Patents by Inventor Corneil S. Paauwe
Corneil S. Paauwe 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: 11149556Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.Type: GrantFiled: October 30, 2019Date of Patent: October 19, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Corneil S. Paauwe, Tracy A. Propheter-Hinckley, Allan N. Arisi
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Publication number: 20210148236Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.Type: ApplicationFiled: October 30, 2019Publication date: May 20, 2021Inventors: Corneil S. Paauwe, Tracy A. Propheter-Hinckley, Allan N. Arisi
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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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Publication number: 20160160652Abstract: An airfoil includes a platform including a pocket, a continuous solid cover plate bonded over the pocket, and a plurality of apertures in the platform in fluid communication with the pocket and adjacent the continuous solid cover plate. A gas turbine engine including the airfoil and a method of cooling an article of a gas turbine engine are also disclosed.Type: ApplicationFiled: June 26, 2015Publication date: June 9, 2016Inventors: James P. Bangerter, Corneil S. Paauwe
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Patent number: 9322285Abstract: A turbine airfoil has a fillet connecting the nominal portion of the airfoil into an end wall. Cooling holes are formed over a greater circumferential extent in the fillet than they are through the nominal portion of the airfoil.Type: GrantFiled: February 20, 2008Date of Patent: April 26, 2016Assignee: United Technologies CorporationInventors: Matthew A. Devore, Corneil S. Paauwe
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Patent number: 8240981Abstract: Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.Type: GrantFiled: November 2, 2007Date of Patent: August 14, 2012Assignee: United Technologies CorporationInventors: Brandon W. Spangler, Corneil S. Paauwe, Christopher J. Lehane, Anita L. Tracy, John D. Wiedemer, Scott D. Hjelm
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Patent number: 8206114Abstract: Gas turbine engine systems involving turbine blade platforms with mateface cooling holes are provided. In this regard, a representative turbine blade for a gas turbine engine includes: an airfoil having a leading edge, a trailing edge, a pressure side and a suction side; and a blade platform on which the airfoil is disposed, the blade platform having a pressure side mateface located adjacent to the pressure side of the airfoil and a suction side mateface located adjacent to the suction side of the airfoil, the blade platform having a cooling hole operative to direct a flow of cooling air toward an adjacent blade platform.Type: GrantFiled: April 29, 2008Date of Patent: June 26, 2012Assignee: United Technologies CorporationInventors: Brandon W. Spangler, Corneil S. Paauwe
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Patent number: 8092179Abstract: An example turbine blade includes a blade having an airfoil profile extending radially toward a blade tip. A shelf is established in the blade tip. A sealing portion of the blade tip extends radially past a floor of the shelf. The sealing portion extends from a blade tip leading edge to a blade tip trailing edge. A groove is established in the blade tip. The groove extends from adjacent the shelf to adjacent the blade tip trailing edge. The groove is configured to communicate a fluid from a position adjacent the shelf to a position adjacent the blade tip trailing edge.Type: GrantFiled: March 12, 2009Date of Patent: January 10, 2012Assignee: United Technologies CorporationInventors: Corneil S. Paauwe, Brandon W. Spangler
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Publication number: 20100310367Abstract: A method of impingement cooling a turbine airfoil with a large platform to airfoil fillet radius which includes coring the airfoil fillet such that the fillet wall is maintained at a minimum thickness. An impingement tube is used which follows the fillet contour as it transitions from airfoil to platform and supplies impingement air to the airfoil walls. The air subsequently flows across the airfoil internal wall and finally exits the airfoil through airfoil holes to provide film cooling to the airfoil fillet.Type: ApplicationFiled: September 28, 2006Publication date: December 9, 2010Inventors: Matthew A. Devore, Joseph W. Bridges, JR., Corneil S. Paauwe
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Publication number: 20100232979Abstract: An example turbine blade includes a blade having an airfoil profile extending radially toward a blade tip. A shelf is established in the blade tip. A sealing portion of the blade tip extends radially past a floor of the shelf. The sealing portion extends from a blade tip leading edge to a blade tip trailing edge. A groove is established in the blade tip. The groove extends from adjacent the shelf to adjacent the blade tip trailing edge. The groove is configured to communicate a fluid from a position adjacent the shelf to a position adjacent the blade tip trailing edge.Type: ApplicationFiled: March 12, 2009Publication date: September 16, 2010Inventors: Corneil S. Paauwe, Brandon W. Spangler
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Publication number: 20090269184Abstract: Gas turbine engine systems involving turbine blade platforms with mateface cooling holes are provided. In this regard, a representative turbine blade for a gas turbine engine includes: an airfoil having a leading edge, a trailing edge, a pressure side and a suction side; and a blade platform on which the airfoil is disposed, the blade platform having a pressure side mateface located adjacent to the pressure side of the airfoil and a suction side mateface located adjacent to the suction side of the airfoil, the blade platform having a cooling hole operative to direct a flow of cooling air toward an adjacent blade platform.Type: ApplicationFiled: April 29, 2008Publication date: October 29, 2009Applicant: UNITED TECHNOLOGIES CORP.Inventors: Brandon W. Spangler, Corneil S. Paauwe
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Patent number: 7600966Abstract: A turbine airfoil includes an outer wall and a plurality of cooling passages or minicores formed in the outer wall. A web separates each adjacent pair of the minicores. In order to provide more effective, even cooling of the airfoil, a baffle inside the airfoil includes a plurality of outlets aligned with the webs. The fluid outlets direct the cooling fluid directly onto the web. The cooling fluid then flows through the minicores and out through exits in the minicores.Type: GrantFiled: January 17, 2006Date of Patent: October 13, 2009Assignee: United Technologies CorporationInventors: Matthew A. Devore, Corneil S. Paauwe
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Publication number: 20090208325Abstract: A turbine airfoil has a fillet connecting the nominal portion of the airfoil into an end wall. Cooling holes are formed over a greater circumferential extent in the fillet than they are through the nominal portion of the airfoil.Type: ApplicationFiled: February 20, 2008Publication date: August 20, 2009Inventors: Matthew A. Devore, Corneil S. Paauwe
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Publication number: 20090116953Abstract: Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.Type: ApplicationFiled: November 2, 2007Publication date: May 7, 2009Inventors: Brandon W. Spangler, Corneil S. Paauwe, Christopher J. Lehane, Anita L. Tracy, John D. Wiedemer, Scott D. Hjelm
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Publication number: 20090096174Abstract: An air seal assembly includes a featherseal engaged between adjacent turbine engine components to close a gap therebetween. The featherseal includes a first lateral tab and a second lateral tab which defines a tab space therebetween. The tab space locks the featherseal into the turbine engine component to prevent fore-aft movement thereof.Type: ApplicationFiled: February 28, 2007Publication date: April 16, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Corneil S. Paauwe, Dominic J. Mongillo
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Publication number: 20080031739Abstract: An airfoil suitable for use in the turbine section of a jet engine. Said airfoil contains a core having a passage for conducting a coolant through said airfoil and discharging the coolant through a radially disposed slot at the trailing edge of the airfoil. A flow barrier is mounted adjacent to the discharge slot within the flow passage which contains openings for tailoring the coolant flow distribution profile in the trailing edge region based upon some identifiable airfoil property such as the airfoil's pressure and/or temperature profile, or a combination of the pressure and temperature profiles.Type: ApplicationFiled: August 1, 2006Publication date: February 7, 2008Inventors: Matthew A. Devore, Corneil S. Paauwe