Patents by Inventor Jonathan Mugglestone
Jonathan Mugglestone 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: 10995622Abstract: A turbine assembly having a hollow aerofoil, an impingement tube, and an impingement tube sleeve. The sleeve has as least one impingement tube sleeve segment, the aerofoil having at its interior surface longitudinal ribs extending from a leading edge towards a trailing edge. A first impingement tube sleeve segment provides a slotted flow blocker at a surface of the first impingement tube sleeve segment, the first impingement tube sleeve segment inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the first impingement tube sleeve segment rests on the ribs. The impingement tube is inserted into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.Type: GrantFiled: June 14, 2018Date of Patent: May 4, 2021Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventor: Jonathan Mugglestone
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Publication number: 20200157950Abstract: A turbine assembly having a hollow aerofoil, an impingement tube, and an impingement tube sleeve. The sleeve has as least one impingement tube sleeve segment, the aerofoil having at its interior surface longitudinal ribs extending from a leading edge towards a trailing edge. A first impingement tube sleeve segment provides a slotted flow blocker at a surface of the first impingement tube sleeve segment, the first impingement tube sleeve segment inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the first impingement tube sleeve segment rests on the ribs. The impingement tube is inserted into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.Type: ApplicationFiled: June 14, 2018Publication date: May 21, 2020Applicant: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 10513933Abstract: A turbine assembly with a hollow aerofoil having a main cavity with an impingement tube, insertable inside the main cavity for impingement cooling of an inner surface of the main cavity, and a platform at a radial end of the hollow aerofoil, and a cooling chamber for cooling the platform arranged relative to the hollow aerofoil on an opposed site of the platform. The cooling chamber is limited at a first radial end by a wall segment of the platform and at an opposed radial second end from a cover plate. The impingement tube extends in span wise direction through the cooling chamber from the platform to the cover plate and restricts a sub-cavity of the main cavity. The wall segment includes an entry aperture for a cooling medium to enter from the cooling chamber of the platform into the sub-cavity of the hollow aerofoil.Type: GrantFiled: August 5, 2015Date of Patent: December 24, 2019Assignee: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 10502071Abstract: An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.Type: GrantFiled: March 10, 2015Date of Patent: December 10, 2019Assignee: Siemens AktiengesellschaftInventors: Anthony Davis, Jonathan Mugglestone
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Patent number: 10450881Abstract: A turbine assembly having a basically hollow aerofoil with at least one cavity spanning the aerofoil in span wise direction of the aerofoil, an outer platform and an inner platform, each comprising at least one cavity, which are in flow communication with each other over at least one jumper tube, which extends in span wise direction along a whole length of the cavity of the aerofoil, and with a sealed gap being arranged between an outer surface of the jumper tube and an inner surface of a cavity wall of the aerofoil. A corresponding method operates a turbine assembly.Type: GrantFiled: April 15, 2015Date of Patent: October 22, 2019Assignee: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 10012093Abstract: A turbine assembly is provided having a hollow aerofoil having a cavity with an impingement tube insertable inside the cavity and used for impingement cooling of an inner surface of the cavity, and a platform arranged at a radial end of the hollow aerofoil, and a cooling chamber used for cooling of the platform which is arranged relative to the hollow aerofoil on an opposed side of the platform. The cooling chamber is limited at a first radial end from the platform and at an opposed radial second end from a cover plate. The impingement tube is formed from a leading piece and a trailing piece. The leading piece extends in span wise direction at least completely through the cooling chamber from the platform to the cover plate and the trailing piece terminates in span wise direction at the platform.Type: GrantFiled: November 22, 2012Date of Patent: July 3, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Patent number: 9919391Abstract: A method for manufacturing a turbine assembly, which includes at least two aerofoils arranged adjacent towards each other and embodied as a twin vane segment, is provided. The method includes: processing the turbine assembly with a first protection technique providing a first protection for the at least two adjacent aerofoils, wherein at least one region of one aerofoil remains unprocessed; pre-processing of the at least one region that will remain unprocessed or post-processing of the at least one region that remained unprocessed with a second protection technique to provide a second protection for the at least one region of the one aerofoil, wherein the first and the second protection techniques differ from one another.Type: GrantFiled: August 23, 2013Date of Patent: March 20, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Patent number: 9909439Abstract: A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.Type: GrantFiled: January 14, 2014Date of Patent: March 6, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Richard Bluck, David Butler, Jonathan Mugglestone, David Overton
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Patent number: 9863255Abstract: A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.Type: GrantFiled: November 22, 2012Date of Patent: January 9, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Publication number: 20170234144Abstract: A turbine assembly with a hollow aerofoil having a main cavity with an impingement tube, insertable inside the main cavity for impingement cooling of an inner surface of the main cavity, and a platform at a radial end of the hollow aerofoil, and a cooling chamber for cooling the platform arranged relative to the hollow aerofoil on an opposed site of the platform. The cooling chamber is limited at a first radial end by a wall segment of the platform and at an opposed radial second end from a cover plate. The impingement tube extends in span wise direction through the cooling chamber from the platform to the cover plate and restricts a sub-cavity of the main cavity. The wall segment includes an entry aperture for a cooling medium to enter from the cooling chamber of the platform into the sub-cavity of the hollow aerofoil.Type: ApplicationFiled: August 5, 2015Publication date: