Patents by Inventor Jeremy Styborski
Jeremy Styborski 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: 11112113Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and an impingement slot extending from the second surface of the second component to the first surface of the second component, the second surface of the first component and the first surface of the second component defining a cooling channel therebetween in fluid communication with the impingement slot, wherein the impingement slot is in fluid communication with the second surface of the first component, wherein the impingement slot includes a slot tab configured to direct airflow into the cooling channel at least partially in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel.Type: GrantFiled: May 30, 2018Date of Patent: September 7, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jeremy Styborski, Corey D. Anderson
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Patent number: 11085304Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.Type: GrantFiled: June 7, 2018Date of Patent: August 10, 2021Assignee: Raytheon Technologies CorporationInventors: Jeremy Styborski, Alex J. Schneider
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Patent number: 11073285Abstract: A combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.Type: GrantFiled: June 21, 2019Date of Patent: July 27, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Jeremy Styborski, Caroline Karanian
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Publication number: 20210148638Abstract: A heat exchanger has: an inlet manifold having an inlet port; and an outlet manifold having an outlet port. A first gas flowpath passes from the inlet port to the outlet port. A plurality of plate banks are positioned end-to-end, each plate bank having a plurality of conduits with interiors along respective branches of the first gas flowpath, a second gas flowpath extending across exteriors of the plurality of conduits. One or more docks couple adjacent ends of the plurality of plate banks.Type: ApplicationFiled: November 15, 2019Publication date: May 20, 2021Inventors: Michael A. Disori, William P. Stillman, David J. Hyland, Jeremy A. Styborski, Kyle F. Shaughnessy, Alexander G. Broulidakis, Alan D. Lees, David Donald Chapdelaine
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Patent number: 10962306Abstract: A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.Type: GrantFiled: February 8, 2019Date of Patent: March 30, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael A. Disori, William P. Stillman, Adam J. Diener, Alexander Broulidakis, David J. Hyland, Jeremy Styborski
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Publication number: 20200400313Abstract: A combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.Type: ApplicationFiled: June 21, 2019Publication date: December 24, 2020Inventors: San Quach, Jeremy Styborski, Caroline Karanian
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Publication number: 20200348023Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface opposite the first surface of the second component; and a cooling circuit formed in the second component, the cooling circuit including an inlet at the second surface of the second component, an outlet at the first surface of the second component, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween, wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the second component and the second surface of the second component.Type: ApplicationFiled: May 3, 2019Publication date: November 5, 2020Inventors: Corneil S. Paauwe, Eva Wong, San Quach, Jeremy Styborski, Caroline Karanian, Lauryn M. Curtis, Steven D. Porter, Zhongtao Dai
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Patent number: 10815793Abstract: An airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern. A gas turbine engine includes a compressor section, a combustor section, and a turbine section, where the turbine section includes an airfoil, where the airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern.Type: GrantFiled: June 19, 2018Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Jeremy Styborski, William P. Stillman
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Patent number: 10738620Abstract: A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.Type: GrantFiled: April 18, 2018Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventors: Corey D. Anderson, Jeremy Styborski
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Patent number: 10697310Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.Type: GrantFiled: May 17, 2018Date of Patent: June 30, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Corey D. Anderson, Jeremy Styborski
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Publication number: 20190383150Abstract: An airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern. A gas turbine engine includes a compressor section, a combustor section, and a turbine section, where the turbine section includes an airfoil, where the airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern.Type: ApplicationFiled: June 19, 2018Publication date: December 19, 2019Inventors: Jeremy Styborski, William P. Stillman
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Publication number: 20190376393Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.Type: ApplicationFiled: June 7, 2018Publication date: December 12, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeremy Styborski, Alex J. Schneider
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Publication number: 20190368734Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and an impingement slot extending from the second surface of the second component to the first surface of the second component, the second surface of the first component and the first surface of the second component defining a cooling channel therebetween in fluid communication with the impingement slot, wherein the impingement slot is in fluid communication with the second surface of the first component, wherein the impingement slot includes a slot tab configured to direct airflow into the cooling channel at least partially in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel.Type: ApplicationFiled: May 30, 2018Publication date: December 5, 2019Inventors: Jeremy Styborski, Corey D. Anderson
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Publication number: 20190353038Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.Type: ApplicationFiled: May 17, 2018Publication date: November 21, 2019Inventors: Corey D. Anderson, Jeremy Styborski
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Publication number: 20190346216Abstract: In a featured embodiment, a heat exchanger assembly includes an inlet manifold defining an expanding area in a direction of flow; and an inlet in flow communication with the inlet manifold, the inlet including a wall for inducing a rotational inertia to flow entering the inlet manifold.Type: ApplicationFiled: May 8, 2018Publication date: November 14, 2019Inventors: Corey D. Anderson, Jeremy Styborski, Lauryn M. Curtis
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Publication number: 20190323358Abstract: A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.Type: ApplicationFiled: April 18, 2018Publication date: October 24, 2019Inventors: Corey D. Anderson, Jeremy Styborski
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Publication number: 20190310030Abstract: A featured embodiment of a cast plate heat exchanger assembly includes a cast plate including a plate portion defining a plurality of internal passages. A plurality of fin portions extend from the plate portion. First augmentation structures are disposed on surfaces of the fin portions for conditioning cooling airflow to enhance transfer of thermal energy. A method is also disclosed.Type: ApplicationFiled: February 20, 2019Publication date: October 10, 2019Inventors: Michael A. Disori, William P. Stillman, Alexander Broulidakis, Dave J. Hyland, Jeremy Styborski, Adam J. Diener, Matthew A. Devore, Dominic J. Mongillo, JR.
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Publication number: 20190310031Abstract: A heat exchanger includes a primary plate including a first surface, a second surface, a leading edge, a trailing edge and a plurality of internal passages extending between an inlet and an outlet. A secondary plate is attached to at least one of the first surface and second surface of the primary plate. The secondary plate includes heat transfer structures. A method is also disclosed.Type: ApplicationFiled: February 18, 2019Publication date: October 10, 2019Inventors: Michael A. Disori, Dave J. Hyland, Jeremy Styborski, Adam J. Diener, Alexander Broulidakis
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Publication number: 20190293366Abstract: A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.Type: ApplicationFiled: February 8, 2019Publication date: September 26, 2019Inventors: Michael A. Disori, William P. Stillman, Adam J. Diener, Alexander Broulidakis, David J. Hyland, Jeremy Styborski
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Publication number: 20190277579Abstract: A heat exchanger includes a plate portion including a top surface, bottom surface, a leading edge, a trailing edge and a plurality of internal passages extending between an inlet and an outlet. A fin portion extends outward from one of the top surface and the bottom surface. The fin portion and the leading edge of the plate portion define a leading edge contour. A cast plate for a heat exchanger and a method are also disclosed.Type: ApplicationFiled: March 7, 2018Publication date: September 12, 2019Inventors: Michael A. Disori, William P. Stillman, Adam J. Diener, Alexander Broulidakis, David J. Hyland, Jeremy Styborski