Patents by Inventor Ulrich Waltke
Ulrich Waltke 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: 10563511Abstract: A method for profiling a turbine rotor blade for an axial flow machine, having the following steps: providing a geometric model of a blade profile, having a camber line of a profile section of the turbine rotor blade; determining boundary conditions for a flow flowing around the turbine rotor blade; changing the camber line such that the flow which is adjusted by the boundary conditions produces the maximum of the difference of the isentropic mach number between the pressure side and the suction side of the turbine rotor blade in a blade section which extends from the blade trailing edge in the direction towards the blade leading edge and the length of which is 65% of the length S of the blade chord.Type: GrantFiled: April 18, 2016Date of Patent: February 18, 2020Assignee: Siemens AktiengesellschaftInventors: Christian Peeren, Stefan Schmitt, Ulrich Waltke, Heinrich Stüer
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Patent number: 10415576Abstract: An ascertainment method for determining a final angle of vanes that are adjustable between an initial angle and the final angle and are part of a row of leading vanes which are arranged upstream of a row of trailing vanes of a compressor in a gas turbine, in order to prevent ice from forming in the compressor. During operation of the gas turbine, a current value of at least one process parameter is determined in a parameter ascertainment step, whereupon the final angle is defined in accordance with the value in a final-angle defining step, an aerodynamic speed being determined as the process parameter.Type: GrantFiled: November 28, 2014Date of Patent: September 17, 2019Assignee: Siemens AktiengesellschaftInventors: Stefan Braun, Tjark Eisfeld, Marco Larson, Ulrich Waltke
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Publication number: 20180100399Abstract: A method for profiling a turbine rotor blade for an axial flow machine, having the following steps: providing a geometric model of a blade profile, having a camber line of a profile section of the turbine rotor blade; determining boundary conditions for a flow flowing around the turbine rotor blade; changing the camber line such that the flow which is adjusted by the boundary conditions produces the maximum of the difference of the isentropic mach number between the pressure side and the suction side of the turbine rotor blade in a blade section which extends from the blade trailing edge in the direction towards the blade leading edge and the length of which is 65% of the length S of the blade chord.Type: ApplicationFiled: April 18, 2016Publication date: April 12, 2018Applicant: Siemens AktiengesellschaftInventors: Christian Peeren, Stefan Schmitt, Ulrich Waltke, Heinrich Stüer
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Publication number: 20180094533Abstract: A device for detecting the rotational angle of the position of a plurality of adjustable guide vanes of a gas turbine, has at least three rotational angle sensors at different locations of the gas turbine, wherein the rotational angle sensors are designed to measure the rotational angle of guide vanes at the respective locations, and has an analyzing unit which is designed to calculate at least three rotational angle changes between each set of two different rotational angle sensors and to provide the at least three rotational angle changes.Type: ApplicationFiled: February 24, 2016Publication date: April 5, 2018Applicant: Siemens AktiengesellschaftInventors: Hans-Georg Gamm, Ulrich Waltke
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Publication number: 20160327051Abstract: A ascertainment method for determining a final angle of vanes that are adjustable between an initial angle and the final angle and are part of a row of leading vanes which are arranged upstream of a row of trailing vanes of a compressor in a gas turbine, in order to prevent ice from forming in the compressor. During operation of the gas turbine, a current value of at least one process parameter is determined in a parameter ascertainment step, whereupon the final angle is defined in accordance with the value in a final-angle defining step, an aerodynamic speed being determined as the process parameter.Type: ApplicationFiled: November 28, 2014Publication date: November 10, 2016Applicant: Siemens AktiengesellschaftInventors: Stefan Braun, Tjark Eisfeld, Marco Larson, Ulrich Waltke
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Patent number: 8721272Abstract: A ring diffuser for an axial turbomachine is provided. The ring diffuser includes an outer wall and an inner wall coaxial thereto, between which a diffuser channel extends in a ring shape along an axial extension from an inflow-side end diverging to an outflow-side end, wherein the inner wall and the outer wall each include a wall surface bounding the diffuser channel. In order to specify a diffuser channel that is tailored to an inflow that is uneven along the circumference and that facilitates a particularly efficient conversion of kinetic energy into static energy, a rotationally asymmetric wall surface bounding the diffuser channel on the inlet side is provided.Type: GrantFiled: November 19, 2009Date of Patent: May 13, 2014Assignee: Siemens AktiengesellschaftInventors: Christian Cornelius, Bernhard Küsters, Ulrich Waltke
