Patents by Inventor Lucas Dvorozniak
Lucas Dvorozniak has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11512601Abstract: 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.Type: GrantFiled: May 18, 2020Date of Patent: November 29, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Lucas Dvorozniak, Jon E. Sobanski, David J. Wasserman
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Patent number: 11492914Abstract: 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.Type: GrantFiled: October 27, 2020Date of Patent: November 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Adam P. Generale, Raymond Surace, Lucas Dvorozniak
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Patent number: 11473444Abstract: 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.Type: GrantFiled: November 8, 2019Date of Patent: October 18, 2022Assignee: Raytheon Technologies CorporationInventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Patent number: 11415002Abstract: 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.Type: GrantFiled: October 18, 2019Date of Patent: August 16, 2022Assignee: Raytheon Technologies CorporationInventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Patent number: 11339667Abstract: 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.Type: GrantFiled: August 11, 2020Date of Patent: May 24, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Bryan P. Dube, Tracy A. Propheter-Hinckley, Allan N. Arisi, Adam P. Generale, Lucas Dvorozniak, Howard J. Liles
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Patent number: 11280201Abstract: 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.Type: GrantFiled: October 14, 2019Date of Patent: March 22, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Adam P. Generale, Lucas Dvorozniak, San Quach, Bryan P. Dube
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Publication number: 20220049608Abstract: 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.Type: ApplicationFiled: August 11, 2020Publication date: February 17, 2022Inventors: San Quach, Bryan P. Dube, Tracy A. Propheter-Hinckley, Allan N. Arisi, Adam P. Generale, Lucas Dvorozniak, Howard J. Liles
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Patent number: 11230931Abstract: 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.Type: GrantFiled: July 3, 2020Date of Patent: January 25, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Lucas Dvorozniak, Dominic J. Mongillo, Jr.
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Publication number: 20220003121Abstract: 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.Type: ApplicationFiled: July 3, 2020Publication date: January 6, 2022Inventors: Lucas Dvorozniak, Dominic J. Mongillo, JR.
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Publication number: 20210355834Abstract: 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.Type: ApplicationFiled: May 18, 2020Publication date: November 18, 2021Inventors: Lucas Dvorozniak, Jon E. Sobanski, David J. Wasserman
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Publication number: 20210140341Abstract: 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.Type: ApplicationFiled: November 8, 2019Publication date: May 13, 2021Inventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Publication number: 20210115801Abstract: 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.Type: ApplicationFiled: October 18, 2019Publication date: April 22, 2021Inventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Publication number: 20210108519Abstract: 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.Type: ApplicationFiled: October 14, 2019Publication date: April 15, 2021Inventors: Adam P. Generale, Lucas Dvorozniak, San Quach, Bryan P. Dube