Patents by Inventor Vincent C. Martling
Vincent C. Martling 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: 11377970Abstract: A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.Type: GrantFiled: November 2, 2018Date of Patent: July 5, 2022Assignee: Chromalloy Gas Turbine LLCInventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling
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Patent number: 11306918Abstract: A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle, a height, and a base width, where the base width is a function of the height and where the turbulators are spaced an axial distance apart that is a function of the turbulator height.Type: GrantFiled: November 2, 2018Date of Patent: April 19, 2022Assignee: Chromalloy Gas Turbine LLCInventors: Daniel L. Folkers, Vincent C. Martling, Zhenhua Xiao, John Bacile
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Patent number: 11248797Abstract: An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.Type: GrantFiled: November 2, 2018Date of Patent: February 15, 2022Assignee: Chromalloy Gas Turbine LLCInventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling, Adam L. Hart
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Patent number: 11021977Abstract: A guide vane for use in a compressor discharge plenum of a gas turbine engine is disclosed. The guide vane comprises a guide support system, a first side panel, a second side panel, and a deflector panel secured to the mounting system and extending between the first side panel and the second side panel. The deflector panel has a curved profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1 where the X, Y, and Z values are in inches from a center point of a bottom surface of the deflector panel. The coordinate values are connected by smooth continuing arcs to form profile sections and the profile sections are joined together smoothly to form the curved profile of the guide vane.Type: GrantFiled: November 2, 2018Date of Patent: June 1, 2021Assignee: Chromalloy Gas Turbine LLCInventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling, Mariano Medrano
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Patent number: 10837298Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately +/?0.049 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: GrantFiled: August 21, 2018Date of Patent: November 17, 2020Assignee: Chromalloy Gas Turbine LLCInventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Mariano Medrano, Jr., Charles A. Ellis
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Patent number: 10711615Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: GrantFiled: August 21, 2018Date of Patent: July 14, 2020Assignee: Chromalloy Gas Turbine LLCInventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Wesley Smith, David Medrano, Charles A. Ellis
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Publication number: 20200141250Abstract: A guide vane for use in a compressor discharge plenum of a gas turbine engine is disclosed. The guide vane comprises a guide support system, a first side panel, a second side panel, and a deflector panel secured to the mounting system and extending between the first side panel and the second side panel. The deflector panel has a curved profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1 where the X, Y, and Z values are in inches from a center point of a bottom surface of the deflector panel. The coordinate values are connected by smooth continuing arcs to form profile sections and the profile sections are joined together smoothly to form the curved profile of the guide vane.Type: ApplicationFiled: November 2, 2018Publication date: May 7, 2020Inventors: DANIEL L. FOLKERS, ZHENHUA XIAO, VINCENT C. MARTLING, MARIANO MEDRANO
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Publication number: 20200141576Abstract: A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle, a height, and a base width, where the base width is a function of the height and where the turbulators are spaced an axial distance apart that is a function of the turbulator height.Type: ApplicationFiled: November 2, 2018Publication date: May 7, 2020Inventors: DANIEL L. FOLKERS, VINCENT C. MARTLING, ZHENHUA XIAO, JOHN BACILE
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Publication number: 20200141585Abstract: An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.Type: ApplicationFiled: November 2, 2018Publication date: May 7, 2020Inventors: DANIEL L. FOLKERS, ZHENHUA XIAO, VINCENT C. MARTLING, ADAM L. HART
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Publication number: 20200141252Abstract: A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.Type: ApplicationFiled: November 2, 2018Publication date: May 7, 2020Inventors: DANIEL L. FOLKERS, ZHENHUA XIAO, VINCENT C. MARTLING
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Patent number: 10590782Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: GrantFiled: August 21, 2018Date of Patent: March 17, 2020Assignee: CHROMALLOY GAS TURBINE LLCInventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
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Patent number: 10590772Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X, Y, and Z distances may be scaled as a function of the same constant number and the X, Y, and Z distances lie within an envelope of approximately +/?0.032 inches in directions normal to the airfoil.Type: GrantFiled: August 21, 2018Date of Patent: March 17, 2020Assignee: CHROMALLOY GAS TURBINE LLCInventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, James Page Strohl
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Publication number: 20200063570Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X, Y, and Z distances may be scaled as a function of the same constant number and the X, Y, and Z distances lie within an envelope of approximately +/?0.032 inches in directions normal to the airfoil.Type: ApplicationFiled: August 21, 2018Publication date: February 27, 2020Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, James Page Strohl
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Publication number: 20200063565Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: ApplicationFiled: August 21, 2018Publication date: February 27, 2020Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Wesley Smith, David Medrano, Charles A. Ellis
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Publication number: 20200063580Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: ApplicationFiled: August 21, 2018Publication date: February 27, 2020Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
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Publication number: 20200063579Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately +/?0.049 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.Type: ApplicationFiled: August 21, 2018Publication date: February 27, 2020Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Mariano Medrano, JR., Charles A. Ellis
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Patent number: 8504276Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.Type: GrantFiled: February 28, 2008Date of Patent: August 6, 2013Assignee: Power Systems Mfg., LLCInventors: Vincent C. Martling, Peter So, Zhenhua Xiao, Plazi Ricklin
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Patent number: 7685823Abstract: An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.Type: GrantFiled: October 28, 2005Date of Patent: March 30, 2010Assignee: Power Systems Mfg., LLCInventors: Vincent C. Martling, Zhenhua Xiao
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Publication number: 20090222187Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.Type: ApplicationFiled: February 28, 2008Publication date: September 3, 2009Applicant: POWER SYSTEMS MFG., LLCInventors: VINCENT C. MARTLING, Peter SO, ZHENHUA XIAO, PLAZI RICKLIN
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Publication number: 20090139238Abstract: An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.Type: ApplicationFiled: October 28, 2005Publication date: June 4, 2009Inventors: Vincent C. Martling, Zhenhua Xiao