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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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公开(公告)号：US20160053621A1
公开(公告)日：2016-02-25
申请号：US14780573
申请日：2014-04-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ky H. Vu , Lisa P. O'Neill , Takao Fukuda , Gerald M. Mace, Jr. , Andy Turko , Andrew P. Boursy , Lynn M. Boy
CPC classification number: F01D9/041 , F01D5/14 , F01D5/143 , F05D2240/57 , F05D2240/81 , F05D2250/19 , F05D2250/192 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.
Abstract translation: 用于燃气涡轮发动机的翼型件包括平台。 机翼部件包括翼面延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 波纹表面毗邻流路表面和后表面。 用于燃气涡轮发动机的翼型件包括平台。 机翼部件包括翼面延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 波纹表面毗邻流路表面和后表面。 后表面在周向延伸的边缘处从第一后边缘延伸到第二后边缘。 轮廓表面从第一和第二边缘中的至少一个设置在内侧。
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公开(公告)号：US10465559B2
公开(公告)日：2019-11-05
申请号：US15839932
申请日：2017-12-13
Applicant: United Technologies Corporation
Inventor： Ky H. Vu , Bryan P. Dube , Michael J. Allen
Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.
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公开(公告)号：US20190178107A1
公开(公告)日：2019-06-13
申请号：US15839932
申请日：2017-12-13
Applicant: United Technologies Corporation
Inventor： Ky H. Vu , Bryan P. Dube , Michael J. Allen
IPC: F01D25/24
CPC classification number: F01D25/246 , F01D9/042 , F04D29/542 , F05B2250/11 , F05B2250/292 , F05D2240/12 , F05D2240/14 , F05D2250/11 , F05D2250/292 , F05D2260/941
Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.
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公开(公告)号：US10822962B2
公开(公告)日：2020-11-03
申请号：US16144677
申请日：2018-09-27
Applicant: United Technologies Corporation
Inventor： Ky H. Vu , Adam P. Generale
Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.
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Patent Agency Ranking
公开(公告)号：US20190178091A1
公开(公告)日：2019-06-13
申请号：US15837784
申请日：2017-12-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ky H. Vu , Adam P. Generale , Brandon L. Howard
Abstract: A vane for a gas turbine engine may comprise a vane platform and an airfoil extending radially from the vane platform. The airfoil may comprise an inlet defined, at least partially, by an internal surface of the airfoil. The internal surface may comprise a convex curve proximate the inlet. A transition between an external surface of the airfoil and a surface of the vane platform may comprise a concave curve. A radius of curvature of the convex curve of the internal surface may be concentric to a radius of curvature of the concave curve of the transition.
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公开(公告)号：US10280793B2
公开(公告)日：2019-05-07
申请号：US15021998
申请日：2014-08-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ky H. Vu
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, and an insert positioned such that a first portion of the insert extends relative to a surface of the platform and a second portion extends inside the airfoil. A standoff supports the insert above the surface.
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公开(公告)号：US10280761B2
公开(公告)日：2019-05-07
申请号：US14872272
申请日：2015-10-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ky H. Vu , Brandon W. Spangler
Abstract: A component for use in a gas turbine engine comprises a body and a micro-core cooling circuit embedded within the body. The micro-core circuit has a variation in either the thickness or contoured surface, away from a generally planar shape to a non-planar shape.
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公开(公告)号：US11415020B2
公开(公告)日：2022-08-16
申请号：US16702887
申请日：2019-12-04
Applicant: United Technologies Corporation
Inventor： Ky H. Vu , Brian R. Pelletier
Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.
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公开(公告)号：US11131212B2
公开(公告)日：2021-09-28
申请号：US15832925
申请日：2017-12-06
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Adam P. Generale , Ky H. Vu
Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.
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