Patents by Inventor Roland Dückershoff
Roland Dückershoff 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: 8801366Abstract: A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.Type: GrantFiled: September 28, 2010Date of Patent: August 12, 2014Assignee: Alstom Technology Ltd.Inventors: Roland Dueckershoff, Shailendra Naik, Martin Schnieder
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Publication number: 20140060766Abstract: A blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity, to improve the transfer of heat between the wall of the blade and the cooling air. An improvement of the internal cooling is achieved by the turbulators or pins extending into the cavity in a direction which can be freely selected within an angular range.Type: ApplicationFiled: November 8, 2013Publication date: March 6, 2014Applicant: ALSTOM Technology LtdInventors: Jose Anguisola MCFEAT, Jörg KRÜCKELS, Roland DÜCKERSHOFF, Brian Kenneth WARDLE
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Patent number: 8459934Abstract: A guide blade for a gas turbine includes an inner and an outer platform, an airfoil extending in a radial direction between the inner and the outer platforms and having a height in the radial direction, and at least one cooling channel disposed in an interior of the airfoil and configured to receive a cooling medium flowing through the at least one cooling channel configured to cool the guide blade, wherein a cross-sectional area of a blade material of the airfoil varies over the height.Type: GrantFiled: September 23, 2010Date of Patent: June 11, 2013Assignee: Alstom Technology LtdInventors: Willy Heinz Hofmann, Roland Dueckershoff, Brian Kenneth Wardle
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Patent number: 8210797Abstract: A gas turbine with a stator blade is disclosed. The stator blade is fastened on a blade carrier and includes a blade airfoil which extends inwards in the radial direction from an outer platform into a hot gas passage. A cooling medium can flow through an interior of the blade airfoil, such as cooling air, which flows through an access in the blade carrier into a first plenum which is arranged above the outer platform, and from there, via an inlet which is provided in the outer platform, flows into the interior of the blade airfoil.Type: GrantFiled: November 24, 2010Date of Patent: July 3, 2012Assignee: ALSTOM Technology LtdInventors: Roland Dueckershoff, Ulrich Steiger, Ulrich Rathmann
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Patent number: 8182225Abstract: A blade for a gas turbine includes a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as to define a pressure side and a suction side; an exit slot disposed in the blade body in an area of the trailing edge and running in the longitudinal direction and configured to discharge a cooling medium from an interior of the blade body; and a row of first and second control elements disposed in the exit slot in a distributed manner in the longitudinal direction and configured to control a mass flow of the cooling medium exiting through the exit slot, the first control elements having a first configuration and the second control elements having a second configuration different from the first configuration.Type: GrantFiled: September 7, 2010Date of Patent: May 22, 2012Assignee: AlstomTechnology LtdInventors: Joerg Krueckels, Roland Dueckershoff, Martin Schnieder
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Publication number: 20110236222Abstract: A blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity, to improve the transfer of heat between the wall of the blade and the cooling air. An improvement of the internal cooling is achieved by the turbulators or pins extending into the cavity in a direction which can be freely selected within an angular range.Type: ApplicationFiled: December 7, 2010Publication date: September 29, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Jose Anguisola MCFEAT, Jörg KRÜCKELS, Roland DÜCKERSHOFF, Brian Kenneth WARDLE
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Publication number: 20110103932Abstract: A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.Type: ApplicationFiled: September 28, 2010Publication date: May 5, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Roland DUECKERSHOFF, Shailendra NAIK, Martin SCHNIEDER
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Publication number: 20110085894Abstract: A gas turbine with a stator blade is disclosed. The stator blade is fastened on a blade carrier and includes a blade airfoil which extends inwards in the radial direction from an outer platform into a hot gas passage. A cooling medium can flow through an interior of the blade airfoil, such as cooling air, which flows through an access in the blade carrier into a first plenum which is arranged above the outer platform, and from there, via an inlet which is provided in the outer platform, flows into the interior of the blade airfoil.Type: ApplicationFiled: November 24, 2010Publication date: April 14, 2011Applicant: ALSTOM Technology LtdInventors: Roland DUECKERSHOFF, Ulrich STEIGER, Ulrich RATHMANN
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Publication number: 20110085915Abstract: A blade for a gas turbine includes a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as to define a pressure side and a suction side; an exit slot disposed in the blade body in an area of the trailing edge and running in the longitudinal direction and configured to discharge a cooling medium from an interior of the blade body; and a row of first and second control elements disposed in the exit slot in a distributed manner in the longitudinal direction and configured to control a mass flow of the cooling medium exiting through the exit slot, the first control elements having a first configuration and the second control elements having a second configuration different from the first configuration.Type: ApplicationFiled: September 7, 2010Publication date: April 14, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Joerg KRUECKELS, Roland DUECKERSHOFF, Martin SCHNIEDER
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Publication number: 20110076155Abstract: A guide blade for a gas turbine includes an inner and an outer platform, an airfoil extending in a radial direction between the inner and the outer platforms and having a height in the radial direction, and at least one cooling channel disposed in an interior of the airfoil and configured to receive a cooling medium flowing through the at least one cooling channel configured to cool the guide blade, wherein a cross-sectional area of a blade material of the airfoil varies over the height.Type: ApplicationFiled: September 23, 2010Publication date: March 31, 2011Applicant: ALSTOM TECHNOLOGY LTD.Inventors: Willy Heinz HOFMANN, Roland DUECKERSHOFF, Brian Kenneth WARDLE
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Publication number: 20110058957Abstract: A blade is provided for a gas turbine, especially for the low-pressure turbine of a gas turbine with sequential combustion, and is produced in accordance with a casting process and has a blade airfoil which extends in the radial direction between an inner platform and an outer platform, and in the interior of which extends a cooling passage, bypassing the platforms, and through which flows a cooling medium, especially cooling air, for cooling the blade. In the outer and/or inner platform there are core outlet openings which arise from the use of a casting core and which connect the cooling passage to the outside space and are sealed off by means of a sealing element. Optimum cooling is ensured by the sealing elements being formed and inserted into the core outlet openings so that they align with the wall surface of the cooling passage in a flush manner.Type: ApplicationFiled: September 29, 2010Publication date: March 10, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Beat VON ARX, Roland Dückershoff, Brian Kenneth WARDLE