August 17, 2017Applicant: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 9650899Abstract: A turbine assembly includes a basically hollow aerofoil. A wall segment may be arranged at a side of the aerofoil. An insertion aperture in the wall segment provides access to the aerofoil and an impingement tube may be inserted via the insertion aperture into the aerofoil to be located within the aerofoil and extend at least in a span wise direction of the aerofoil. A protrusion section of the impingement tube may extend in a direction basically perpendicular to the span wise direction over an edge of the insertion aperture. The protrusion section may be overlapped by at least a part of the wall segment. Adjacent to the protrusion section, an overlap section of the impingement tube is arranged to abut the edge of the insertion aperture. The protrusion section and the overlap section may be formed integrally with each other in one piece.Type: GrantFiled: June 11, 2012Date of Patent: May 16, 2017Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Publication number: 20170122112Abstract: An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.Type: ApplicationFiled: March 10, 2015Publication date: May 4, 2017Applicant: Siemens AktiengesellschaftInventors: Anthony Davis, Jonathan Mugglestone
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Publication number: 20170044915Abstract: A turbine assembly having a basically hollow aerofoil with at least one cavity spanning the aerofoil in span wise direction of the aerofoil, an outer platform and an inner platform, each comprising at least one cavity, which are in flow communication with each other over at least one jumper tube, which extends in span wise direction along a whole length of the cavity of the aerofoil, and with a sealed gap being arranged between an outer surface of the jumper tube and an inner surface of a cavity wall of the aerofoil. A corresponding method operates a turbine assembly.Type: ApplicationFiled: April 15, 2015Publication date: February 16, 2017Applicant: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 9267383Abstract: A turbine airfoil includes an airfoil body with a leading edge, trailing edge, and an exterior surface including a suction side and a pressure side located opposite to the suction side. The exterior surface shows away from the interior of the airfoil body. A thermal barrier coating system is present on the exterior surface of the airfoil body in a coated surface region. The airfoil also includes an uncoated surface region where a thermal barrier coating system is not present. The uncoated region extends on the suction side of the exterior surface from the trailing edge towards the leading edge to a boundary line between the coated surface region and the uncoated surface region, wherein the boundary line is located on the suction side between the leading edge and the trailing edge. The airfoil body also includes a step in the exterior surface extending along the boundary line.Type: GrantFiled: February 15, 2011Date of Patent: February 23, 2016Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Stephen Batt, Jonathan Mugglestone, Li Shing Wong
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Patent number: 9238969Abstract: A turbine arrangement includes first and second platforms forming a section of a main fluid path, aerofoils, and an impingement plate. Each aerofoil extends from the first to the second platform. The second platform has a surface opposite to the main fluid path with recesses surrounded by a raised edge, which provides support for the mountable impingement plate. The edge is formed as a first closed loop surrounding a first recess and further surrounding a first aperture of a first aerofoil and as a second closed loop surrounding a second recess and further surrounding a second aperture of a second aerofoil. A portion of the edge defines a continuous barrier between the first recess and the second recess for blocking cooling fluid. The barrier forms a mating surface for a central area of the impingement plate.Type: GrantFiled: September 19, 2011Date of Patent: January 19, 2016Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Stephen Batt, Jonathan Mugglestone
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Publication number: 20150361814Abstract: A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.Type: ApplicationFiled: January 14, 2014Publication date: December 17, 2015Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Richard Bluck, David Butler, Jonathan Mugglestone, David Overton
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Publication number: 20150266143Abstract: A method for manufacturing a turbine assembly, which includes at least two aerofoils arranged adjacent towards each other and embodied as a twin vane segment, is provided. The method includes: processing the turbine assembly with a first protection technique providing a first protection for the at least two adjacent aerofoils, wherein at least one region of one aerofoil remains unprocessed; pre-processing of the at least one region that will remain unprocessed or post-processing of the at least one region that remained unprocessed with a second protection technique to provide a second protection for the at least one region of the one aerofoil, wherein the first and the second protection techniques differ from one another.Type: ApplicationFiled: August 23, 2013Publication date: September 24, 2015Applicant: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Publication number: 20150030461Abstract: A turbine assembly is provided having a hollow aerofoil having a cavity with an impingement tube insertable inside the cavity and used for impingement cooling of an inner surface of the cavity, and a platform arranged at a radial end of the hollow aerofoil, and a cooling chamber used for cooling of the platform which is arranged relative to the hollow aerofoil on an opposed side of the platform. The cooling chamber is limited at a first radial end from the platform and at an opposed radial second end from a cover plate. The impingement tube is formed from a leading piece and a trailing piece. The leading piece extends in span wise direction at least completely through the cooling chamber from the platform to the cover plate and the trailing piece terminates in span wise direction at the platform.Type: ApplicationFiled: November 22, 2012Publication date: January 29, 2015Applicant: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Publication number: 20150016973Abstract: A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.Type: ApplicationFiled: November 22, 2012Publication date: January 15, 2015Applicant: SIEMENS AKTIENGESELLSCHAFTInventor: Jonathan Mugglestone
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Patent number: 8790073Abstract: A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side.Type: GrantFiled: January 21, 2010Date of Patent: July 29, 2014Assignee: Siemens AktiengesellschaftInventor: Jonathan Mugglestone