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Patent number: 8721273Abstract: An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.Type: GrantFiled: January 17, 2012Date of Patent: May 13, 2014Assignee: Siemens AktiengesellschaftInventors: Christian Cornelius, Bernhard Küsters, Ulrich Waltke
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Patent number: 8622708Abstract: A stator blade and a stator blade arrangement for a turbomachine which is exposable to axial throughflow is provided. Each stator blade is retained via a fixed clamping in a circumferential groove. For the fixed clamping, provision is made on one side of the blade root for a shaped piece with a threaded hole into which a tensioning screw, which is supported on the bottom of the circumferential groove, may be screwed.Type: GrantFiled: August 26, 2010Date of Patent: January 7, 2014Assignee: Siemens AktiengesellschaftInventors: Bernhard Küsters, Marc Mittelbach, Uwe Sieber, Ulrich Waltke, Dirk Wistuba
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Publication number: 20120121401Abstract: An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.Type: ApplicationFiled: January 17, 2012Publication date: May 17, 2012Inventors: Christian CORNELIUS, Bernhard KÜSTERS, Ulrich WALTKE
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Patent number: 8157531Abstract: A closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery is provided. The assembly includes at least two parts each of which can be hooked onto projections that form an undercut in the peripheral groove and includes a securing element, which secures the parts from becoming detached from the peripheral groove. For closing the remaining gap, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web can be positioned by rotation is such a way that to fit the parts in the peripheral groove. The parts can be displaced in relation to one another and to secure the parts from being detached from the groove. The web can be placed against at least one lateral face of one of the parts.Type: GrantFiled: December 27, 2006Date of Patent: April 17, 2012Assignee: Siemens AktiengesellschaftInventors: Joachim Krützfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schröder, Michael Schwarz, Ulrich Waltke
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Patent number: 8157530Abstract: A closing assembly is provided. The closing assembly closes the gap remaining between the first blade and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, the assembly consisting of at least two lateral parts, at least one of which may be hooked onto a projection that forms an undercut in the peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit.Type: GrantFiled: December 27, 2006Date of Patent: April 17, 2012Assignee: Siemens AktiengesellschaftInventors: Joachim Krützfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schröder, Michael Schwarz, Ulrich Waltke
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Publication number: 20110311355Abstract: An axial turbo-compressor for a gas turbine having a stator vane assembly that is formed by stator vanes having vane tips exposed on the hub side and a stationary shaft cover on the hub side and delimits the flow channel of the axial compressor is provided. A radial gap is designed between the shaft cover and the van tips that is minimally sized such that the axial turbo-compressor may still be assembled, and there is a plurality of recesses in the shaft cover, wherein one of the recesses is allocated to each vane tip that is arranged directly neighboring the vane tip allocated thereto and is sized such that during operation of the axial turbo compressor every vane tip may be plunged into the recess allocated thereto without one of the vane tips significantly contacting the shaft cover.Type: ApplicationFiled: January 27, 2010Publication date: December 22, 2011Inventors: Francois Benkler, Karl Klein, Torsten Matthias, Achim Schirrmacher, Oliver Schneider, Vadim Shevchenko, Ulrich Waltke
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Publication number: 20110250055Abstract: A ring diffuser for an axial turbomachine is provided. The ring diffuser includes an outer wall and an inner wall coaxial thereto, between which a diffuser channel extends in a ring shape along an axial extension from an inflow-side end diverging to an outflow-side end, wherein the inner wall and the outer wall each include a wall surface bounding the diffuser channel. In order to specify a diffuser channel that is tailored to an inflow that is uneven along the circumference and that facilitates a particularly efficient conversion of kinetic energy into static energy, a rotationally asymmetric wall surface bounding the diffuser channel on the inlet side is provided.Type: ApplicationFiled: November 19, 2009Publication date: October 13, 2011Inventors: Christian Cornelius, Bernhard Küsters, Ulrich Waltke
