Patents by Inventor Jeffrey De Jonge
Jeffrey De Jonge 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: 11371699Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.Type: GrantFiled: November 12, 2019Date of Patent: June 28, 2022Assignee: General Electric CompanyInventors: Felipe Bolanos Chaverri, Dariusz Oliwiusz Palys, Andre Theuer, Jeffrey De Jonge
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Publication number: 20210140638Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.Type: ApplicationFiled: November 12, 2019Publication date: May 13, 2021Inventors: Felipe Bolanos Chaverri, Dariusz Oliwiusz Palys, Andre Theuer, Jeffrey De Jonge
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Patent number: 10570771Abstract: The present disclosure relates to a damping device for absorbing structural vibrations or high excitation frequencies between a first component and a second component of a turbomachine, particularly in connection with high temperature operating conditions. The first component may be a combustor or a burner of a gas turbine and the second component may be a fuel supply line, connected to or passed through a wall of the first component. The damping device may include at least one wire mesh element which is inserted into a housing with a radially outer surface of the wire mesh element being compressed by the housing, and a radially inner surface of the wire mesh element closely surrounding the second component, wherein the housing is fixedly connected to the wall of the first component by a weld seam.Type: GrantFiled: June 15, 2016Date of Patent: February 25, 2020Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Martin Kollenrott, Ivo Belina, Armando Alsina, Jeffrey De Jonge
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Patent number: 10378767Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.Type: GrantFiled: January 12, 2016Date of Patent: August 13, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Michael Thomas Maurer, Jeffrey De Jonge, Karolina Krystyna Sobol
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Patent number: 10253985Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.Type: GrantFiled: February 22, 2016Date of Patent: April 9, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Michael Thomas Maurer, Jeffrey De Jonge, Felix Baumgartner, Patrik Meng
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Patent number: 9631813Abstract: An insert element for closing an opening inside a wall of a hot gas path component of a gas turbine includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).Type: GrantFiled: November 22, 2013Date of Patent: April 25, 2017Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Felix Reinert, Guenter Ambrosy, Matthias Hoebel, Jeffrey De Jonge
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Publication number: 20160363002Abstract: The present disclosure relates to a damping device for absorbing structural vibrations or high excitation frequencies between a first component and a second component of a turbomachine, particularly in connection with high temperature operating conditions. The first component may be a combustor or a burner of a gas turbine and the second component may be a fuel supply line, connected to or passed through a wall of the first component. The damping device may include at least one wire mesh element which is inserted into a housing with a radially outer surface of the wire mesh element being compressed by the housing, and a radially inner surface of the wire mesh element closely surrounding the second component, wherein the housing is fixedly connected to the wall of the first component by a weld seam. In addition.Type: ApplicationFiled: June 15, 2016Publication date: December 15, 2016Applicant: ANSALDO ENERGIA IP UK LIMITEDInventors: Martin KOLLENROTT, Ivo BELINA, Armando ALSINA, Jeffrey DE JONGE
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Publication number: 20160258625Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.Type: ApplicationFiled: February 22, 2016Publication date: September 8, 2016Applicant: General Electric Technology GmbHInventors: Michael Thomas MAURER, Jeffrey DE JONGE, Felix BAUMGARTNER, Patrik MENG
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Publication number: 20160209034Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.Type: ApplicationFiled: January 12, 2016Publication date: July 21, 2016Applicant: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Michael Thomas Maurer, Jeffrey De Jonge, Karolina Krystyna Sobol
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Publication number: 20150075168Abstract: A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels.Type: ApplicationFiled: September 26, 2014Publication date: March 19, 2015Inventors: Jeffrey DE JONGE, Andreas Huber, Bruno Schuermans, Urs Benz
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Publication number: 20140147251Abstract: The invention refers an insert element for closing an opening inside a wall of a hot gas path component of a gas turbine. The insert includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).Type: ApplicationFiled: November 22, 2013Publication date: May 29, 2014Applicant: ALSTOM Technology LtdInventors: Felix REINERT, Guenter Ambrosy, Matthias Hoebel, Jeffrey De Jonge