Patents by Inventor Christoph DIDION
Christoph DIDION 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: 10132172Abstract: It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.Type: GrantFiled: December 9, 2015Date of Patent: November 20, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Carl Berger, Marco Lamminger, Christoph Didion, Cyrille Bricaud, Philippe Thomas Lott, Igor Tsypkaykin
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Patent number: 10087778Abstract: A wall for a hot gas channel in a gas turbine is described, the wall having a back side and a front side and an impingement sheet having impingement cooling holes, the wall being for exposure to a hot fluid at the front side, and the wall having an array of pins attached to the back side and extending between the back side and the impingement sheet, the wall additionally having a plurality of ribs attached to the back side, each rib extending between two pins to delineate an array of cells on the back side, and/or at least one compartment wall attached to the back side to delineate compartments on the back side. Embodiments include an impingement sheet with impingement cooling holes and cooling exit holes. A gas turbine including the wall is also described.Type: GrantFiled: January 12, 2016Date of Patent: October 2, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Christoph Didion, Herbert Brandl, Magali Cochet, Rene Koehnke
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Patent number: 10012101Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.Type: GrantFiled: December 18, 2014Date of Patent: July 3, 2018Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Carlos Simon-Delgado, Christoph Didion, Marc Widmer, Martin Schaefer, Guenter Filkorn
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Patent number: 9816393Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.Type: GrantFiled: July 21, 2014Date of Patent: November 14, 2017Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Carlos Simon-Delgado, Christoph Didion, Stefan Biedermann, Beat Von Arx, Thomas Zierer
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Publication number: 20160376891Abstract: A method and device for cooling a turboengine rotor. A blade member includes a platform having a hot gas side and a coolant side. An airfoil is on the platform hot gas side and a blade foot section is on the platform coolant side. The blade foot section includes a blade shank and a blade root. The blade shank extends from the platform coolant side and is interposed between the blade root and the platform coolant side. The blade root includes root fixation features and is received by a fixation feature of a rotor shaft. A first fluid flows along the rotor front face and into a cavity of the blade shank and a second fluid flows within the blade shank cavity. The first fluid flow is relatively colder than the second fluid flow and a combined shank cavity fluid flow is formed inside the blade shank cavity.Type: ApplicationFiled: June 24, 2016Publication date: December 29, 2016Applicant: ANSALDO ENERGIA IP UK LIMITEDInventors: Cyrille BRICAUD, Carlos SIMON-DELGADO, Thomas ZIERER, Ulrich Robert STEIGER, Stephan STRUEKEN, Christoph DIDION
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Publication number: 20160208649Abstract: A wall for a hot gas channel in a gas turbine is described, the wall having a back side and a front side and an impingement sheet having impingement cooling holes, the wall being for exposure to a hot fluid at the front side, and the wall having an array of pins attached to the back side and extending between the back side and the impingement sheet, the wall additionally having a plurality of ribs attached to the back side, each rib extending between two pins to delineate an array of cells on the back side, and/or at least one compartment wall attached to the back side to delineate compartments on the back side. Embodiments include an impingement sheet with impingement cooling holes and cooling exit holes. A gas turbine including the wall is also described.Type: ApplicationFiled: January 12, 2016Publication date: July 21, 2016Applicant: General Electric Technology GmbHInventors: Christoph DIDION, Herbert BRANDL, Magali COCHET, Rene KOEHNKE
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Publication number: 20160177750Abstract: It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.Type: ApplicationFiled: December 9, 2015Publication date: June 23, 2016Applicant: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Carl BERGER, Marco LAMMINGER, Christoph DIDION, Cyrille BRICAUD, Philippe Thomas LOTT, Igor TSYPKAYKIN
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Publication number: 20150176424Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.Type: ApplicationFiled: December 18, 2014Publication date: June 25, 2015Inventors: Carlos Simon-Delgado, Christoph Didion, Marc Widmer, Martin Schaefer, Guenter Filkorn
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Patent number: 9051838Abstract: A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.Type: GrantFiled: December 20, 2011Date of Patent: June 9, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Brian Kenneth Wardle, Christoph Didion, Herbert Brandl, Shailendra Naik
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Publication number: 20150037167Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.Type: ApplicationFiled: July 21, 2014Publication date: February 5, 2015Inventors: Carlos SIMON-DELGADO, Christoph Didion, Stefan Biedermann, Beat Von Arx, Thomas Zierer
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Patent number: 8721284Abstract: A hollow-cast casting is provided, which includes at least one core opening that is caused by the production technique and which has a closure device that closes the core opening. The closure device can be inserted into the core opening axially in relation to the core opening and provides at least one surface region which, in axial projection in relation to the core opening, can be made to abut a surface region of the casting that is facing toward the casting. The surface region lies radially outside a cross-sectional area predetermined by the core opening.Type: GrantFiled: September 9, 2010Date of Patent: May 13, 2014Assignee: Alstom Technology Ltd.Inventors: Martin Balliel, Christoph Didion, Thomas Duda, Marcel Koenig
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Publication number: 20120163995Abstract: A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.Type: ApplicationFiled: December 20, 2011Publication date: June 28, 2012Inventors: Brian Kenneth Wardle, Christoph Didion, Herbert Brandl, Shailendra Naik
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Publication number: 20110056648Abstract: A hollow-cast casting is provided, which includes at least one core opening that is caused by the production technique and which has a closure device that closes the core opening. The closure device can be inserted into the core opening axially in relation to the core opening and provides at least one surface region which, in axial projection in relation to the core opening, can be made to abut a surface region of the casting that is facing toward the casting. The surface region lies radially outside a cross-sectional area predetermined by the core opening.Type: ApplicationFiled: September 9, 2010Publication date: March 10, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Martin BALLIEL, Christoph DIDION, Thomas DUDA, Marcel KOENIG