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公开(公告)号：US11280201B2
公开(公告)日：2022-03-22
申请号：US16600875
申请日：2019-10-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Adam P. Generale , Lucas Dvorozniak , San Quach , Bryan P. Dube
IPC: F01D5/18
Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
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公开(公告)号：US20200158018A1
公开(公告)日：2020-05-21
申请号：US16197835
申请日：2018-11-21
Applicant: United Technologies Corporation
Inventor： Adam P. Generale , Bryan P. Dube
Abstract: An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.
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公开(公告)号：US11078844B2
公开(公告)日：2021-08-03
申请号：US16197835
申请日：2018-11-21
Applicant: United Technologies Corporation
Inventor： Adam P. Generale , Bryan P. Dube
Abstract: An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.
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公开(公告)号：US10822963B2
公开(公告)日：2020-11-03
申请号：US16210696
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Adam P. Generale
Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.
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公开(公告)号：US10655496B2
公开(公告)日：2020-05-19
申请号：US15852198
申请日：2017-12-22
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Adam P. Generale
Abstract: Component for gas turbine engines are provided. The components include a platform, the platform defining a platform cavity on a first side, an airfoil extending from a second side of the platform, wherein the airfoil comprises at least one airfoil cavity located within the airfoil, the at least one airfoil cavity fluidly connected to the platform cavity through an airfoil cavity inlet, and a platform flow turning element positioned on the first side of the platform, the platform flow turning element having a turning portion and a tapering portion, wherein the turning portion directs incoming air to turn from the platform cavity into the airfoil cavity and the tapering portion extends through the airfoil cavity inlet and into the airfoil cavity.
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Patent Agency Ranking
公开(公告)号：US11473444B2
公开(公告)日：2022-10-18
申请号：US16677760
申请日：2019-11-08
Applicant: United Technologies Corporation
Inventor： Adam P. Generale , Lucas Dvorozniak , San Quach
Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.
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公开(公告)号：US20210140341A1
公开(公告)日：2021-05-13
申请号：US16677760
申请日：2019-11-08
Applicant: United Technologies Corporation
Inventor： Adam P. Generale , Lucas Dvorozniak , San Quach
Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.
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公开(公告)号：US10934857B2
公开(公告)日：2021-03-02
申请号：US16210052
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Adam P. Generale
Abstract: Airfoils, shells, and spars are provided. The airfoils include a shell having a first channel and a first engagement element arranged along the first channel and a spar having a second channel and a second engagement element arranged along the second channel and the spar defines an inner cavity. A connector is configured to be installed between and connect the shell and the spar to allow for thermal growth of the shell relative to the spar. The connector has first and second engageable portions connected by a link. The first engageable portion is configured to engage with the shell and the second engageable portion is configured to engage with the spar. When assembled, an outer cavity is formed between the spar and the shell, and the first and second engagement elements and the first and second engageable portions are configured to define an axial flow path through the outer cavity.
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公开(公告)号：US10648351B2
公开(公告)日：2020-05-12
申请号：US15832948
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 an internal cavity that has an inlet on 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 is at least partially aligned with the inlet.
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公开(公告)号：US11608749B2
公开(公告)日：2023-03-21
申请号：US16549187
申请日：2019-08-23
Applicant: United Technologies Corporation
Inventor： Richard Wesley Jackson , Adam P. Generale , Xuan Liu , Mark F. Zelesky
IPC: F01D5/28
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.
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