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公开(公告)号：US10208602B2
公开(公告)日：2019-02-19
申请号：US14697329
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Ryan Alan Waite , Peter Balawajder , Benjamin F. Hagan
Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
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公开(公告)号：US20180355731A1
公开(公告)日：2018-12-13
申请号：US16049987
申请日：2018-07-31
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Dominic J. Mongillo, JR.
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.
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公开(公告)号：US10138750B2
公开(公告)日：2018-11-27
申请号：US15071439
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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公开(公告)号：US10132184B2
公开(公告)日：2018-11-20
申请号：US15071467
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan
Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls, with the radially-extending sidewalls and the radially inner surface defining a pocket. A rail shield has radially-extending walls that line the radially-extending sidewalls. A spring is configured to bias the rail shield radially inward.
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公开(公告)号：US09927123B2
公开(公告)日：2018-03-27
申请号：US14517962
申请日：2014-10-20
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan
Abstract: A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages.
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Patent Agency Ranking
公开(公告)号：US20180066532A1
公开(公告)日：2018-03-08
申请号：US15810279
申请日：2017-11-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
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公开(公告)号：US20170268368A1
公开(公告)日：2017-09-21
申请号：US15071467
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan
CPC classification number: F01D11/08 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2260/231 , F05D2260/30 , F05D2300/6033 , Y02T50/672 , Y02T50/675
Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls, with the radially-extending sidewalls and the radially inner surface defining a pocket. A rail shield has radially-extending walls that line the radially-extending sidewalls. A spring is configured to bias the rail shield radially inward.
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公开(公告)号：US20160230596A1
公开(公告)日：2016-08-11
申请号：US15022943
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite
CPC classification number: F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.
Abstract translation: 燃气涡轮发动机部件具有从外平台径向向内延伸到内平台的翼型件。 中心通道形成在翼型内，并具有用于接收冷却空气的入口端。 内平台中的出口端将冷却空气输送到下游使用。 翼型件具有抽吸壁和压力壁，并且在从前缘到后缘的轴向方向上延伸。 吸力皮芯位于中央通道和吸壁之间。 压力皮芯位于中央通道和压壁之间。
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公开(公告)号：US20160208618A1
公开(公告)日：2016-07-21
申请号：US14600048
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Dominic J. Mongillo, JR.
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.
Abstract translation: 机翼包括具有平台前端和后端，侧面以及内外表面的平台。 翼面部分从平台的内表面向外延伸。 机翼部分包括翼型件的前端和后端以及连接翼型件前端和后端的侧壁。 该平台包括一个冷却通道，该冷却通道在前部位置具有一个入口，在该平台后端具有一个出口槽，以及一个从入口延伸到出口槽的中间通道部分。 中间通道部分包括供给出口槽的公共歧管区域。
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公开(公告)号：US20160061112A1
公开(公告)日：2016-03-03
申请号：US14837398
申请日：2015-08-27
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Allen Waite
CPC classification number: F02C7/18 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/04 , F05D2220/32 , F05D2260/202 , Y02T50/676
Abstract: a gas turbine engine structure includes a body radially spanning an inner portion and an outer portion. The structure body includes a first passage interior to the structure body. The first passage includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage is also included interior to the structure. The second passage is approximately aligned with the first passage, and is disposed between the first passage and one of the first surface and the second surface of the structure. The second passage insulates the first passage from heat transfer through one of the first surface and the second surface.
Abstract translation: 燃气涡轮发动机结构包括径向跨越内部部分和外部部分的主体。 结构体包括在结构体内部的第一通道。 第一通道包括在结构的径向向外边缘和径向向内边缘中的一个上的第一开口，以及结构的径向向外边缘和径向向内边缘中的另一个的第二开口。 第二个通道也包括在结构的内部。 第二通道与第一通道大致对准，并且设置在第一通道和结构的第一表面和第二表面中的一个之间。 第二通道将第一通道隔离通过第一表面和第二表面之一的热传递。
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