US14479566
申请日：2014-09-08
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Christopher B. Lyons
IPC: F02C7/22
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.
Abstract translation: 用于燃气涡轮发动机的切向机载喷射器组件包括包括增压室的环形壳体。 多个离散管流体地连接到集气室，并且被配置为向环形壳体提供冷却流体。
-
公开(公告)号：US10352566B2
公开(公告)日：2019-07-16
申请号：US14896576
申请日：2014-04-14
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Stanislav Kostka, Jr. , Frank J. Cunha
Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.
-
公开(公告)号：US10088166B2
公开(公告)日：2018-10-02
申请号：US14904490
申请日：2014-05-15
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Seth A. Max , Meggan Harris
Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.
-
Patent Agency Ranking
公开(公告)号：US10088161B2
公开(公告)日：2018-10-02
申请号：US15038906
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Stanislav Kostka, Jr. , Frank J. Cunha
Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.
-
公开(公告)号：US20170159935A1
公开(公告)日：2017-06-08
申请号：US15038906
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F23R3/002 , F01D25/12 , F02C7/18 , F05D2220/323 , F05D2230/60 , F05D2240/35 , F05D2260/201 , F05D2260/31 , F16B33/004 , F23R3/005 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.
-
18.发明申请CONDUCTIVE PANEL SURFACE COOLING AUGMENTATION FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开燃气轮机发动机导电面板冷却补给公开(公告)号：US20160370008A1
公开(公告)日：2016-12-22
申请号：US14893819
申请日：2014-06-13
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Stanislav Kostka, Jr.
CPC classification number: F23R3/002 , F02C3/04 , F05D2220/32 , F05D2230/31 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/221 , F05D2300/611 , F23M2900/05004 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675 , Y02T50/6765
Abstract: A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side of the substrate of a material different than a material of the substrate. A wall assembly for use in a combustor of a gas turbine engine includes a shell with a multiple of impingement flow passages; and a liner panel mounted to the shell, where the panel includes a convective feature which faces the shell. A method of cooling a liner panel for a combustor section of a gas turbine engine includes directing an impingement flow towards a convective feature of a liner panel; and directing an effusion flow through the liner panel.
Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括具有热侧和冷侧的衬底; 在基板的热侧和冷侧中的至少一个上的粘合涂层; 以及在衬底的冷侧与不同于衬底的材料的材料的对流特征。 用于燃气涡轮发动机的燃烧器的壁组件包括具有多个冲击流动通道的壳体; 以及安装到壳体的衬板，其中面板包括面向壳体的对流特征。 一种冷却燃气涡轮发动机的燃烧器部分的衬板的方法包括将冲击流引向衬板的对流特征; 并引导渗流流过衬板。
-
公开(公告)号：US20160215633A1
公开(公告)日：2016-07-28
申请号：US14916291
申请日：2014-09-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake , Christopher B. Lyons
CPC classification number: F01D9/041 , F01D5/187 , F01D9/065 , F01D11/005 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/35 , F23R3/04
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.
Abstract translation: 燃气涡轮发动机包括具有流体端口的发动机静态结构。 涡轮叶片相对于发动机静态结构被支撑并且包括冷却通道。 在发动机静态结构和涡轮叶片之间设置有分流器。 分流器构造成将流分配器上游的流分配成设置到流体端口的第一流体流和设置到冷却通道的第二流体流。
-
公开(公告)号：US20160169521A1
公开(公告)日：2016-06-16
申请号：US14904490
申请日：2014-05-15
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Seth A. MAx , Meggan Harris
CPC classification number: F23R3/28 , B23P19/04 , F02C7/22 , F02C7/2365 , F23R3/10 , F23R3/14 , F23R3/60 , F23R2900/00012 , Y02T50/671 , Y02T50/675
Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.
Abstract translation: 为燃气涡轮发动机提供旋流器。 旋流器包括具有螺纹部分的旋流器主体和可操作以径向向外弯曲的周向布置的凸片的多个。 周向布置的突片的多个从螺纹部分径向偏移。
-
-
-
-
-
-
-
-
-
Search Results
21
records
(took 0.014 seconds)
