Patents by Inventor Marc Henze
Marc Henze 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).
-
Patent number: 11353214Abstract: The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.Type: GrantFiled: July 8, 2016Date of Patent: June 7, 2022Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Joerg Krueckels, Marc Henze
-
Patent number: 10487663Abstract: The present invention relates to an airfoil for a gas turbine, including an improved turbulator arrangement formed on an inner cooling channel of the airfoil. According to preferred embodiments of the invention, in order to ensure a constant angle of the cooling flow inside the channel relative to each turbulator, the angle formed between the turbulator and the vertical axis is advantageously adapted, in the curved area, for every single turbulator. Furthermore, the same principle may be applied to all the cooling channels present within the airfoil.Type: GrantFiled: May 6, 2015Date of Patent: November 26, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Rainer Bauer, Shailendra Naik, Marc Henze
-
Patent number: 10294800Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.Type: GrantFiled: July 1, 2016Date of Patent: May 21, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Emanuele Facchinetti, Guillaume Wagner, Marc Henze
-
Patent number: 9896951Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.Type: GrantFiled: March 19, 2015Date of Patent: February 20, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Emanuele Facchinetti, Guillaume Wagner, Marc Henze, Joerg Krueckels, Marc Widmer
-
Publication number: 20170009990Abstract: The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.Type: ApplicationFiled: July 8, 2016Publication date: January 12, 2017Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Joerg KRUECKELS, Marc HENZE
-
Publication number: 20170002665Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.Type: ApplicationFiled: July 1, 2016Publication date: January 5, 2017Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Emanuele FACCHINETTI, Guillaume WAGNER, Marc HENZE
-
Publication number: 20160130951Abstract: The invention concerns a turbine blade for a gas turbine having a platform part and an aerofoil part. The platform part includes a platform surface arranged to be attached to a corresponding aerofoil surface of the aerofoil part. The turbine blade further includes a cooling duct for cooling the platform and aerofoil surfaces, the cooling duct having at least one cavity in the platform surface and at least one cavity in the corresponding aerofoil surface, and the platform and aerofoil surface cavities are aligned such that when the platform surface and the aerofoil surface are touching, the cooling duct remains open. This provides a reliable cooling of both the platform and aerofoil surfaces.Type: ApplicationFiled: November 6, 2015Publication date: May 12, 2016Applicant: ALSTOM TECHNOLOGY LTD.Inventors: Marc HENZE, Joerg KRÜCKELS, Laura BOGDANIC
-
Publication number: 20150322798Abstract: The present invention relates to an airfoil for a gas turbine, including an improved turbulator arrangement formed on an inner cooling channel of the airfoil. According to preferred embodiments of the invention, in order to ensure a constant angle of the cooling flow inside the channel relative to each turbulator, the angle formed between the turbulator and the vertical axis is advantageously adapted, in the curved area, for every single turbulator. Furthermore, the same principle may be applied to all the cooling channels present within the airfoil.Type: ApplicationFiled: May 6, 2015Publication date: November 12, 2015Inventors: Rainer BAUER, Shailendra NAIK, Marc HENZE
-
Publication number: 20150267557Abstract: An airfoil portion including an outer wall that defines a cavity for receiving cooling air. The airfoil portion includes a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, and a concave pressure side. At least one insert disposed within the cavity is configured to initially receive at least a portion of the cooling air entering the chamber of the insert and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall of the airfoil portion. The insert further includes a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto. A portion of the cooling air exits the airfoil portion through a plurality of film cooling apertures formed through the outer wall.Type: ApplicationFiled: March 18, 2015Publication date: September 24, 2015Inventors: Emanuele FACCHINETTI, Guillaume Wagner, Marc Henze
-
Publication number: 20150267549Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.Type: ApplicationFiled: March 19, 2015Publication date: September 24, 2015Inventors: Emanuele FACCHINETTI, Guillaume Wagner, Marc Henze, Joerg Krueckels, Marc Widmer