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公开(公告)号：US20220003121A1
公开(公告)日：2022-01-06
申请号：US16920496
申请日：2020-07-03
Applicant: Raytheon Technologies Corporation
Inventor： Lucas Dvorozniak , Dominic J. Mongillo, JR.
IPC: F01D5/18
Abstract: Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.
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Patent Agency Ranking
公开(公告)号：US11492914B1
公开(公告)日：2022-11-08
申请号：US17080969
申请日：2020-10-27
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Adam P. Generale , Raymond Surace , Lucas Dvorozniak
Abstract: A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.
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公开(公告)号：US11339667B2
公开(公告)日：2022-05-24
申请号：US16990420
申请日：2020-08-11
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Bryan P. Dube , Tracy A. Propheter-Hinckley , Allan N. Arisi , Adam P. Generale , Lucas Dvorozniak , Howard J. Liles
Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.
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公开(公告)号：US11230931B1
公开(公告)日：2022-01-25
申请号：US16920496
申请日：2020-07-03
Applicant: Raytheon Technologies Corporation
Inventor： Lucas Dvorozniak , Dominic J. Mongillo, Jr.
IPC: F01D5/18
Abstract: Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.
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公开(公告)号：US11512601B2
公开(公告)日：2022-11-29
申请号：US16876197
申请日：2020-05-18
Applicant: Raytheon Technologies Corporation
Inventor： Lucas Dvorozniak , Jon E. Sobanski , David J. Wasserman
Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.
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公开(公告)号：US20210355834A1
公开(公告)日：2021-11-18
申请号：US16876197
申请日：2020-05-18
Applicant: Raytheon Technologies Corporation
Inventor： Lucas Dvorozniak , Jon E. Sobanski , David J. Wasserman
Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.
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