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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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Patent Agency Ranking
公开(公告)号：US11415002B2
公开(公告)日：2022-08-16
申请号：US16657135
申请日：2019-10-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Adam P. Generale , Lucas Dvorozniak , San Quach
Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil. The second zone includes a second plurality of cooling holes that provide a second cooling density that is lower than the first cooling density such that the high temperature area and the low temperature area are balanced to lower a thermal gradient across the first and second zones of the vane airfoil. An vane airfoil and a method of assembling a ceramic matrix composite vane airfoil are also disclosed.
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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：US20210115801A1
公开(公告)日：2021-04-22
申请号：US16657135
申请日：2019-10-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Adam P. Generale , Lucas Dvorozniak , San Quach
Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil. The second zone includes a second plurality of cooling holes that provide a second cooling density that is lower than the first cooling density such that the high temperature area and the low temperature area are balanced to lower a thermal gradient across the first and second zones of the vane airfoil. An vane airfoil and a method of assembling a ceramic matrix composite vane airfoil are also disclosed.
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公开(公告)号：US20210108519A1
公开(公告)日：2021-04-15
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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