Patents by Inventor Andreas Sadil
Andreas Sadil 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: 10830441Abstract: A swirler is provided for a turbine engine. The swirler includes a swirler housing and a swirler nozzle that is attached to the housing. The housing defines a first inlet and a second inlet. The housing and the nozzle form an inner passage and an outer passage. The inner passage is radially within the nozzle and coupled with the first inlet. The outer passage is radially between the housing and the nozzle and coupled with the second inlet.Type: GrantFiled: October 1, 2014Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: Andreas Sadil, Steven W. Trinks, Jonathan M. Jause
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Patent number: 10823412Abstract: A coated panel for a gas turbine engine includes a panel having a panel inner surface and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is disposed within the pocket to enhance coating retention to the panel. A gas turbine engine includes a turbine, a combustor to supply hot combustion gases to the turbine along a gas path, and one or more coated panels located along the gas path. The one or more panels includes a panel having a panel inner surface, and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is located within the pocket to enhance coating retention to the panel.Type: GrantFiled: April 3, 2017Date of Patent: November 3, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Andreas Sadil, Donald W. Peters
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Patent number: 10815891Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: GrantFiled: September 27, 2013Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Patent number: 10648670Abstract: An assembly for a turbine engine includes a combustor bulkhead, a swirler and a mounting strap. The swirler includes a mounting lug and a tubular swirler body that extends along an axis. The mounting lug projects radially out from the swirler body. The mounting strap is attached to the combustor bulkhead. The mounting lug is axially restrained between the combustor bulkhead and the mounting strap.Type: GrantFiled: August 17, 2015Date of Patent: May 12, 2020Assignee: United Technologies CorporationInventors: Andreas Sadil, Russell B. Hanson, Raymond Lamoureux, Dave J. Hyland
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Patent number: 10487687Abstract: A seal damper assembly includes a seal housing, a sliding seal, and a damping member. The seal housing is disposed on a case assembly that is disposed about an engine component. The seal housing has a base and a wall that axially extends from the base. The base and the wall define a cavity. The sliding seal is received within the cavity. The damping member is received within the cavity and is disposed between the wall and the sliding seal.Type: GrantFiled: September 15, 2016Date of Patent: November 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Andreas Sadil
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Patent number: 10443848Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.Type: GrantFiled: April 2, 2015Date of Patent: October 15, 2019Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr., Andreas Sadil
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Patent number: 10422532Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor section. The combustor includes a combustor region defined by at least one bulkhead panel and at least one heat shielding panel inside the combustor region. The at least one heat shielding panel is connected to the bulkhead panel via at least one cooled fastener.Type: GrantFiled: July 22, 2014Date of Patent: September 24, 2019Assignee: United Technologies CorporationInventors: Andreas Sadil, Jonathan M. Jause, Alexander Broulidakis
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Patent number: 10280791Abstract: A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.Type: GrantFiled: July 11, 2016Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Donald W. Peters, Andreas Sadil, Nico M. Rappoli, Amarnath Ramlogan
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Publication number: 20180283688Abstract: A coated panel for a gas turbine engine includes a panel having a panel inner surface and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is disposed within the pocket to enhance coating retention to the panel. A gas turbine engine includes a turbine, a combustor to supply hot combustion gases to the turbine along a gas path, and one or more coated panels located along the gas path. The one or more panels includes a panel having a panel inner surface, and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is located within the pocket to enhance coating retention to the panel.Type: ApplicationFiled: April 3, 2017Publication date: October 4, 2018Inventors: San Quach, Andreas Sadil, Donald W. Peters
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Publication number: 20180010482Abstract: A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.Type: ApplicationFiled: July 11, 2016Publication date: January 11, 2018Inventors: Donald W. Peters, Andreas Sadil, Nico M. RappoIi, Amarnath Ramlogan
