Patents by Inventor Anthony J. Malandra
Anthony J. Malandra 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: 9920625Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).Type: GrantFiled: January 13, 2011Date of Patent: March 20, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Christopher Rawlings, Robert M. Dysert, Billie E. Sealey, Jose Paulino, Anthony J. Malandra
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Patent number: 9797267Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 2, 3, and 4.Type: GrantFiled: November 24, 2015Date of Patent: October 24, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Andrew S. Lohaus, Anthony J. Malandra, Carmen Andrew Scribner, Farzad Taremi, Horia Flitan, Ching-Pang Lee, Gm Salam Azad, Tobias Buchal
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Publication number: 20160177723Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 2, 3, and 4.Type: ApplicationFiled: November 24, 2015Publication date: June 23, 2016Inventors: Andrew S. Lohaus, Anthony J. Malandra, Carmen Andrew Scribner, Farzad Taremi, Horia Flitan, Ching-Pang Lee, Gm Salam Azad, Tobias Buchal
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Patent number: 9115602Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.Type: GrantFiled: October 15, 2013Date of Patent: August 25, 2015Assignee: Siemens AktiengesellschaftInventors: Anthony J. Malandra, John A. Orosa
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Patent number: 8864457Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 3, 5 and 7.Type: GrantFiled: August 20, 2012Date of Patent: October 21, 2014Assignee: Siemens Energy, Inc.Inventors: Anthony J. Malandra, Ching-Pang Lee, Barry J. Brown, Eric Munoz
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Publication number: 20140041357Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.Type: ApplicationFiled: October 15, 2013Publication date: February 13, 2014Inventors: Anthony J. Malandra, John A. Orosa
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Publication number: 20130089415Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 3, 5 and 7.Type: ApplicationFiled: August 20, 2012Publication date: April 11, 2013Inventors: Barry J. Brown, Ching-Pang Lee, Anthony J. Malandra, Eric Munoz
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Publication number: 20120269649Abstract: A turbine blade (110) is provided, where an exterior surface of the turbine blade (110) is exposed to a hot combustion gas (125) above a flow path line (141). The turbine blade (110) includes a trailing edge pin bank cooling channel (118) in an airfoil section (112), a cooling air supply channel (120) in a root section (114), and a channel (122) shaped with a radius of curvature (126), to extend the channel (122) across the flow path line (141) and interconnect the cooling air supply channel (120) to the trailing edge pin bank cooling channel (118). A width of the trailing edge pin bank cooling channel (118) is adjusted, such that the width at an inner diameter region (128) and an outer diameter region (131) is less than the width at an intermediate region (130) between the inner and outer diameter regions (128,131).Type: ApplicationFiled: April 22, 2011Publication date: October 25, 2012Inventors: Christopher Rawlings, Robert M. Dysert, Billie E. Sealey, Jose Paulino, Anthony J. Malandra
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Publication number: 20120183405Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).Type: ApplicationFiled: January 13, 2011Publication date: July 19, 2012Inventors: Christopher Rawlings, Robert M. Dysert, Billie E. Sealey, Jose Paulino, Anthony J. Malandra
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Patent number: 7632075Abstract: A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z.Type: GrantFiled: February 15, 2007Date of Patent: December 15, 2009Assignee: Siemens Energy, Inc.Inventors: George Liang, Anthony J. Malandra
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Publication number: 20080273984Abstract: A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z.Type: ApplicationFiled: February 15, 2007Publication date: November 6, 2008Inventors: George Liang, Anthony J. Malandra
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Patent number: 5482435Abstract: A gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade. The shroud is cooled by cooling air passages formed within it. A radial cooling air supply hole directs cooling air directly from the blade root through the airfoil and to the shroud. A plurality of cooling air passages extend from the supply hole and are disposed adjacent bearing surfaces along which the shroud contacts the shroud of an adjacent blade. One of these cooling air holes is formed in the portion of the shroud that projects from the convex surface of the airfoil and another one of the cooling air holes is formed in the portion of the shroud that projects from the concave surface of the airfoil. The cooling air holes extend to the edge of the shroud and discharge the cooling through an opening in the edge.Type: GrantFiled: October 26, 1994Date of Patent: January 9, 1996Assignee: Westinghouse Electric CorporationInventors: Robert A. Dorris, William E. North, Anthony J. Malandra