Patents by Inventor Willy Heinz Hofmann
Willy Heinz Hofmann 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: 11555411Abstract: The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.Type: GrantFiled: August 10, 2021Date of Patent: January 17, 2023Assignee: DOOSAN ENERBILITY CO., LTD.Inventors: Herbert Brandl, Joerg Krueckels, Ulrich Rathmann, Willy Heinz Hofmann
-
Patent number: 11506062Abstract: A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.Type: GrantFiled: August 10, 2021Date of Patent: November 22, 2022Inventors: Kwang Il Kim, Jin Woo Song, Willy Heinz Hofmann, Herbert Brandl
-
Publication number: 20220098986Abstract: A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.Type: ApplicationFiled: August 10, 2021Publication date: March 31, 2022Inventors: Kwang Il KIM, Jin Woo SONG, Willy Heinz HOFMANN, Herbert BRANDL
-
Publication number: 20220090511Abstract: The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.Type: ApplicationFiled: August 10, 2021Publication date: March 24, 2022Inventors: Herbert BRANDL, Joerg Krueckels, Ulrich Rathmann, Willy Heinz Hofmann
-
Patent number: 10006309Abstract: An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.Type: GrantFiled: September 26, 2014Date of Patent: June 26, 2018Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Willy Heinz Hofmann, Philipp Schaefer
-
Patent number: 9765626Abstract: The invention refers to a gas turbine blade including an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord with an axial chord length defined by an axial length of a straight line connecting the leading edge and trailing edge of the airfoil depending on the span. The axial chord length increases at least from 80% span to 100% span.Type: GrantFiled: March 18, 2015Date of Patent: September 19, 2017Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Fabian Neubrand, Willy Heinz Hofmann
-
Patent number: 9377029Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.Type: GrantFiled: June 22, 2012Date of Patent: June 28, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Willy Heinz Hofmann, Josef Ballmann
-
Publication number: 20150345297Abstract: The invention refers to a gas turbine blade including an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord with an axial chord length defined by an axial length of a straight line connecting the leading edge and trailing edge of the airfoil depending on the span. The axial chord length increases at least from 80% span to 100% span.Type: ApplicationFiled: March 18, 2015Publication date: December 3, 2015Inventors: Fabian NEUBRAND, Willy Heinz HOFMANN
-
Publication number: 20150016982Abstract: An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.Type: ApplicationFiled: September 26, 2014Publication date: January 15, 2015Inventors: Willy Heinz Hofmann, Philipp Schaefer
-
Patent number: 8720207Abstract: A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric.Type: GrantFiled: April 30, 2010Date of Patent: May 13, 2014Assignee: Alstom Technology LtdInventors: Frank Gersbach, Christian Sommer, Willy Heinz Hofmann, Ulrich Steiger
-
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
-
Publication number: 20120328447Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.Type: ApplicationFiled: June 22, 2012Publication date: December 27, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Willy Heinz Hofmann, Josef Ballmann
-
Patent number: 8132417Abstract: A gas turbine system includes a combustion chamber (2), a turbine (3), a radially inward and/or radially outward axial gap (4; 16, 17) between the combustion chamber (2) and the turbine (3), at which gap inner and/or outer combustion chamber walls (7, 8) and inner and/or outer turbine walls (11, 12) end, and a cooling gas supply (5), which via the gap (4; 16, 17) introduces a cooling gas into the turbine gas path (13) and/or into the combustion chamber gas path (9). An end section (21, 22, 23, 24) of the respective turbine wall (11, 12) and/or of the respective chamber wall (7, 8) adjoining the gap (4; 16, 17) is radially inwardly and/or radially outwardly, alternatingly formed.Type: GrantFiled: February 4, 2010Date of Patent: March 13, 2012Assignee: ALSTOM Technology Ltd.Inventors: Ulrich Steiger, Willy Heinz Hofmann
-
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
-
Publication number: 20110038733Abstract: A blade for a rotating thermal machine, such as a stator blade for a low-pressure turbine of a gas turbine with sequential combustion, includes a blade airfoil which extends essentially in the radial direction, is exposed to circumflow by an operating medium in a flow direction, and is delimited by a leading edge and a trailing edge in the flow direction. The concurring fluidic and constructional demands on the blade with sharp inclination of the flow are met by the blade airfoil being structured in such a way that an angle which the flow lines form with the trailing edge of the blade airfoil deviates from a right angle within a limited range.Type: ApplicationFiled: September 28, 2010Publication date: February 17, 2011Applicant: ALSTOM Technology LtdInventors: Willy Heinz HOFMANN, Michael HUBER
-
Publication number: 20100278644Abstract: A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric.Type: ApplicationFiled: April 30, 2010Publication date: November 4, 2010Applicant: ALSTOM Technology Ltd.Inventors: Frank GERSBACH, Christian Sommer, Willy Heinz Hofmann, Ulrich Steiger
-
Publication number: 20100146988Abstract: A gas turbine system, in particular for a utility power plant, includes a combustion chamber (2), which at least in an annular outlet region (6) having a chamber inner wall (7) and a chamber outer wall (8), radially delimits a combustion chamber gas path (9), a turbine (3), which at least in a stationary annular inlet region (10) having a turbine inner wall (11) and a turbine outer wall (12), radially delimits a turbine gas path (13), a radially inward and/or radially outward axial gap (4; 16, 17) between the combustion chamber (2) and the turbine (3), at which gap the inner and/or outer chamber wall (7, 8) and the inner and/or outer turbine wall (11, 12) end, and a cooling gas supply (5), which via the gap (4; 16, 17) introduces a cooling gas into the turbine gas path (13) and/or into the combustion chamber gas path (9).Type: ApplicationFiled: February 4, 2010Publication date: June 17, 2010Inventors: Ulrich Steiger, Willy Heinz Hofmann