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Publication number: 20110052397Abstract: A stator blade and a stator blade arrangement for a turbomachine which is exposable to axial throughflow is provided. Each stator blade is retained via a fixed clamping in a circumferential groove. For the fixed clamping, provision is made on one side of the blade root for a shaped piece with a threaded hole into which a tensioning screw, which is supported on the bottom of the circumferential groove, may be screwed.Type: ApplicationFiled: August 26, 2010Publication date: March 3, 2011Inventors: Bernhard Kusters, Marc Mittelbach, Uwe Sieber, Ulrich Waltke, Dirk Wistuba
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Publication number: 20090220345Abstract: The invention relates to a closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery. Said assembly comprises at least two parts each of which can be hooked onto projections that form an undercut in said peripheral groove and comprises a securing element, which secures the parts from becoming detached from the peripheral groove. To provide a closing assembly for closing the remaining gap, which can be simply and cost-effectively detached and which reliably withstands high mechanical stress, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web.Type: ApplicationFiled: December 27, 2006Publication date: September 3, 2009Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Joachim Krützfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schröder, Michael Schwarz, Ulrich Waltke
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Publication number: 20090016889Abstract: The invention relates to a closing assembly for closing the gap remaining between the first and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, said assembly consisting of at least two lateral parts, at least one of which can be hooked onto a projection that forms an undercut in said peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit.Type: ApplicationFiled: December 27, 2006Publication date: January 15, 2009Inventors: Joachim Krutzfeldt, Markus Kunze, Silvio-Ulrich Martin, Stefan Mutke, Kang Qian, Christoph Richter, Oliver Schneider, Peter Schroder, Michael Schwarz, Ulrich Waltke
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Patent number: 6647602Abstract: Described is a fixation device for blading of a turbo-machine, in which, longitudinally to a mounting groove (1), a plurality of blades (31, 32) is positioned, and in which, between at least two blades (31, 32) positioned adjacent to each other inside the mounting groove (1), a mounting gap is provided, having two insertion elements constructed as collar halves (41, 42) that can be inserted into the mounting gap, and each of which has a width adapted to the width of the mounting gap and which enclose between themselves a gap space (5) into which a wedge element (43) can be inserted that can be wedged in such a way that both collar halves (41, 42) are fixed in a force-derived manner by means of the wedge element (43) inside the mounting groove (1).Type: GrantFiled: November 30, 2001Date of Patent: November 18, 2003Assignee: Alstom (Switzerland) LtdInventors: René Bachofner, Wolfgang Kappis, Pavel Rihak, Ferdinand Thueringer, Ulrich Waltke, Hans Wettstein
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Patent number: 6575693Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.Type: GrantFiled: June 25, 2001Date of Patent: June 10, 2003Assignee: Alstom (Switzerland) LtdInventors: Joerg Pross, Thomas Kramer, Ulrich Waltke
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Publication number: 20020182081Abstract: A device for fastening a moving blade (3) to a rotor (2) of a thermal turbomachine is described. The moving blade (3) has a blade root (36), a blade leaf (32) and a platform (31) arranged between the blade root (36) and the blade leaf (32) and having at least two side flanks (33, 34). The idea, on which the invention is based, of avoiding axial forces occurring on the rotor (2) on account of bearing faces set obliquely to the rotor axis (4) between two adjacent moving blades (3) is that adjacent moving blades (3) meet solely at axially oriented bearing faces (52).Type: ApplicationFiled: April 18, 2002Publication date: December 5, 2002Inventors: Rene Bachofner, Urban Eschbach, Michael Mueller, Guenter Regnath, Ulrich Waltke
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Publication number: 20020127105Abstract: A device is shown for fixing blades of a turbo-machine having a plurality of blades positioned longitudinally relative to a mounting groove. At least two blades are positioned adjacent to each other inside the mounting groove, and a mounting gap is defined between the blades. Two insertion elements constructed as collar halves can be inserted into the mounting gap, and each insertion element has a width adapted to the width of the mounting gap such that a gap space is defined between the insertion elements when they are inserted into the mounting gap. A wedge element can be inserted in the mounting gap to fix both collar halves inside the mounting groove. At least one connecting element is provided on the wedge element towards the side of a blade, and at least one of the two blades adjoining the wedge element is provided with a mating recess corresponding to the connecting element so that the wedge element and the blade are connected by a shape-mated connection.Type: ApplicationFiled: November 30, 2001Publication date: September 12, 2002Inventors: Rene Bachofner, Wolfgang Kappis, Pavel Rihak, Ferdinand Thueringer, Ulrich Waltke, Hans Wettstein