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Publication number: 20160245520Abstract: An assembly for a turbine engine includes a combustor bulkhead, a swirler and a mounting strap. The swirler includes a mounting lug and a tubular swirler body that extends along an axis. The mounting lug projects radially out from the swirler body. The mounting strap is attached to the combustor bulkhead. The mounting lug is axially restrained between the combustor bulkhead and the mounting strap.Type: ApplicationFiled: August 17, 2015Publication date: August 25, 2016Inventors: Andreas Sadil, Russell B. Hanson, Raymond Lamoureux, Dave J. Hyland
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Publication number: 20160231000Abstract: A swirler is provided for a turbine engine. The swirler includes a swirler housing and a swirler nozzle that is attached to the housing. The housing defines a first inlet and a second inlet. The housing and the nozzle form an inner passage and an outer passage. The inner passage is radially within the nozzle and coupled with the first inlet. The outer passage is radially between the housing and the nozzle and coupled with the second inlet.Type: ApplicationFiled: October 1, 2014Publication date: August 11, 2016Inventors: Andreas Sadil, Steven W. Trinks, Jonathan M. Jause
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Publication number: 20160186997Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor section. The combustor includes a combustor region defined by at least one bulkhead panel and at least one heat shielding panel inside the combustor region. The at least one heat shielding panel is connected to the bulkhead panel via at least one cooled fastener.Type: ApplicationFiled: July 22, 2014Publication date: June 30, 2016Inventors: Andreas Sadil, Jonathan M. Jause, Alexander Broulidakis
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Publication number: 20150285498Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.Type: ApplicationFiled: April 2, 2015Publication date: October 8, 2015Inventors: Frank J. Cunha, Stanislav Kostka, JR., Andreas Sadil
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Patent number: 9140213Abstract: A turbine engine fuel delivery system includes a mounting platform, a spray bar assembly and a leaf spring damper with a stack of a plurality of leaf springs. The stack includes a base segment connected longitudinally between a first spray bar contact segment and a second spray bar contact segment. The base segment is connected to the mounting platform and is located a first distance from the spray bar assembly. The first spray bar contact segment engages the spray bar assembly and is located a second distance from the mounting platform. The second spray bar contact segment engages the spray bar assembly and is located a third distance from the mounting platform.Type: GrantFiled: December 6, 2011Date of Patent: September 22, 2015Assignee: United Technologies CorporationInventors: Andreas Sadil, Marc J. Muldoon, Bessem Jlidi
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Publication number: 20150252729Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: ApplicationFiled: September 27, 2013Publication date: September 10, 2015Inventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Patent number: 8893502Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.Type: GrantFiled: October 14, 2011Date of Patent: November 25, 2014Assignee: United Technologies CorporationInventors: Andreas Sadil, Steven W. Burd, Bessem Jlidi, Dennis M. Moura, Christopher R. Brdar, Leong Ma, Fernando K. Grant, Jodie L. Herrmann, Kelly A. Vanston, Matthew J. Westergard, George F. Titterton, III
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Patent number: 8833721Abstract: Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.Type: GrantFiled: July 2, 2012Date of Patent: September 16, 2014Assignee: United Technologies CorporationInventors: Andreas Sadil, Claude I. Barnett, Jr., Ricky A. Daigle
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Publication number: 20130139512Abstract: A turbine engine fuel delivery system includes a mounting platform, a spray bar assembly and a leaf spring damper with a stack of a plurality of leaf springs. The stack includes a base segment connected longitudinally between a first spray bar contact segment and a second spray bar contact segment. The base segment is connected to the mounting platform and is located a first distance from the spray bar assembly. The first spray bar contact segment engages the spray bar assembly and is located a second distance from the mounting platform. The second spray bar contact segment engages the spray bar assembly and is located a third distance from the mounting platform.Type: ApplicationFiled: December 6, 2011Publication date: June 6, 2013Applicant: United Technologies CorporationInventors: Andreas Sadil, Marc J. Muldoon, Bessem Jlidi
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Publication number: 20130091849Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.Type: ApplicationFiled: October 14, 2011Publication date: April 18, 2013Applicant: United Technologies CorporationInventors: Andreas Sadil, Steven W. Burd, Bessem Jlidi, Dennis M. Moura, Christopher R. Brdar, Leong Ma, Fernando K. Grant, Jodie L. Hermann, Kelly A. Vanston, Matthew J. Westergard, George F. Titterton