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公开(公告)号：US10012092B2
公开(公告)日：2018-07-03
申请号：US14824195
申请日：2015-08-12
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Brandon W. Spangler
CPC classification number: F01D5/187 , F01D5/147 , F01D5/188 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/2214 , F16L53/00 , Y02T50/676
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections coupled at a turn section. A baffle includes a body arranged in the second passage section to define two cooling flow paths, and a first wedge region extends from the body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the two cooling flow paths.
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公开(公告)号：US09957813B2
公开(公告)日：2018-05-01
申请号：US14766071
申请日：2014-02-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D5/187 , B22C7/06 , B22C9/103 , F01D5/284 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2240/81 , F05D2250/11 , F05D2250/185 , F05D2260/20 , F05D2300/20 , Y02T50/676
Abstract: A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.
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公开(公告)号：US20180023407A1
公开(公告)日：2018-01-25
申请号：US15708603
申请日：2017-09-19
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US20170298762A1
公开(公告)日：2017-10-19
申请号：US14615509
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US09771814B2
公开(公告)日：2017-09-26
申请号：US14641470
申请日：2015-03-09
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC classification number: F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
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Patent Agency Ranking
公开(公告)号：US09726023B2
公开(公告)日：2017-08-08
申请号：US14605366
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , Daniel A. Snyder , Jaimie Taraskevich , Di Wu
CPC classification number: F01D5/187 , F01D5/147 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/22141 , Y02T50/676
Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.
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公开(公告)号：US20170145923A1
公开(公告)日：2017-05-25
申请号：US14946279
申请日：2015-11-19
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edward F. Pietraszkiewicz
CPC classification number: F02C7/18 , F01D5/08 , F01D5/18 , F01D5/187 , F05D2230/232 , F05D2240/81 , F05D2250/185 , F05D2260/202 , F05D2260/204 , F05D2260/205 , Y02T50/672 , Y02T50/676
Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.
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公开(公告)号：US20170044907A1
公开(公告)日：2017-02-16
申请号：US14824307
申请日：2015-08-12
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D5/187 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/126 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that has an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections and a turn section that connects the first and second passage sections. A baffle is located in the second passage section and the turn section. The baffle includes a wedge region situated in at least the turn section and is oriented to either divide or join the fluid flow through the turn section.
Abstract translation: 根据本公开的示例性方面的翼型件尤其包括具有用于输送流体流动的内部通道的翼型件主体。 内部通道包括第一和第二通道部分以及连接第一和第二通道部分的转向部分。 挡板位于第二通道部分和转向部分中。 挡板包括位于至少转向部分中的楔形区域，并且被定向成将通过转向部分的流体流分开或连接。
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公开(公告)号：US20170044906A1
公开(公告)日：2017-02-16
申请号：US14824195
申请日：2015-08-12
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Brandon W. Spangler
CPC classification number: F01D5/187 , F01D5/147 , F01D5/188 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/2214 , F16L53/00 , Y02T50/676
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections coupled at a turn section. A baffle includes a body arranged in the second passage section to define two cooling flow paths, and a first wedge region extends from the body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the two cooling flow paths.
Abstract translation: 根据本公开的示例的翼型件尤其包括具有用于输送流体流动的内部通道的翼型件主体。 内部通道包括在转弯部分处联接的第一和第二通道部分。 挡板包括布置在第二通道部分中以限定两个冷却流动路径的主体，并且第一楔形区域从主体延伸到第一通道部分中，使得流体流动被引导通过第一通道部分和第二通道部分之间的转向部分 两个冷却流路。
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公开(公告)号：US20160222796A1
公开(公告)日：2016-08-04
申请号：US15022640
申请日：2014-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Edwin Otero
CPC classification number: F01D5/187 , F01D5/147 , F01D5/189 , F05D2220/32 , F05D2230/22 , F05D2230/31 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F05D2300/606
Abstract: A blade includes a platform and a monolithic airfoil extending from the platform to a tip. The airfoil includes a first wall extending from a leading edge to a trailing edge, a second wall extending from the leading edge to the trailing edge and joined to the first wall at the leading edge, and at least one rib extending from the first wall to the second wall. The at least one rib and the first and second walls define a cavity. The blade also includes a baffle positioned within the cavity. The baffle has walls that are separate and distinct from and not attached to the at least one rib and the first and second walls of the airfoil. A method for forming a blade includes forming a platform and forming an airfoil and a baffle within the airfoil on a layer-by-layer basis using additive manufacturing.
Abstract translation: 叶片包括平台和从平台延伸到尖端的整体翼型件。 翼型件包括从前缘延伸到后缘的第一壁，从前缘延伸到后缘并在前缘处连接到第一壁的第二壁以及从第一壁延伸到至少一个肋 第二个墙。 所述至少一个肋和所述第一壁和所述第二壁限定空腔。 叶片还包括位于腔内的挡板。 挡板具有与所述翼型件的至少一个肋部以及翼型件的第一和第二壁分开并且不连接的壁。 用于形成叶片的方法包括使用添加剂制造在层叠的基础上形成平台并在翼型内形成翼型和挡板。
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