Patents by Inventor Ya-Tien Chiu
Ya-Tien Chiu 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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Publication number: 20240044257Abstract: A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.Type: ApplicationFiled: August 4, 2022Publication date: February 8, 2024Inventors: Ya-tien Chiu, Giridhar Jothiprasad, David V. Parker, Michael Macrorie
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Patent number: 10041370Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: September 4, 2015Date of Patent: August 7, 2018Assignee: General Electric CompanyInventors: Ya-Tien Chiu, Chih Fang
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Patent number: 9732761Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: September 4, 2015Date of Patent: August 15, 2017Assignee: General Electric CompanyInventors: Ya-Tien Chiu, John David Dyer
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Publication number: 20170067357Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: September 4, 2015Publication date: March 9, 2017Inventors: Ya-Tien Chiu, Chih Fang
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Publication number: 20170067475Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: September 4, 2015Publication date: March 9, 2017Inventors: Ya-Tien Chiu, John David Dyer
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Patent number: 9175693Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: June 19, 2012Date of Patent: November 3, 2015Assignee: General Electric CompanyInventors: Michael James Dutka, John Duong, Ya-Tien Chiu, Alexander David Shrum, Kelvin Rono Aaron, Christopher Edward LaMaster, San-Dar Gau, Franco Monteleone, Paul Griffin Delvernois, Matthew John McKeever, Govindarajan Rengarajan, Jeremy Peter Latimer, Marc Edward Blohm, Eric Richard Bonini, Venkata Siva Prasad Chaluvadi
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Patent number: 9145777Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: July 24, 2012Date of Patent: September 29, 2015Assignee: General Electric CompanyInventors: Michael James Dutka, John Duong, Ya-Tien Chiu, Alexander David Shrum, Kelvin Rono Aaron, Christopher Edward LaMaster, San-Dar Gau, Franco Monteleone, Paul Griffin Delvernois, Matthew John McKeever, Govindarajan Rengarajan, Jeremy Peter Latimer, Marc Edward Blohm, Eric Richard Bonini, Venkata Siva Prasad Chaluvadi, Jamie Dean Lumpkin, Thomas Robbins Tipton
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Patent number: 9017019Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: June 19, 2012Date of Patent: April 28, 2015Assignee: General Electric CompanyInventors: Matthew John McKeever, Gang Liu, Umesh Garg, Ryan Wesley Murphy, Edward Charles Schurr, Michael James Dutka, Govindarajan Rengarajan, Paul Griffin Delvernois, Ya-Tien Chiu, Roger Claude Beharrysingh, Marc Edward Blohm, SenthilKumar Narendran
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Publication number: 20140130513Abstract: A compressor section of a gas turbine generally includes a stage of inlet guide vanes positioned adjacent to an inlet of the compressor section and a stage of rotor blades disposed downstream from the inlet guide vanes. A stage of stator vanes is positioned downstream from the stage of rotor blades. The stage of stator blades includes a row of leading guide vanes having a trailing edge. A row of trailing guide vanes coupled to an actuator is disposed between two corresponding adjacent leading guide vanes. Each of the trailing guide vanes includes a trailing edge. The leading edge of each trailing guide vane is disposed upstream of the trailing edge of a corresponding leading guide vane when the trailing guide vane is in an open position and downstream from the trailing edge of the corresponding leading guide vane when the trailing guide vane is in a closed position.Type: ApplicationFiled: November 9, 2012Publication date: May 15, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Ya-tien Chiu, John David Stampfli, Rudolf Selmeier
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Publication number: 20140030098Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a. characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: July 24, 2012Publication date: January 30, 2014Inventors: Michael James Dutka, John Duong, Ya-Tien Chiu, Alexander David Shrum, Kelvin Rono Aaron, Christopher Edward LaMaster, San-Dar Gau, Franco Monteleone, Paul Griffin Delvernois, Matthew John McKeever, Govindarajan Rengarajan, Jeremy Peter Latimer, Marc Edward Blohm, Eric Richard Bonini, Venkata Siva Prasad Chaluvadi, Jamie Dean Lumpkin, Thomas Robbins Tipton
