-
公开(公告)号：US20160208631A1
公开(公告)日：2016-07-21
申请号：US14601033
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
IPC: F01D9/06
CPC classification number: F01D9/065 , F01D9/02 , F01D25/12 , Y02T50/675
Abstract: A cooling system for a turbomachine includes a vane having an outer diameter platform at one end and an inner diameter platform at another end opposite the outer diameter platform. The outer diameter platform includes outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure. The inner diameter platform is operative to be disposed on an inner diameter stationary structure. The cooling system also includes an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage. The first cross-passage defines a first outer diameter opening in the outer diameter platform. The first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane.
Abstract translation: 涡轮机的冷却系统包括叶片，叶片的一端具有外径平台，在与外径平台相对的另一端具有内径平台。 外径平台包括可操作地将叶片安装到外径静止结构的外径连接结构。 内径平台可操作地设置在内径静止结构上。 冷却系统还包括设置在外径平台和内径平台之间并限定第一横向通道的翼型件。 第一横向通道限定外径平台中的第一外径开口。 第一横向通道限定内径平台中的第一内径开口，使得第一泄漏流可以从内径平台穿过叶片通过翼型件到达外径平台，并且进入外径泄漏路径 的叶片。
-
公开(公告)号：US20160201487A1
公开(公告)日：2016-07-14
申请号：US14880620
申请日：2015-10-12
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D9/041 , F01D5/188 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/232 , F05D2230/60 , F05D2240/12 , F05D2240/126 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity.
Abstract translation: 叶片包括沿着纵向轴线从根部延伸到相对的尖端的叶片体，以及第一和第二挡板体。 叶片主体限定了前缘和后缘，以及限定在前缘，后缘，根部和尖端之间的空腔。 叶片主体包括限定在空腔内的前缘和后缘之间的至少一个叶片肋。 第一挡板体限定在空腔的前缘部分和后缘部分之一中。 第二挡板体限定在空腔的中间部分。
-
公开(公告)号：US20160186587A1
公开(公告)日：2016-06-30
申请号：US14911148
申请日：2014-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan A. Waite , Brandon W. Spangler , Steven B. Gautschi
CPC classification number: F01D9/065 , F01D5/189 , F05D2220/32 , F05D2240/126 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/204 , Y02T50/673 , Y02T50/676
Abstract: A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the airfoil section between the first inner airfoil wall surface and the second inner airfoil wall surface.
Abstract translation: 叶片结构包括具有第一内翼面壁表面和第二内翼面壁表面的翼型段。 挡板安装在第一内翼面壁表面和第二内翼面壁表面之间的翼型部分内。
-
公开(公告)号：US20160131037A1
公开(公告)日：2016-05-12
申请号：US14900730
申请日：2014-07-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Ricardo Trindade
CPC classification number: F02C7/18 , F01D5/081 , F01D5/082 , F01D5/084 , F01D5/085 , F01D5/088 , F01D9/06 , F01D9/065 , F01D25/08 , F01D25/12 , F01D25/14 , F02C3/04 , F02C6/08 , F05D2220/32 , F05D2260/205 , F05D2260/232 , F05D2270/3062 , Y02T50/676
Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.
Abstract translation: 在特征实施例中，燃气涡轮发动机具有压缩机部分，该压缩机部分具有在压缩机部分下游的下游转子和扩散器。 燃烧器在扩散器的下游接收空气。 涡轮部分具有至少一个待冷却的部件。 导管与扩散器间隔开并限定冷却气流路径。 冷却气流路径与扩散器下游的气流分离，并且通过燃烧器。 导管将冷却空气传递到要冷却的部件。
-
公开(公告)号：US20160102563A1
公开(公告)日：2016-04-14
申请号：US14893795
申请日：2014-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Dominic J. Mongillo
CPC classification number: F01D5/188 , F01D5/02 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.
Abstract translation: 公开了一种燃气涡轮发动机，其包括压缩机部和涡轮部。 燃气涡轮发动机包括燃气涡轮发动机部件，其具有提供燃气涡轮发动机部件的外表面的第一壁和与第一壁间隔开的第二壁。 第一壁是暴露于燃气涡轮发动机的核心流动路径的气体通道壁。 第二个墙是非气道壁。 在第二壁和第一壁之间设置冷却通道。 第二壁具有设置在其上的跳闸条。
-
Patent Agency Ranking
公开(公告)号：US20140090384A1
公开(公告)日：2014-04-03
申请号：US13629705
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John McBrien , Brandon W. Spangler , Matthew A. Devore
CPC classification number: F01D5/186 , F05D2250/14 , F05D2250/141 , F05D2250/314 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.
Abstract translation: 燃气涡轮发动机部件包括具有外表面的结构。 冷却孔从冷却通道延伸到外表面，以在外表面上形成大致圆形形状的出口区域。 燃气涡轮发动机包括压缩机部和涡轮部。 在压缩机和涡轮机部分之间提供燃烧器。 压缩机和涡轮机部分中的至少一个中的部件具有外表面。 薄膜冷却孔从冷却通道延伸到外表面以提供基本上圆形的出口区域。 一种加工薄膜冷却孔的方法包括提供具有内部冷却通道和外部表面的部件，从外表面到内部冷却通道加工薄膜冷却孔，以在外部表面上提供基本上圆形的出口区域。
-
公开(公告)号：US11952911B2
公开(公告)日：2024-04-09
申请号：US16683640
申请日：2019-11-14
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack , JinQuan Xu
IPC: F01D5/18
CPC classification number: F01D5/18 , F05D2220/32 , F05D2240/304 , F05D2260/22141
Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.
-
公开(公告)号：US11781439B2
公开(公告)日：2023-10-10
申请号：US16571678
申请日：2019-09-16
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Brandon W. Spangler , Lane Thornton
CPC classification number: F01D11/006 , F01D11/005 , F01D25/246 , F05D2240/11 , F05D2240/57 , F05D2250/182 , Y02T50/60
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
-
公开(公告)号：US11480059B2
公开(公告)日：2022-10-25
申请号：US16545417
申请日：2019-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.
-
公开(公告)号：US11149550B2
公开(公告)日：2021-10-19
申请号：US16270080
申请日：2019-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , David R. Pack
Abstract: A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.
-
-
-
-
-
-
-
-
-
Search Results
194
records
(took 0.02 seconds)
