Patents by Inventor Krishan Mohan
Krishan Mohan 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: 11371361Abstract: A turbine blade tip includes a tip cap disposed over a blade airfoil and having a pressure side edge and a suction side edge. A notch is formed by a radially inward step adjacent to the suction side edge of the tip cap. The notch is defined by a radially extending step wall and a radially outward facing land. The step wall extends radially inward from the suction side edge of the tip cap to the land, whereby the land is positioned radially inward in relation to a radially outer surface of the tip cap. The notch extends along at least a portion of the suction sidewall in a direction from the leading edge to the trailing edge. In a further aspect, a method is provided for servicing a blade that includes machining a suction side notch as described above.Type: GrantFiled: August 7, 2018Date of Patent: June 28, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Ali Akturk, Taylor Hynds, Krishan Mohan, David Monk, Jose L. Rodriguez
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Patent number: 11293288Abstract: A turbine blade includes a tip cap disposed over an outer wall of a blade airfoil. A trench is defined on a radially outer side of the tip cap facing a hot gas path fluid. The trench is formed by a trench floor flanked on laterally opposite sides by first and second trench side faces such that the trench floor is located radially inwardly in relation to a radially outer surface of the tip cap. The trench extends from a trench inlet located at or proximal to an airfoil leading edge to a trench outlet located at or proximal to an airfoil trailing edge. The trench is configured to entrain a tip leakage flow from the trench inlet to the trench outlet.Type: GrantFiled: October 31, 2017Date of Patent: April 5, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ali Akturk, Andrew Miller, Krishan Mohan, David Monk
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Publication number: 20210199015Abstract: A turbine blade includes a tip cap disposed over an outer wall of a blade airfoil. A trench is defined on a radially outer side of the tip cap facing a hot gas path fluid. The trench is formed by a trench floor flanked on laterally opposite sides by first and second trench side faces such that the trench floor is located radially inwardly in relation to a radially outer surface of the tip cap. The trench extends from a trench inlet located at or proximal to an airfoil leading edge to a trench outlet located at or proximal to an airfoil trailing edge. The trench is configured to entrain a tip leakage flow from the trench inlet to the trench outlet.Type: ApplicationFiled: October 31, 2017Publication date: July 1, 2021Inventors: Ali Akturk, Andrew Miller, Krishan Mohan, David Monk
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Publication number: 20200256198Abstract: A turbine blade tip includes a tip cap disposed over a blade airfoil and having a pressure side edge and a suction side edge. A notch is formed by a radially inward step adjacent to the suction side edge of the tip cap. The notch is defined by a radially extending step wall and a radially outward facing land. The step wall extends radially inward from the suction side edge of the tip cap to the land, whereby the land is positioned radially inward in relation to a radially outer surface of the tip cap. The notch extends along at least a portion of the suction sidewall in a direction from the leading edge to the trailing edge. In a further aspect, a method is provided for servicing a blade that includes machining a suction side notch as described above.Type: ApplicationFiled: August 7, 2018Publication date: August 13, 2020Inventors: Ali Akturk, Taylor Hynds, Krishan Mohan, David Monk, Jose L. Rodriguez
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Patent number: 10513929Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: August 31, 2017Date of Patent: December 24, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Niloofar Moradi, Krishan Mohan, Panagiota Tsifourdaris, Sami Girgis, Vincent Paradis, Robert Huszar, Jasrobin Grewal
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Patent number: 10487661Abstract: A power turbine includes a first stage vane having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: August 31, 2017Date of Patent: November 26, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Krishan Mohan, Panagiota Tsifourdaris
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Patent number: 10329915Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: September 1, 2017Date of Patent: June 25, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Krishan Mohan, Panagiota Tsifourdaris, Lorenzo Sanzari, Igal Acher Abenhaim, Anthony Pham
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Publication number: 20190071974Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: September 1, 2017Publication date: March 7, 2019Inventors: Krishan MOHAN, Panagiota TSIFOURDARIS, Lorenzo SANZARI, Igal Acher ABENHAIM, Anthony PHAM
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Publication number: 20190063225Abstract: A power turbine includes a first stage vane having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: August 31, 2017Publication date: February 28, 2019Inventors: Krishan MOHAN, Panagiota TSIFOURDARIS
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Publication number: 20190063226Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: August 31, 2017Publication date: February 28, 2019Inventors: Niloofar MORADI, Krishan MOHAN, Panagiota TSIFOURDARIS, Sami GIRGIS, Vincent PARADIS, Robert HUSZAR, Jasrobin GREWAL
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Patent number: 7632074Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2006Date of Patent: December 15, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Constantinos Ravanis, Krishan Mohan, Sami Girgis, Edward Vlasic
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Publication number: 20090274558Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: ApplicationFiled: November 28, 2006Publication date: November 5, 2009Inventors: Constantinos Ravanis, Krishan Mohan, Sami Girgis, Edward Vlasic
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Patent number: 7568890Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: August 4, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Peter Findlay, Krishan Mohan, Saml Girgis
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Patent number: 7568889Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: August 4, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Krishan Mohan, Sami Girgis
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Patent number: 7568891Abstract: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: August 4, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Krishan Mohan, Sami Girgis
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Patent number: 7559747Abstract: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are Joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: July 14, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Krishan Mohan, Sami Girgis
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Patent number: 7559746Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: November 22, 2006Date of Patent: July 14, 2009Assignee: pratt & Whitney Canada Corp.Inventors: Panagiota Tsifourdaris, Krishan Mohan, Sami Girgis
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Patent number: 7537433Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: September 5, 2006Date of Patent: May 26, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Sami Girgis, Krishan Mohan
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Patent number: 7534091Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: September 5, 2006Date of Patent: May 19, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Constantinos Ravanis, Sami Girgis, Krishan Mohan
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Patent number: 7402026Abstract: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: March 2, 2006Date of Patent: July 22, 2008Assignee: Pratt & Whitney Canada Corp.Inventors: Sami Girgis, Krishan Mohan, Mona El-Fouly