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Patent number: 8616838Abstract: A compressor of a turbine engine, the compressor including stator blades with shrouds, the shrouds being surrounded, at least in part, by rotating structure and forming a shroud cavity therebetween, the compressor including: a plurality of tangential flow inducers disposed within the shroud cavity; wherein each tangential flow inducer comprises a surface disposed on the rotating structure that is configured such that, when rotated, induces a tangential directional component to and/or increases the velocity of a flow of leakage exiting the shroud cavity.Type: GrantFiled: December 31, 2009Date of Patent: December 31, 2013Assignee: General Electric CompanyInventors: Ya-Tien Chiu, Venkata S. P. Chaluvadi, Peter S. King
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Publication number: 20130336777Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: June 19, 2012Publication date: December 19, 2013Inventors: Matthew John McKeever, Gang Liu, Umesh Garg, Ryan Wesley Murphy, Edward Charles Schurr, Michael James Dutka, Govindarajan Rengarajan, Paul Griffin Delvernois, Ya-Tien Chiu, Roger Claude Beharrysingh, Marc Edward Blohm, SenthilKumar Narendran
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Publication number: 20130336798Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: June 19, 2012Publication date: December 19, 2013Inventors: Michael James Dutka, John Duong, Ya-Tien Chiu, Alexander David Shrum, Kelvin Rono Aaron, Christopher Edward LaMaster, San-Dar Gau, Franco Monteleone, Paul Griffin Delvernois, Matthew John McKeever, Govindarajan Rengarajan, Jeremy Peter Latimer, Marc Edward Blohm, Eric Richard Bonini, Venkata Siva Prasad Chaluvadi
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Patent number: 8578717Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.Type: GrantFiled: December 11, 2008Date of Patent: November 12, 2013Assignee: Nuovo Pignone S.p.A.Inventors: Giovanni Tonno, Mariateresa Paci, Michele D'Ercole, Alessandro Russo, Jesse F. Stewart, Ya-Tien Chiu, Marco Ulivi, Antonio Baldassarre
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Patent number: 8348599Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.Type: GrantFiled: March 26, 2010Date of Patent: January 8, 2013Assignee: General Electric CompanyInventors: Ya-Tien Chiu, Venkata Siva Chaluvadi, Matthew Ryan Ferslew
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Publication number: 20120076642Abstract: A method of assembling a sealing assembly for a turbomachine is provided. The method includes positioning at least one sealing element that includes a substantially tortuous flow path defined therein within at least one channel defined in a rotatable element of the turbomachine. The sealing element is extended circumferentially about the rotatable element such that the sealing element extends into a cavity defined between the rotatable element and a stationary element. This facilitates substantially reducing flow leakage from an upstream region of the cavity to a downstream region of the cavity.Type: ApplicationFiled: September 23, 2010Publication date: March 29, 2012Inventors: Ya-Tien Chiu, James Royce Howes
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Publication number: 20110236190Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.Type: ApplicationFiled: March 26, 2010Publication date: September 29, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Ya-Tien Chiu, Venkata Siva Chaluvadi, Matthew Ryan Ferslew
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Publication number: 20110158797Abstract: A compressor of a turbine engine, the compressor including stator blades with shrouds, the shrouds being surrounded, at least in part, by rotating structure and forming a shroud cavity therebetween, the compressor including: a plurality of tangential flow inducers disposed within the shroud cavity; wherein each tangential flow inducer comprises a surface disposed on the rotating structure that is configured such that, when rotated, induces a tangential directional component to and/or increases the velocity of a flow of leakage exiting the shroud cavity.Type: ApplicationFiled: December 31, 2009Publication date: June 30, 2011Inventors: Ya-Tien Chiu, Venkata S.P. Chaluvadi, Peter S. King
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Publication number: 20090158702Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.Type: ApplicationFiled: December 11, 2008Publication date: June 25, 2009Inventors: Giovanni TONNO, Mariateresa PACI, Michele D'ERCOLE, Alessandro RUSSO, Jesse F. STEWART, Ya-Tien CHIU, Marco ULIVI, Antonio BALDASSARRE